From c24d4a6e704187fcbc8be863a761b06115dcca51 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Tue, 23 Jul 2024 22:00:11 -0400 Subject: [PATCH 001/113] cannonball multi mission exampls --- cannonball.py | 294 +++++++++++++++++++++++++++++++++++++++++++++ cannonball_copy.py | 274 ++++++++++++++++++++++++++++++++++++++++++ 2 files changed, 568 insertions(+) create mode 100644 cannonball.py create mode 100644 cannonball_copy.py diff --git a/cannonball.py b/cannonball.py new file mode 100644 index 000000000..ba9bb8088 --- /dev/null +++ b/cannonball.py @@ -0,0 +1,294 @@ +from os import stat +import numpy as np +from scipy.interpolate import interp1d +import matplotlib.pyplot as plt +import openmdao.api as om +import dymos as dm +from dymos.models.atmosphere.atmos_1976 import USatm1976Data + +""" +Currently has linked sizing and motion ODEs, want to add ability to have +multiple trajectories (and associated ODEs) that are linked with the same +sizing class. radii/density etc can be defined as 1xn inputs, with n corresponding +to num of missions. + +Additionally need to incorporate some output into a compound objective that is optimized, +aside from each mission optimizing for max range. Could for example assign $/kg of material. + +Could also add a "fuel" parameter which can then be minimized. +""" + + +class CannonballSizing(om.ExplicitComponent): + def setup(self): + self.add_input(name='radius', val=1.0, units='m') + self.add_input(name='dens', val=7870., units='kg/m**3') + + self.add_output(name='mass', shape=(1,), units='kg') + self.add_output(name='S', shape=(1,), units='m**2') + self.add_output(name='price', shape=(1,), units='USD') + + self.declare_partials(of='mass', wrt='dens') + self.declare_partials(of='mass', wrt='radius') + self.declare_partials(of='S', wrt='radius') + self.declare_partials(of='price', wrt='radius') + self.declare_partials(of='price', wrt='dens') + + def compute(self, inputs, outputs): + radius = inputs['radius'] + dens = inputs['dens'] + outputs['mass'] = (4/3.) * dens * np.pi * radius ** 3 + outputs['S'] = np.pi * radius ** 2 + outputs['price'] = (4/3.) * dens * np.pi * radius ** 3 * 10 # $10 per kg + + def compute_partials(self, inputs, partials): + radius = inputs['radius'] + dens = inputs['dens'] + partials['mass', 'dens'] = (4/3.) * np.pi * radius ** 3 + partials['mass', 'radius'] = 4. * dens * np.pi * radius ** 2 + partials['S', 'radius'] = 2 * np.pi * radius + partials['price', 'dens'] = (4/3.) * np.pi * radius ** 3 * 10 + partials['price', 'radius'] = 4. * dens * np.pi * radius ** 2 * 10 + + +class CannonballODE(om.ExplicitComponent): + def initialize(self): + self.options.declare('num_nodes', types=int) + + def setup(self): + nn = self.options['num_nodes'] + # static params + self.add_input('m', units='kg') + self.add_input('S', units='m**2') + self.add_input('CD', 0.5) + + # time varying inputs + self.add_input('h', units='m', shape=nn) + self.add_input('v', units='m/s', shape=nn) + self.add_input('gam', units='rad', shape=nn) + + # state rates + self.add_output('v_dot', shape=nn, units='m/s**2', + tags=['dymos.state_rate_source:v']) + self.add_output('gam_dot', shape=nn, units='rad/s', + tags=['dymos.state_rate_source:gam']) + self.add_output('h_dot', shape=nn, units='m/s', + tags=['dymos.state_rate_source:h']) + self.add_output('r_dot', shape=nn, units='m/s', + tags=['dymos.state_rate_source:r']) + self.add_output('ke', shape=nn, units='J') + + # Ask OpenMDAO to compute the partial derivatives using complex-step + # with a partial coloring algorithm for improved performance, and use + # a graph coloring algorithm to automatically detect the sparsity pattern. + self.declare_coloring(wrt='*', method='cs') + + alt_data = USatm1976Data.alt * om.unit_conversion('ft', 'm')[0] + rho_data = USatm1976Data.rho * om.unit_conversion('slug/ft**3', 'kg/m**3')[0] + self.rho_interp = interp1d(np.array(alt_data, dtype=complex), + np.array(rho_data, dtype=complex), + kind='linear') + + def compute(self, inputs, outputs): + + gam = inputs['gam'] + v = inputs['v'] + h = inputs['h'] + m = inputs['m'] + S = inputs['S'] + CD = inputs['CD'] + + GRAVITY = 9.80665 # m/s**2 + + # handle complex-step gracefully from the interpolant + if np.iscomplexobj(h): + rho = self.rho_interp(inputs['h']) + else: + rho = self.rho_interp(inputs['h']).real + + q = 0.5*rho*inputs['v']**2 + qS = q * S + D = qS * CD + cgam = np.cos(gam) + sgam = np.sin(gam) + outputs['v_dot'] = - D/m-GRAVITY*sgam + outputs['gam_dot'] = -(GRAVITY/v)*cgam + outputs['h_dot'] = v*sgam + outputs['r_dot'] = v*cgam + outputs['ke'] = 0.5*m*v**2 + + +# ODEs are unique to each traj created +def createTrajectory(ke_max): + traj = dm.Trajectory() + transcription = dm.Radau(num_segments=5, order=3, compressed=True) + ascent = dm.Phase(ode_class=CannonballODE, transcription=transcription) + traj.add_phase('ascent', ascent) + + transcription = dm.GaussLobatto(num_segments=5, order=3, compressed=True) + descent = dm.Phase(ode_class=CannonballODE, transcription=transcription) + traj.add_phase('descent', descent) + + for phase in (ascent, descent): + is_ascent = phase.name == "ascent" + phase.set_time_options(fix_initial=True if is_ascent else False, + duration_bounds=(1, 100), duration_ref=100, units='s') + phase.set_state_options('r', fix_initial=is_ascent, fix_final=False) + phase.set_state_options('h', fix_initial=is_ascent, fix_final=not is_ascent) + phase.set_state_options('gam', fix_initial=False, fix_final=is_ascent) + phase.set_state_options('v', fix_initial=False, fix_final=False) + phase.add_parameter('S', units='m**2', static_target=True, val=0.005) + phase.add_parameter('m', units='kg', static_target=True, val=1.0) + phase.add_parameter('price', units='USD', static_target=True, val=10) + phase.add_parameter('CD', units=None, static_target=True, val=0.5) + + # descent.add_objective('r', loc='final', scaler=-1.0) # negative means to maximize + for param in ('CD', 'm', 'S', 'price'): + traj.add_parameter(param, static_target=True) + + # Link Phases (link time and all state variables) + traj.link_phases(phases=['ascent', 'descent'], vars=['*']) + # have to set muzzle energy here before setup for sim to run properly + ascent.add_boundary_constraint('ke', loc='initial', + upper=ke_max, lower=0, ref=100000) + return traj, ascent, descent + + +p = om.Problem(model=om.Group()) + +p.driver = om.ScipyOptimizeDriver() +p.driver.options['optimizer'] = 'SLSQP' +p.driver.declare_coloring() + +kes = [4e5, 5e5] +weights = [2, 1.01] +num_trajs = len(kes) + +p.model.add_subsystem(f"sizing_comp", CannonballSizing(), + promotes_inputs=['radius', 'dens']) + +p.model.set_input_defaults('dens', val=7.87, units='g/cm**3') +p.model.add_design_var('radius', lower=0.01, upper=0.10, + ref0=0.01, ref=0.10, units='m') + +trajs, ascents, descents = [], [], [] +for i, ke in enumerate(kes): + traj, ascent, descent = createTrajectory(ke) + p.model.add_subsystem(f"traj_{i}", traj) + + # Issue Connections + p.model.connect(f"sizing_comp.mass", f"traj_{i}.parameters:m") + p.model.connect(f"sizing_comp.S", f"traj_{i}.parameters:S") + p.model.connect(f"sizing_comp.price", f"traj_{i}.parameters:price") + trajs.append(traj) + ascents.append(ascent) + descents.append(descent) + +ranges = [f"r{i}" for i in range(num_trajs)] +weighted_sum_str = "+".join([f"{weight}*{r}" for r, weight in zip(ranges, weights)]) +p.model.add_subsystem('compoundComp', om.ExecComp("compound_range="+weighted_sum_str), + promotes=['compound_range', *ranges]) + +for i in range(num_trajs): + p.model.connect(f"traj_{i}.descent.states:r", ranges[i], src_indices=-1) + +p.model.add_objective('compound_range', scaler=-1) + + +# A linear solver at the top level can improve performance. +p.model.linear_solver = om.DirectSolver() +p.setup() + +p.set_val('radius', 0.05, units='m') +p.set_val('dens', 7.87, units='g/cm**3') + +for i, (ascent, descent) in enumerate(zip(ascents, descents)): + p.set_val(f"traj_{i}.parameters:CD", 0.5) + + p.set_val(f"traj_{i}.ascent.t_initial", 0.0) + p.set_val(f"traj_{i}.ascent.t_duration", 10.0) + # list is initial and final, based on phase info some are fixed others are not + p.set_val(f"traj_{i}.ascent.states:r", ascent.interp('r', [0, 100])) + p.set_val(f'traj_{i}.ascent.states:h', ascent.interp('h', [0, 100])) + p.set_val(f'traj_{i}.ascent.states:v', ascent.interp('v', [200, 150])) + p.set_val(f'traj_{i}.ascent.states:gam', ascent.interp('gam', [25, 0]), units='deg') + + p.set_val(f'traj_{i}.descent.t_initial', 10.0) + p.set_val(f'traj_{i}.descent.t_duration', 10.0) + + p.set_val(f'traj_{i}.descent.states:r', descent.interp('r', [100, 200])) + p.set_val(f'traj_{i}.descent.states:h', descent.interp('h', [100, 0])) + p.set_val(f'traj_{i}.descent.states:v', descent.interp('v', [150, 200])) + p.set_val(f'traj_{i}.descent.states:gam', + descent.interp('gam', [0, -45]), units='deg') + + +dm.run_problem(p, simulate=True) +sol = om.CaseReader('dymos_solution.db').get_case('final') +sim = om.CaseReader('dymos_simulation.db').get_case('final') + + +def plotstuff(): + print("\n\n=================================================") + print( + f"Optimized {num_trajs} trajectories with weights: {', '.join(map(str,weights))}") + rad = p.get_val('radius', units='m')[0] + mass = p.get_val('sizing_comp.mass', units='kg')[0] + price = p.get_val('sizing_comp.price', units='USD')[0] + area = p.get_val('sizing_comp.S', units='cm**2')[0] + print("Optimal Cannonball Description:") + print( + f"Radius: {rad:.2f} m, Mass: {mass:.2f} kg, Price: ${price:.2f}, Area: {area} sqcm") + + print("Optimal Trajectory Descriptions:") + for i, ke in enumerate(kes): + angle = p.get_val(f'traj_{i}.ascent.timeseries.gam', units='deg')[0, 0] + max_range = p.get_val(f'traj_{i}.descent.timeseries.r')[-1, 0] + + print( + f"KE: {ke/1e3:.2f} KJ, Launch Angle: {angle:.2f} deg, Max Range: {max_range:.2f} m") + + # fig, axes = plt.subplots(nrows=1, ncols=1, figsize=(10, 6)) + # time_imp = {'ascent': p.get_val('traj_0.ascent.timeseries.time'), + # 'descent': p.get_val('traj_0.descent.timeseries.time')} + # time_exp = {'ascent': sim.get_val('traj_0.ascent.timeseries.time'), + # 'descent': sim.get_val('traj_0.descent.timeseries.time')} + # r_imp = {'ascent': p.get_val('traj_0.ascent.timeseries.r'), + # 'descent': p.get_val('traj_0.descent.timeseries.r')} + # r_exp = {'ascent': sim.get_val('traj_0.ascent.timeseries.r'), + # 'descent': sim.get_val('traj_0.descent.timeseries.r')} + # h_imp = {'ascent': p.get_val('traj_0.ascent.timeseries.h'), + # 'descent': p.get_val('traj_0.descent.timeseries.h')} + # h_exp = {'ascent': sim.get_val('traj_0.ascent.timeseries.h'), + # 'descent': sim.get_val('traj_0.descent.timeseries.h')} + + # axes.plot(r_imp['ascent'], h_imp['ascent'], 'bo') + # axes.plot(r_imp['descent'], h_imp['descent'], 'ro') + # axes.plot(r_exp['ascent'], h_exp['ascent'], 'b--') + # axes.plot(r_exp['descent'], h_exp['descent'], 'r--') + + # axes.set_xlabel('range (m)') + # axes.set_ylabel('altitude (m)') + # axes.grid(True) + + # fig, axes = plt.subplots(nrows=4, ncols=1, figsize=(10, 6)) + # states = ['r', 'h', 'v', 'gam'] + # for i, state in enumerate(states): + # x_imp = {'ascent': sol.get_val(f'traj_0.ascent.timeseries.{state}'), + # 'descent': sol.get_val(f'traj_0.descent.timeseries.{state}')} + + # x_exp = {'ascent': sim.get_val(f'traj_0.ascent.timeseries.{state}'), + # 'descent': sim.get_val(f'traj_0.descent.timeseries.{state}')} + + # axes[i].set_ylabel(state) + # axes[i].grid(True) + + # axes[i].plot(time_imp['ascent'], x_imp['ascent'], 'bo') + # axes[i].plot(time_imp['descent'], x_imp['descent'], 'ro') + # axes[i].plot(time_exp['ascent'], x_exp['ascent'], 'b--') + # axes[i].plot(time_exp['descent'], x_exp['descent'], 'r--') + + # plt.show() + + +plotstuff() diff --git a/cannonball_copy.py b/cannonball_copy.py new file mode 100644 index 000000000..2124345ec --- /dev/null +++ b/cannonball_copy.py @@ -0,0 +1,274 @@ +from os import stat +import numpy as np +from scipy.interpolate import interp1d +import matplotlib.pyplot as plt +import openmdao.api as om +import dymos as dm +from dymos.models.atmosphere.atmos_1976 import USatm1976Data + +""" +Currently has linked sizing and motion ODEs, want to add ability to have +multiple trajectories (and associated ODEs) that are linked with the same +sizing class. radii/density etc can be defined as 1xn inputs, with n corresponding +to num of missions. + +Additionally need to incorporate some output into a compound objective that is optimized, +aside from each mission optimizing for max range. Could for example assign $/kg of material. + +Could also add a "fuel" parameter which can then be minimized. +""" +# Working version + + +class CannonballSizing(om.ExplicitComponent): + def setup(self): + self.add_input(name='radius', val=1.0, units='m') + self.add_input(name='dens', val=7870., units='kg/m**3') + + self.add_output(name='mass', shape=(1,), units='kg') + self.add_output(name='S', shape=(1,), units='m**2') + self.add_output(name='price', shape=(1,), units='USD') + + self.declare_partials(of='mass', wrt='dens') + self.declare_partials(of='mass', wrt='radius') + self.declare_partials(of='S', wrt='radius') + self.declare_partials(of='price', wrt='radius') + self.declare_partials(of='price', wrt='dens') + + def compute(self, inputs, outputs): + radius = inputs['radius'] + dens = inputs['dens'] + outputs['mass'] = (4/3.) * dens * np.pi * radius ** 3 + outputs['S'] = np.pi * radius ** 2 + outputs['price'] = (4/3.) * dens * np.pi * radius ** 3 * 10 # $10 per kg + + def compute_partials(self, inputs, partials): + radius = inputs['radius'] + dens = inputs['dens'] + partials['mass', 'dens'] = (4/3.) * np.pi * radius ** 3 + partials['mass', 'radius'] = 4. * dens * np.pi * radius ** 2 + partials['S', 'radius'] = 2 * np.pi * radius + partials['price', 'dens'] = (4/3.) * np.pi * radius ** 3 * 10 + partials['price', 'radius'] = 4. * dens * np.pi * radius ** 2 * 10 + + +class CannonballODE(om.ExplicitComponent): + def initialize(self): + self.options.declare('num_nodes', types=int) + + def setup(self): + nn = self.options['num_nodes'] + # static params + self.add_input('m', units='kg') + self.add_input('S', units='m**2') + self.add_input('CD', 0.5) + + # time varying inputs + self.add_input('h', units='m', shape=nn) + self.add_input('v', units='m/s', shape=nn) + self.add_input('gam', units='rad', shape=nn) + + # state rates + self.add_output('v_dot', shape=nn, units='m/s**2', + tags=['dymos.state_rate_source:v']) + self.add_output('gam_dot', shape=nn, units='rad/s', + tags=['dymos.state_rate_source:gam']) + self.add_output('h_dot', shape=nn, units='m/s', + tags=['dymos.state_rate_source:h']) + self.add_output('r_dot', shape=nn, units='m/s', + tags=['dymos.state_rate_source:r']) + self.add_output('ke', shape=nn, units='J') + + # Ask OpenMDAO to compute the partial derivatives using complex-step + # with a partial coloring algorithm for improved performance, and use + # a graph coloring algorithm to automatically detect the sparsity pattern. + self.declare_coloring(wrt='*', method='cs') + + alt_data = USatm1976Data.alt * om.unit_conversion('ft', 'm')[0] + rho_data = USatm1976Data.rho * om.unit_conversion('slug/ft**3', 'kg/m**3')[0] + self.rho_interp = interp1d(np.array(alt_data, dtype=complex), + np.array(rho_data, dtype=complex), + kind='linear') + + def compute(self, inputs, outputs): + + gam = inputs['gam'] + v = inputs['v'] + h = inputs['h'] + m = inputs['m'] + S = inputs['S'] + CD = inputs['CD'] + + GRAVITY = 9.80665 # m/s**2 + + # handle complex-step gracefully from the interpolant + if np.iscomplexobj(h): + rho = self.rho_interp(inputs['h']) + else: + rho = self.rho_interp(inputs['h']).real + + q = 0.5*rho*inputs['v']**2 + qS = q * S + D = qS * CD + cgam = np.cos(gam) + sgam = np.sin(gam) + outputs['v_dot'] = - D/m-GRAVITY*sgam + outputs['gam_dot'] = -(GRAVITY/v)*cgam + outputs['h_dot'] = v*sgam + outputs['r_dot'] = v*cgam + outputs['ke'] = 0.5*m*v**2 + + +def createTrajectory(ke_max): + traj = dm.Trajectory() + transcription = dm.Radau(num_segments=5, order=3, compressed=True) + ascent = dm.Phase(ode_class=CannonballODE, transcription=transcription) + traj.add_phase('ascent', ascent) + + transcription = dm.GaussLobatto(num_segments=5, order=3, compressed=True) + descent = dm.Phase(ode_class=CannonballODE, transcription=transcription) + traj.add_phase('descent', descent) + + for phase in (ascent, descent): + is_ascent = phase.name == "ascent" + phase.set_time_options(fix_initial=True if is_ascent else False, + duration_bounds=(1, 100), duration_ref=100, units='s') + phase.set_state_options('r', fix_initial=is_ascent, fix_final=False) + phase.set_state_options('h', fix_initial=is_ascent, fix_final=not is_ascent) + phase.set_state_options('gam', fix_initial=False, fix_final=is_ascent) + phase.set_state_options('v', fix_initial=False, fix_final=False) + phase.add_parameter('S', units='m**2', static_target=True, val=0.005) + phase.add_parameter('m', units='kg', static_target=True, val=1.0) + phase.add_parameter('price', units='USD', static_target=True, val=10) + phase.add_parameter('CD', units=None, static_target=True, val=0.5) + + descent.add_objective('r', loc='final', scaler=-1.0) # negative means to maximize + for param in ('CD', 'm', 'S', 'price'): + traj.add_parameter(param, static_target=True) + + # Link Phases (link time and all state variables) + traj.link_phases(phases=['ascent', 'descent'], vars=['*']) + # have to set muzzle energy here before setup for sim to run properly + ascent.add_boundary_constraint('ke', loc='initial', + upper=ke_max, lower=0, ref=100000) + return traj, ascent, descent + + +p = om.Problem(model=om.Group()) + +p.driver = om.ScipyOptimizeDriver() +p.driver.options['optimizer'] = 'SLSQP' +p.driver.declare_coloring() + +p.model.add_subsystem('size_comp', CannonballSizing(), + promotes_inputs=['radius', 'dens']) +p.model.set_input_defaults('dens', val=7.87, units='g/cm**3') +p.model.add_design_var('radius', lower=0.01, upper=0.10, + ref0=0.01, ref=0.10, units='m') + +kes = [4e5, 5e5] +trajs, ascents, descents = [], [], [] +for ke in kes: + a, b, c = createTrajectory(ke) + trajs.append(a) + ascents.append(b) + descents.append(c) +# traj, ascent, descent = createTrajectory(4e5) +p.model.add_subsystem('traj', trajs[1]) +ascent = ascents[1] +descent = descents[1] + +# Issue Connections +p.model.connect('size_comp.mass', 'traj.parameters:m') +p.model.connect('size_comp.price', 'traj.parameters:price') +p.model.connect('size_comp.S', 'traj.parameters:S') + +# A linear solver at the top level can improve performance. +p.model.linear_solver = om.DirectSolver() +p.setup() + +p.set_val('radius', 0.05, units='m') +p.set_val('dens', 7.87, units='g/cm**3') + +p.set_val('traj.parameters:CD', 0.5) + +p.set_val('traj.ascent.t_initial', 0.0) +p.set_val('traj.ascent.t_duration', 10.0) +# list is initial and final, based on phase info some are fixed others are not +p.set_val('traj.ascent.states:r', ascent.interp('r', [0, 100])) +p.set_val('traj.ascent.states:h', ascent.interp('h', [0, 100])) +p.set_val('traj.ascent.states:v', ascent.interp('v', [200, 150])) +p.set_val('traj.ascent.states:gam', ascent.interp('gam', [25, 0]), units='deg') + +p.set_val('traj.descent.t_initial', 10.0) +p.set_val('traj.descent.t_duration', 10.0) + +p.set_val('traj.descent.states:r', descent.interp('r', [100, 200])) +p.set_val('traj.descent.states:h', descent.interp('h', [100, 0])) +p.set_val('traj.descent.states:v', descent.interp('v', [150, 200])) +p.set_val('traj.descent.states:gam', descent.interp('gam', [0, -45]), units='deg') + + +dm.run_problem(p, simulate=True) +sol = om.CaseReader('dymos_solution.db').get_case('final') +sim = om.CaseReader('dymos_simulation.db').get_case('final') + + +def plotstuff(): + rad = p.get_val('radius', units='m')[0] + print(f'optimal radius: {rad} m ') + mass = p.get_val('size_comp.mass', units='kg')[0] + print(f'cannonball mass: {mass} kg ') + price = p.get_val('size_comp.price', units='USD')[0] + print(f'cannonball price: ${price:.2f}') + area = p.get_val('size_comp.S', units='cm**2')[0] + print(f'cannonball aerodynamic reference area: {area} cm**2 ') + angle = p.get_val('traj.ascent.timeseries.gam', units='deg')[0, 0] + print(f'launch angle: {angle} deg') + max_range = p.get_val('traj.descent.timeseries.r')[-1, 0] + print(f'maximum range: {max_range} m') + + fig, axes = plt.subplots(nrows=1, ncols=1, figsize=(10, 6)) + time_imp = {'ascent': p.get_val('traj.ascent.timeseries.time'), + 'descent': p.get_val('traj.descent.timeseries.time')} + time_exp = {'ascent': sim.get_val('traj.ascent.timeseries.time'), + 'descent': sim.get_val('traj.descent.timeseries.time')} + r_imp = {'ascent': p.get_val('traj.ascent.timeseries.r'), + 'descent': p.get_val('traj.descent.timeseries.r')} + r_exp = {'ascent': sim.get_val('traj.ascent.timeseries.r'), + 'descent': sim.get_val('traj.descent.timeseries.r')} + h_imp = {'ascent': p.get_val('traj.ascent.timeseries.h'), + 'descent': p.get_val('traj.descent.timeseries.h')} + h_exp = {'ascent': sim.get_val('traj.ascent.timeseries.h'), + 'descent': sim.get_val('traj.descent.timeseries.h')} + + axes.plot(r_imp['ascent'], h_imp['ascent'], 'bo') + axes.plot(r_imp['descent'], h_imp['descent'], 'ro') + axes.plot(r_exp['ascent'], h_exp['ascent'], 'b--') + axes.plot(r_exp['descent'], h_exp['descent'], 'r--') + + axes.set_xlabel('range (m)') + axes.set_ylabel('altitude (m)') + axes.grid(True) + + fig, axes = plt.subplots(nrows=4, ncols=1, figsize=(10, 6)) + states = ['r', 'h', 'v', 'gam'] + for i, state in enumerate(states): + x_imp = {'ascent': sol.get_val(f'traj.ascent.timeseries.{state}'), + 'descent': sol.get_val(f'traj.descent.timeseries.{state}')} + + x_exp = {'ascent': sim.get_val(f'traj.ascent.timeseries.{state}'), + 'descent': sim.get_val(f'traj.descent.timeseries.{state}')} + + axes[i].set_ylabel(state) + axes[i].grid(True) + + axes[i].plot(time_imp['ascent'], x_imp['ascent'], 'bo') + axes[i].plot(time_imp['descent'], x_imp['descent'], 'ro') + axes[i].plot(time_exp['ascent'], x_exp['ascent'], 'b--') + axes[i].plot(time_exp['descent'], x_exp['descent'], 'r--') + + plt.show() + + +plotstuff() From e1c77215932e5d917b35cab3d3c0d90a38b9889d Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Tue, 23 Jul 2024 22:06:14 -0400 Subject: [PATCH 002/113] pseudocode for multi mission aviary example --- multimission.py | 64 +++++++++++++++++++++++++++++++++++++++++++++++++ 1 file changed, 64 insertions(+) create mode 100644 multimission.py diff --git a/multimission.py b/multimission.py new file mode 100644 index 000000000..b7c430bc8 --- /dev/null +++ b/multimission.py @@ -0,0 +1,64 @@ +""" +Goal: use single aircraft description but optimize it for multiple missions simultaneously, +i.e. all missions are on the range-payload line instead of having excess performance +Aircraft csv: defines plane, but also defines payload (passengers, cargo) which can vary with mission + These will have to be specified in some alternate way such as a list correspond to mission # +Phase info: defines a particular mission, will have multiple phase infos +""" +import aviary.api as av +from aviary.examples.example_phase_info import phase_info +from copy import deepcopy +import openmdao.api as om + +# TODO: modify one of these to represent a different mission (e.g. change cruise length) +phase_info1 = phase_info +phase_info2 = phase_info + +if __name__ == '__main__': + super_prob = om.Problem.model() + prob1 = av.AviaryProblem() + prob2 = av.AviaryProblem() + + # Load aircraft and options data from user + # Allow for user overrides here + prob1.load_inputs('models/test_aircraft/aircraft_for_bench_FwFm.csv', phase_info1) + prob2.load_inputs('models/test_aircraft/aircraft_for_bench_FwFm.csv', phase_info1) + + # Preprocess inputs + prob1.check_and_preprocess_inputs() + prob2.check_and_preprocess_inputs() + + prob1.add_pre_mission_systems() + prob2.add_pre_mission_systems() + + prob1.add_phases() + prob2.add_phases() + + prob1.add_post_mission_systems() + prob2.add_post_mission_systems() + + # Link phases and variables + prob1.link_phases() + prob2.link_phases() + + super_prob.add_driver("SLSQP", max_iter=100) + + super_prob.add_parameter('mission.design.gross_mass') + + # use submodelcomp to instantiate both problems inside of the super problem + # https://openmdao.org/newdocs/versions/latest/features/building_blocks/components/submodel_comp.html?highlight=subproblem + # promote the correct inputs and outputs from the submodels + # add and execComp that sums the fuel burn output + + # Load optimization problem formulation + # Detail which variables the optimizer can control + super_prob.add_objective() # output from execcomp goes here) + + super_prob.setup() + + prob1.set_initial_guesses() + prob2.set_initial_guesses() + + # remove all plots and extras + super_prob.run_aviary_problem(record_filename='reserve_mission_fixedrange.db') + super_prob.get_val() # look at final fuel burn From a2b70c09f0b37dfee46bdcf349e9db7020b0bc82 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 24 Jul 2024 09:36:44 -0400 Subject: [PATCH 003/113] checkpoint --- cannonball.py | 17 ++++++++++------- multimission.py | 35 ++++++++++++++++++++++++++++++++--- 2 files changed, 42 insertions(+), 10 deletions(-) diff --git a/cannonball.py b/cannonball.py index ba9bb8088..9f1d81303 100644 --- a/cannonball.py +++ b/cannonball.py @@ -160,8 +160,11 @@ def createTrajectory(ke_max): p.driver.options['optimizer'] = 'SLSQP' p.driver.declare_coloring() -kes = [4e5, 5e5] -weights = [2, 1.01] +kes = [4e5, 5e5, 6e5] +# 2:1 ratio (or 1:2) causes results that essentially don't optimize the 1 mission, +# 1.01 works, 1.009 doesn't +# 2:1:1 works?! - may be related some normalization/bounds issue +weights = [2.1, 1.5, 1.1] num_trajs = len(kes) p.model.add_subsystem(f"sizing_comp", CannonballSizing(), @@ -232,21 +235,21 @@ def plotstuff(): print("\n\n=================================================") print( f"Optimized {num_trajs} trajectories with weights: {', '.join(map(str,weights))}") - rad = p.get_val('radius', units='m')[0] + rad = p.get_val('radius', units='cm')[0] mass = p.get_val('sizing_comp.mass', units='kg')[0] price = p.get_val('sizing_comp.price', units='USD')[0] area = p.get_val('sizing_comp.S', units='cm**2')[0] - print("Optimal Cannonball Description:") + print("\nOptimal Cannonball Description:") print( - f"Radius: {rad:.2f} m, Mass: {mass:.2f} kg, Price: ${price:.2f}, Area: {area} sqcm") + f"\tRadius: {rad:.2f} cm, Mass: {mass:.2f} kg, Price: ${price:.2f}, Area: {area:.2f} sqcm") - print("Optimal Trajectory Descriptions:") + print("\nOptimal Trajectory Descriptions:") for i, ke in enumerate(kes): angle = p.get_val(f'traj_{i}.ascent.timeseries.gam', units='deg')[0, 0] max_range = p.get_val(f'traj_{i}.descent.timeseries.r')[-1, 0] print( - f"KE: {ke/1e3:.2f} KJ, Launch Angle: {angle:.2f} deg, Max Range: {max_range:.2f} m") + f"\tKE: {ke/1e3:.2f} KJ, Launch Angle: {angle:.2f} deg, Max Range: {max_range:.2f} m") # fig, axes = plt.subplots(nrows=1, ncols=1, figsize=(10, 6)) # time_imp = {'ascent': p.get_val('traj_0.ascent.timeseries.time'), diff --git a/multimission.py b/multimission.py index b7c430bc8..4100c553e 100644 --- a/multimission.py +++ b/multimission.py @@ -11,8 +11,8 @@ import openmdao.api as om # TODO: modify one of these to represent a different mission (e.g. change cruise length) -phase_info1 = phase_info -phase_info2 = phase_info +phase_info1 = deepcopy(phase_info) +phase_info2 = deepcopy(phase_info) if __name__ == '__main__': super_prob = om.Problem.model() @@ -21,8 +21,9 @@ # Load aircraft and options data from user # Allow for user overrides here + # TODO: modify one of these to represent a different payload case prob1.load_inputs('models/test_aircraft/aircraft_for_bench_FwFm.csv', phase_info1) - prob2.load_inputs('models/test_aircraft/aircraft_for_bench_FwFm.csv', phase_info1) + prob2.load_inputs('models/test_aircraft/aircraft_for_bench_FwFm.csv', phase_info2) # Preprocess inputs prob1.check_and_preprocess_inputs() @@ -62,3 +63,31 @@ # remove all plots and extras super_prob.run_aviary_problem(record_filename='reserve_mission_fixedrange.db') super_prob.get_val() # look at final fuel burn + + +""" +Example phase info mission: +Times (min): 0, 128, 241, 299 + Alt (ft): 0, 32000, 34000, 500 + Mach: 0.2, 0.72, 0.72, 0.36 + + +Hard to find multiple payload/range values for FwFm (737), so use C-5 instead +Based on: + https://en.wikipedia.org/wiki/Lockheed_C-5_Galaxy#Specifications_(C-5M), + https://www.af.mil/About-Us/Fact-Sheets/Display/Article/1529718/c-5-abc-galaxy-and-c-5m-super-galaxy/ + +MTOW: 840,000 lb +Max Payload: 281,000 lb +Max Fuel: 341,446 lb +Empty Weight: 380,000 lb -> leaves 460,000 lb for fuel+payload (max fuel + max payload = 622,446 lb) + +Payload/range: + 281,000 lb payload -> 2,150 nmi range (AF.mil) [max payload case] + 120,000 lb payload -> 4,800 nmi range (AF.mil) [intermediate case] + 0 lb payload -> 7,000 nmi range (AF.mil) [ferry case] + +Flight characteristics: + Cruise at M0.77 at 33k ft + Max rate of climb: 2100 ft/min +""" From 079313b24fc476e184c073a97508675448962502 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 24 Jul 2024 09:51:51 -0400 Subject: [PATCH 004/113] checkpt --- c5.csv | 166 ++++++++++++++++++++++++++++++++++++++++ c5_ferry_phase_info.py | 83 ++++++++++++++++++++ multimission.py | 8 +- outputted_phase_info.py | 83 ++++++++++++++++++++ singlemission.py | 37 +++++++++ 5 files changed, 373 insertions(+), 4 deletions(-) create mode 100644 c5.csv create mode 100644 c5_ferry_phase_info.py create mode 100644 outputted_phase_info.py create mode 100644 singlemission.py diff --git a/c5.csv b/c5.csv new file mode 100644 index 000000000..42aa03315 --- /dev/null +++ b/c5.csv @@ -0,0 +1,166 @@ +# author: Chris Psenica +#aircraft:air_conditioning:mass_scaler,1.0,unitless +#aircraft:anti_icing:mass_scaler,1.0,unitless +#aircraft:apu:mass_scaler,1.0,unitless +#aircraft:avionics:mass_scaler,1.0,unitless +#aircraft:canard:area,0.0,ft**2 +#aircraft:canard:aspect_ratio,0.0,unitless +#aircraft:canard:thickness_to_chord,0.0,unitless +aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm +#aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless +#aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:mass_per_passenger,180.0,lbm +aircraft:crew_and_payload:cargo_mass,281000,lbm +#misc_cargo +#aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:num_flight_crew,7,unitless +aircraft:crew_and_payload:num_passengers,82,unitless +#aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless +aircraft:crew_and_payload:wing_cargo,0.0,lbm +aircraft:design:base_area,0.0,ft**2 +#aircraft:design:empty_mass_margin_scaler,1.0,unitless +aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless +#aircraft:design:touchdown_mass,498554,lbm +aircraft:design:reserve_fuel_additional,0,lbm +aircraft:design:subsonic_drag_coeff_factor,1.0,unitless +aircraft:design:supersonic_drag_coeff_factor,1.0,unitless +aircraft:design:use_alt_mass,False,unitless +aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless +#aircraft:electrical:mass_scaler,1.0,unitless + +aircraft:engine:data_file,models/engines/CF6.deck,unitless + +aircraft:engine:additional_mass_fraction,0.,unitless +aircraft:engine:constant_fuel_consumption,0.,lbm/h + +aircraft:engine:flight_idle_thrust_fraction,0.0,unitless +aircraft:engine:flight_idle_max_fraction,1.0,unitless +aircraft:engine:flight_idle_min_fraction,0.08,unitless +#aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless +#aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless +aircraft:engine:generate_flight_idle,False,unitless +aircraft:engine:geopotential_alt,False,unitless +aircraft:engine:ignore_negative_thrust,False,unitless +aircraft:engine:interpolation_method,slinear,unitless +aircraft:engine:mass_scaler,1.0,unitless +aircraft:engine:mass,8176,lbm +aircraft:engine:reference_mass,8176,lbm +aircraft:engine:reference_sls_thrust,51250.,lbf +aircraft:engine:scale_mass,True,unitless +aircraft:engine:scale_performance,True,unitless +aircraft:engine:scaled_sls_thrust,51250,lbf +#aircraft:engine:subsonic_fuel_flow_scaler,1.0,unitless +#aircraft:engine:supersonic_fuel_flow_scaler,1.0,unitless +#aircraft:engine:thrust_reversers_mass_scaler,1.0,unitless +aircraft:engine:num_fuselage_engines,0,unitless +aircraft:engine:num_engines,4,unitless +aircraft:engine:num_wing_engines,4,unitless +aircraft:engine:wing_locations,[0.3561541339,0.555929667],unitless +#aircraft:fins:area,0.0,ft**2 +#aircraft:fins:mass_scaler,1.0,unitless +#aircraft:fins:mass,0.0,lbm +#aircraft:fins:num_fins,0,unitless +#aircraft:fins:taper_ratio,10.0,unitless +aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm +#aircraft:fuel:density_ratio,1.0,unitless +#aircraft:fuel:fuel_system_mass_scaler,1.0,unitless +aircraft:fuel:fuselage_fuel_capacity,0.0,lbm +aircraft:fuel:num_tanks,12,unitless +aircraft:fuel:total_capacity,341446,lbm +#aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless +#aircraft:furnishings:mass_scaler,1.0,unitless +aircraft:fuselage:length,230.58,ft +#aircraft:fuselage:mass_scaler,1.0,unitless +aircraft:fuselage:max_height,26.83,ft +aircraft:fuselage:max_width,23.9,ft +aircraft:fuselage:military_cargo_floor,True,unitless +aircraft:fuselage:num_fuselages,1,unitless +aircraft:fuselage:passenger_compartment_length,143.75,ft +aircraft:fuselage:planform_area,4462.78,ft**2 +#aircraft:fuselage:wetted_area_scaler,1.0,unitless +aircraft:horizontal_tail:area,965.8,ft**2 +aircraft:horizontal_tail:aspect_ratio,4.2,unitless +#aircraft:horizontal_tail:mass_scaler,1.0,unitless +aircraft:horizontal_tail:taper_ratio,0.43,unitless +aircraft:horizontal_tail:thickness_to_chord,0.16,unitless +aircraft:horizontal_tail:vertical_tail_fraction,1.0,unitless +#aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless +#aircraft:hydraulics:mass_scaler,1.0,unitless +#aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 +#aircraft:instruments:mass_scaler,1.0,unitless +#aircraft:landing_gear:carrier_based,False,unitless +#aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless +#aircraft:landing_gear:main_gear_oleo_length,45,inch +#aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless +#aircraft:landing_gear:nose_gear_oleo_length,45,inch +aircraft:nacelle:avg_diameter,9.15,ft +aircraft:nacelle:avg_length,20.56,ft +#aircraft:nacelle:mass_scaler,1.0,unitless +#aircraft:nacelle:wetted_area_scaler,1.0,unitless +#aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 +#aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless +#aircraft:propulsion:misc_mass_scaler,1.0,unitless +aircraft:vertical_tail:area,537.9,ft**2 +aircraft:vertical_tail:aspect_ratio,0.958,unitless +#aircraft:vertical_tail:mass_scaler,1.0,unitless +aircraft:vertical_tail:num_tails,1,unitless +aircraft:vertical_tail:taper_ratio,0.846,unitless +aircraft:vertical_tail:thickness_to_chord,0.157,unitless +#aircraft:vertical_tail:wetted_area_scaler,1.0,unitless +aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless +aircraft:wing:airfoil_technology,1.0,unitless +aircraft:wing:area,6200,ft**2 +aircraft:wing:aspect_ratio,7.75,unitless +#aircraft:wing:bending_mass_scaler,1.0,unitless +#aircraft:wing:composite_fraction,0.1,unitless +aircraft:wing:control_surface_area,2323.7,ft**2 +aircraft:wing:control_surface_area_ratio,0.37479,unitless +aircraft:wing:load_distribution_control,2.0,unitless +aircraft:wing:load_fraction,1.0,unitless +#aircraft:wing:mass_scaler,1.0,unitless +aircraft:wing:max_camber_at_70_semispan,0.0,unitless +#aircraft:wing:misc_mass_scaler,1.0,unitless +#aircraft:wing:shear_control_mass_scaler,1.0,unitless +aircraft:wing:span_efficiency_reduction,False,unitless +aircraft:wing:span,222.75,ft +#aircraft:wing:strut_bracing_factor,0.0,unitless +#aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless +aircraft:wing:sweep,20.0,deg +aircraft:wing:taper_ratio,0.419,unitless +aircraft:wing:thickness_to_chord,0.1284,unitless +aircraft:wing:ultimate_load_factor,3.75,unitless +aircraft:wing:var_sweep_mass_penalty,0.0,unitless +#aircraft:wing:wetted_area_scaler,1.0,unitless +aircraft:wing:num_integration_stations,50,unitless +aircraft:wing:thickness_to_chord_dist,0.1239,0.108,0.013,unitless +aircraft:wing:load_path_sweep_dist,0.0,0.0,deg +aircraft:wing:input_station_dist,0.0,0.3298,0.884,unitless +aircraft:wing:chord_per_semispan,0.362,0.2667,0.0456,unitless +aircraft:wing:glove_and_bat,0.0,ft**2 +aircraft:wing:detailed_wing,False,unitless + + +mission:constraints:max_mach,0.77,unitless +mission:design:cruise_altitude,34000,ft +mission:design:gross_mass,840000,lbm +mission:design:range,2300,NM +mission:design:thrust_takeoff_per_eng,51250,lbf +mission:landing:lift_coefficient_max,3.0,unitless +mission:summary:cruise_mach,0.77,unitless +#mission:summary:fuel_flow_scaler,1.0,unitless +mission:takeoff:fuel_simple,6.32,lbm +mission:takeoff:lift_coefficient_max,3.62,unitless +mission:takeoff:lift_over_drag,19.5,unitless +settings:equations_of_motion,height_energy +settings:mass_method,FLOPS + + +### missions definition +# mission_name: payload +# times: 0, 50, 280, 300 +# altitudes: 0, 30000, 30000, 0 +# machs: 0.30, 0.77, 0.77, 0.30 +# optimize_altitudes: F,F,F +# optimize_machs: F,F,F +# takeoff: F +# landing: F diff --git a/c5_ferry_phase_info.py b/c5_ferry_phase_info.py new file mode 100644 index 000000000..3e84cf09c --- /dev/null +++ b/c5_ferry_phase_info.py @@ -0,0 +1,83 @@ +phase_info = { + "pre_mission": {"include_takeoff": False, "optimize_mass": True}, + "climb_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.3, "unitless"), + "final_mach": (0.77, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (0.0, "ft"), + "final_altitude": (32000.0, "ft"), + "altitude_bounds": ((0.0, 32500.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": True, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((0.0, 0.0), "min"), + "duration_bounds": ((15.0, 45.0), "min"), + }, + "initial_guesses": {"time": ([0.0, 30.0], "min")}, + }, + "cruise_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.77, "unitless"), + "final_mach": (0.77, "unitless"), + "mach_bounds": ((0.75, 0.79), "unitless"), + "initial_altitude": (32000.0, "ft"), + "final_altitude": (32000.0, "ft"), + "altitude_bounds": ((31500.0, 32500.0), "ft"), + "throttle_enforcement": "boundary_constraint", + "fix_initial": False, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((15.0, 45.0), "min"), + "duration_bounds": ((390.0, 1170.0), "min"), + }, + "initial_guesses": {"time": ([30.0, 780.0], "min")}, + }, + "descent_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.77, "unitless"), + "final_mach": (0.3, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (32000.0, "ft"), + "final_altitude": (0.0, "ft"), + "altitude_bounds": ((0.0, 32500.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": False, + "constrain_final": True, + "fix_duration": False, + "initial_bounds": ((405.0, 1215.0), "min"), + "duration_bounds": ((12.5, 37.5), "min"), + }, + "initial_guesses": {"time": ([810.0, 25.0], "min")}, + }, + "post_mission": { + "include_landing": False, + "constrain_range": True, + "target_range": (7001.03, "nmi"), + }, +} diff --git a/multimission.py b/multimission.py index 4100c553e..b64870317 100644 --- a/multimission.py +++ b/multimission.py @@ -66,10 +66,10 @@ """ -Example phase info mission: -Times (min): 0, 128, 241, 299 - Alt (ft): 0, 32000, 34000, 500 - Mach: 0.2, 0.72, 0.72, 0.36 +Ferry mission phase info: +Times (min): 0, 30, 810, 835 + Alt (ft): 0, 32000, 32000, 0 + Mach: 0.3, 0.77, 0.77, 0.3 Hard to find multiple payload/range values for FwFm (737), so use C-5 instead diff --git a/outputted_phase_info.py b/outputted_phase_info.py new file mode 100644 index 000000000..3e84cf09c --- /dev/null +++ b/outputted_phase_info.py @@ -0,0 +1,83 @@ +phase_info = { + "pre_mission": {"include_takeoff": False, "optimize_mass": True}, + "climb_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.3, "unitless"), + "final_mach": (0.77, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (0.0, "ft"), + "final_altitude": (32000.0, "ft"), + "altitude_bounds": ((0.0, 32500.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": True, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((0.0, 0.0), "min"), + "duration_bounds": ((15.0, 45.0), "min"), + }, + "initial_guesses": {"time": ([0.0, 30.0], "min")}, + }, + "cruise_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.77, "unitless"), + "final_mach": (0.77, "unitless"), + "mach_bounds": ((0.75, 0.79), "unitless"), + "initial_altitude": (32000.0, "ft"), + "final_altitude": (32000.0, "ft"), + "altitude_bounds": ((31500.0, 32500.0), "ft"), + "throttle_enforcement": "boundary_constraint", + "fix_initial": False, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((15.0, 45.0), "min"), + "duration_bounds": ((390.0, 1170.0), "min"), + }, + "initial_guesses": {"time": ([30.0, 780.0], "min")}, + }, + "descent_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.77, "unitless"), + "final_mach": (0.3, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (32000.0, "ft"), + "final_altitude": (0.0, "ft"), + "altitude_bounds": ((0.0, 32500.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": False, + "constrain_final": True, + "fix_duration": False, + "initial_bounds": ((405.0, 1215.0), "min"), + "duration_bounds": ((12.5, 37.5), "min"), + }, + "initial_guesses": {"time": ([810.0, 25.0], "min")}, + }, + "post_mission": { + "include_landing": False, + "constrain_range": True, + "target_range": (7001.03, "nmi"), + }, +} diff --git a/singlemission.py b/singlemission.py new file mode 100644 index 000000000..f10979840 --- /dev/null +++ b/singlemission.py @@ -0,0 +1,37 @@ +import aviary.api as av +from c5_ferry_phase_info import phase_info + +if __name__ == '__main__': + prob = av.AviaryProblem() + + # Load aircraft and options data from user + # Allow for user overrides here + prob.load_inputs('c5.csv', phase_info) + + # Preprocess inputs + prob.check_and_preprocess_inputs() + + prob.add_pre_mission_systems() + + prob.add_phases() + + prob.add_post_mission_systems() + + # Link phases and variables + prob.link_phases() + + prob.add_driver("SLSQP", max_iter=50) + + prob.add_design_variables() + + # Load optimization problem formulation + # Detail which variables the optimizer can control + prob.add_objective() # output from execcomp goes here) + + prob.setup() + + prob.set_initial_guesses() + + # remove all plots and extras + prob.run_aviary_problem(record_filename='c5_ferry.db') + # prob.get_val() # look at final fuel burn From 232e98a73dca16692fa34ef90e72334be92db3c6 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 24 Jul 2024 10:06:57 -0400 Subject: [PATCH 005/113] checkpt --- aviary/interface/methods_for_level2.py | 4 +- aviary/models/engines/CF6.deck | 623 +++++++++++++++++++++++++ c5.csv | 20 +- c5_ferry_phase_info.py | 30 +- singlemission.py | 27 ++ 5 files changed, 678 insertions(+), 26 deletions(-) create mode 100644 aviary/models/engines/CF6.deck diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index 076fda82d..b251abab1 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -1719,14 +1719,14 @@ def add_design_variables(self): self.model.add_design_var( Mission.Design.GROSS_MASS, lower=10.0, - upper=400e3, + upper=900e3, units='lbm', ref=175e3, ) self.model.add_design_var( Mission.Summary.GROSS_MASS, lower=10.0, - upper=400e3, + upper=900e3, units='lbm', ref=175e3, ) diff --git a/aviary/models/engines/CF6.deck b/aviary/models/engines/CF6.deck new file mode 100644 index 000000000..2d4b0f42a --- /dev/null +++ b/aviary/models/engines/CF6.deck @@ -0,0 +1,623 @@ +Mach_Number (unitless), Altitude (ft), Throttle (unitless), Gross_Thrust (lbf), Ram_Drag (lbf), Fuel_Flow (lb/h), NOx_Rate (lb/h) +0, 0, 50, 51463, 0, 22544.2, 0.438066 +0, 0, 47, 46316.7, 0, 19554.2, 0.422184 +0, 0, 44, 41168.9, 0, 16706.8, 0.405811 +0, 0, 41, 36024.5, 0, 13993.4, 0.388441 +0, 0, 38, 30878.2, 0, 11478.9, 0.371747 +0, 0, 35, 25731.7, 0, 9223.64, 0.358454 +0, 0, 32, 20585, 0, 7189.32, 0.34925 +0, 0, 29, 15438.9, 0, 5352.09, 0.346662 +0, 0, 26, 10292.6, 0, 3719.21, 0.361348 +0.1, 0, 50, 54023, 5123.45, 23900.4, 0.488765 +0.1, 0, 47, 48904.4, 4894.93, 20792.4, 0.472452 +0.1, 0, 44, 43772.3, 4652.35, 17907.1, 0.457748 +0.1, 0, 41, 38628.8, 4399.32, 15117.4, 0.441647 +0.1, 0, 38, 33471.3, 4130.98, 12495.1, 0.425866 +0.1, 0, 35, 28290.4, 3840.72, 10110.9, 0.413537 +0.1, 0, 32, 23067.1, 3507.29, 7960.7, 0.406992 +0.1, 0, 29, 17780.3, 3110.29, 5995.71, 0.408705 +0.1, 0, 26, 12400.2, 2620.36, 4197.43, 0.429192 +0.2, 0, 50, 57647.3, 10603.3, 25425.5, 0.540462 +0.2, 0, 47, 52504, 10164.3, 22162.3, 0.523439 +0.2, 0, 44, 47327.3, 9692.14, 19180.2, 0.509636 +0.2, 0, 41, 42129, 9198.28, 16310.9, 0.495309 +0.2, 0, 38, 36905.1, 8679.85, 13562.1, 0.480496 +0.2, 0, 35, 31649.4, 8127.32, 10997.6, 0.467541 +0.2, 0, 32, 26321.7, 7503.92, 8696.87, 0.462162 +0.2, 0, 29, 20873.9, 6760.73, 6578.5, 0.466124 +0.2, 0, 26, 15253.2, 5844.67, 4620.23, 0.491067 +0.25, 0, 50, 59887.9, 13531.2, 26264, 0.566562 +0.25, 0, 47, 54709.5, 12988.4, 22946.7, 0.550002 +0.25, 0, 44, 49496.2, 12410.9, 19864.2, 0.535636 +0.25, 0, 41, 44250, 11801.1, 16940.8, 0.522076 +0.25, 0, 38, 38975.5, 11161.9, 14130.5, 0.508044 +0.25, 0, 35, 33661.3, 10482.8, 11491.3, 0.495772 +0.25, 0, 32, 28276.6, 9734.59, 9078.89, 0.48964 +0.25, 0, 29, 22745.7, 8838.64, 6880.2, 0.494728 +0.25, 0, 26, 17001.5, 7730.26, 4863.81, 0.524611 +0.3, 0, 50, 61345.2, 16480.9, 26442.8, 0.589397 +0.3, 0, 47, 56222.3, 15844.4, 23161.1, 0.573608 +0.3, 0, 44, 51062.6, 15171.4, 20084, 0.55958 +0.3, 0, 41, 45863.4, 14458.8, 17172.1, 0.546804 +0.3, 0, 38, 40630.7, 13712.8, 14371.1, 0.533887 +0.3, 0, 35, 35354.9, 12921.9, 11733, 0.523024 +0.3, 0, 32, 30003.3, 12058.2, 9305.99, 0.518583 +0.3, 0, 29, 24490.1, 11030.8, 7081.42, 0.526135 +0.3, 0, 26, 18737.7, 9764.8, 5027.29, 0.560277 +0.4, 0, 50, 65109.9, 22791, 26900.6, 0.635663 +0.4, 0, 47, 60065.1, 21978.5, 23682.1, 0.621795 +0.4, 0, 44, 54979.7, 21124.2, 20632.6, 0.609431 +0.4, 0, 41, 49860.8, 20237.6, 17672.8, 0.596586 +0.4, 0, 38, 44688.5, 19298.1, 14871.6, 0.585718 +0.4, 0, 35, 39465.8, 18305.4, 12227, 0.577823 +0.4, 0, 32, 34166.3, 17239.4, 9767.5, 0.57704 +0.4, 0, 29, 28693.9, 15998.2, 7482.36, 0.589363 +0.4, 0, 26, 22941.7, 14477.9, 5359.4, 0.633215 +0.5, 0, 50, 70055, 29779.2, 27487, 0.68247 +0.5, 0, 47, 65050.3, 28802.7, 24313.7, 0.670767 +0.5, 0, 44, 60006.3, 27785.4, 21267.7, 0.660061 +0.5, 0, 41, 54933.8, 26740.6, 18278.4, 0.648327 +0.5, 0, 38, 49804.8, 25639.6, 15438, 0.638853 +0.5, 0, 35, 44613.5, 24475.6, 12761.1, 0.633688 +0.5, 0, 32, 39346.5, 23236.6, 10261.2, 0.636952 +0.5, 0, 29, 33908.7, 21826, 7940.59, 0.657184 +0.5, 0, 26, 28159.8, 20104.6, 5792.28, 0.719078 +0, 2000, 50, 49123, 0, 21568.5, 0.439072 +0, 2000, 47, 44210.8, 0, 18665, 0.422182 +0, 2000, 44, 39298.6, 0, 15951.1, 0.405896 +0, 2000, 41, 34385.7, 0, 13349.7, 0.388235 +0, 2000, 38, 29474, 0, 10936.3, 0.371051 +0, 2000, 35, 24561.4, 0, 8769.85, 0.357058 +0, 2000, 32, 19649.5, 0, 6824.42, 0.347308 +0, 2000, 29, 14737, 0, 5070.39, 0.34406 +0, 2000, 26, 9824.59, 0, 3510.74, 0.357342 +0.1, 2000, 50, 51538.6, 4821.09, 22855.7, 0.489231 +0.1, 2000, 47, 46652.4, 4606.79, 19839.4, 0.471855 +0.1, 2000, 44, 41751.7, 4377.35, 17079.5, 0.456984 +0.1, 2000, 41, 36839.9, 4137.67, 14421.4, 0.440991 +0.1, 2000, 38, 31915.2, 3884.26, 11907.2, 0.424786 +0.1, 2000, 35, 26969.6, 3610.79, 9613.12, 0.411541 +0.1, 2000, 32, 21985.2, 3298.23, 7554.94, 0.404289 +0.1, 2000, 29, 16940.5, 2925.36, 5678.88, 0.405195 +0.1, 2000, 26, 11808.4, 2464.95, 3961.86, 0.424026 +0.2, 2000, 50, 54856.9, 9965.33, 24261, 0.540436 +0.2, 2000, 47, 49954, 9551.35, 21122.7, 0.522806 +0.2, 2000, 44, 45021.5, 9108.3, 18243.8, 0.507997 +0.2, 2000, 41, 40063.8, 8640.77, 15515.3, 0.493757 +0.2, 2000, 38, 35085.2, 8150.44, 12894.4, 0.478727 +0.2, 2000, 35, 30074.3, 7628.41, 10439.8, 0.46511 +0.2, 2000, 32, 25000.6, 7044.03, 8236.45, 0.458687 +0.2, 2000, 29, 19814, 6346.56, 6218.85, 0.461769 +0.2, 2000, 26, 14463.4, 5485.34, 4356.44, 0.485233 +0.25, 2000, 50, 56889.7, 12706.1, 25024.5, 0.566374 +0.25, 2000, 47, 51961.3, 12195.5, 21825, 0.54884 +0.25, 2000, 44, 47000.7, 11653.7, 18858.8, 0.533533 +0.25, 2000, 41, 42003.8, 11076.7, 16083.3, 0.520042 +0.25, 2000, 38, 36983.1, 10472.6, 13408.8, 0.505793 +0.25, 2000, 35, 31923.6, 9831.26, 10889.6, 0.492914 +0.25, 2000, 32, 26801.1, 9128.33, 8586.63, 0.485867 +0.25, 2000, 29, 21543.1, 8287.86, 6496.23, 0.490086 +0.25, 2000, 26, 16082.8, 7246.19, 4580.78, 0.518386 +0.3, 2000, 50, 58331.4, 15483.3, 25230.6, 0.588838 +0.3, 2000, 47, 53446.2, 14882.7, 22072.7, 0.572374 +0.3, 2000, 44, 48527.8, 14249.2, 19112.4, 0.557561 +0.3, 2000, 41, 43569.4, 13575.4, 16334.7, 0.544599 +0.3, 2000, 38, 38578.2, 12869, 13661.2, 0.531375 +0.3, 2000, 35, 33545.5, 12120.8, 11136.9, 0.519816 +0.3, 2000, 32, 28446.2, 11307.5, 8816.1, 0.514398 +0.3, 2000, 29, 23197.6, 10343, 6696.12, 0.520911 +0.3, 2000, 26, 17721.2, 9151.59, 4740.96, 0.553229 +0.4, 2000, 50, 61981.9, 21423.2, 25729.2, 0.634369 +0.4, 2000, 47, 57158, 20655.1, 22625.3, 0.619823 +0.4, 2000, 44, 52291.4, 19844.4, 19699.7, 0.607135 +0.4, 2000, 41, 47394.8, 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+0.75, 43000, 21, 6007.87, 5632.78, 602.735, 1.60688 +0.8, 43000, 50, 17493, 9796.33, 5319.42, 0.691131 +0.8, 43000, 47, 16432.7, 9505.68, 4711.69, 0.680191 +0.8, 43000, 44, 15355.7, 9198.3, 4143.59, 0.672948 +0.8, 43000, 41, 14272.4, 8884.99, 3594.12, 0.66713 +0.8, 43000, 38, 13188.6, 8570.38, 3056.82, 0.661901 +0.8, 43000, 35, 12092.2, 8243.91, 2547.91, 0.662085 +0.8, 43000, 32, 10983.5, 7904.9, 2070.06, 0.672414 +0.8, 43000, 29, 9855.1, 7546.08, 1618.99, 0.701162 +0.8, 43000, 26, 8699.97, 7160.63, 1193.37, 0.775253 +0.8, 43000, 21, 6751.37, 6366.54, 640.55, 1.66448 +0.85, 43000, 50, 18795.8, 10872.5, 5651.78, 0.713312 +0.85, 43000, 47, 17681.5, 10550.6, 5006.32, 0.702055 +0.85, 43000, 44, 16548.3, 10209.7, 4402.05, 0.69449 +0.85, 43000, 41, 15408.2, 9862.12, 3817.82, 0.688385 +0.85, 43000, 38, 14267.3, 9513.05, 3246.11, 0.682786 +0.85, 43000, 35, 13112.2, 9150.58, 2704.26, 0.682616 +0.85, 43000, 32, 11944.3, 8775.09, 2195.24, 0.692682 +0.85, 43000, 29, 10763.4, 8386.44, 1715.16, 0.721569 +0.85, 43000, 26, 9560.52, 7975.87, 1263.34, 0.797234 +0.85, 43000, 21, 7545.89, 7149.73, 677.138, 1.70923 +0.9, 43000, 50, 20230.2, 12048.8, 6021.6, 0.736009 +0.9, 43000, 47, 19055.7, 11692.4, 5333.92, 0.724392 +0.9, 43000, 44, 17859.8, 11314.8, 4689.04, 0.716427 +0.9, 43000, 41, 16656.1, 10929.4, 4065.39, 0.7099 +0.9, 43000, 38, 15451.5, 10542.4, 3455.17, 0.70383 +0.9, 43000, 35, 14230.9, 10140.3, 2876.26, 0.703126 +0.9, 43000, 32, 12995.8, 9723.33, 2332.1, 0.71265 +0.9, 43000, 29, 11745.8, 9291.37, 1818.79, 0.741025 +0.9, 43000, 26, 10478.6, 8842.36, 1336.74, 0.816939 +0.9, 43000, 21, 8392.24, 7983.17, 712.209, 1.74104 diff --git a/c5.csv b/c5.csv index 42aa03315..1447bf4b0 100644 --- a/c5.csv +++ b/c5.csv @@ -10,22 +10,24 @@ aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm #aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless #aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless aircraft:crew_and_payload:mass_per_passenger,180.0,lbm -aircraft:crew_and_payload:cargo_mass,281000,lbm -#misc_cargo + +#aircraft:crew_and_payload:cargo_mass,281000,lbm +#aircraft:crew_and_payload:num_passengers,82,unitless + + #aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless aircraft:crew_and_payload:num_flight_crew,7,unitless -aircraft:crew_and_payload:num_passengers,82,unitless #aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless -aircraft:crew_and_payload:wing_cargo,0.0,lbm -aircraft:design:base_area,0.0,ft**2 +#aircraft:crew_and_payload:wing_cargo,0.0,lbm +#aircraft:design:base_area,0.0,ft**2 #aircraft:design:empty_mass_margin_scaler,1.0,unitless -aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless +#aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless #aircraft:design:touchdown_mass,498554,lbm aircraft:design:reserve_fuel_additional,0,lbm -aircraft:design:subsonic_drag_coeff_factor,1.0,unitless -aircraft:design:supersonic_drag_coeff_factor,1.0,unitless +#aircraft:design:subsonic_drag_coeff_factor,1.0,unitless +#aircraft:design:supersonic_drag_coeff_factor,1.0,unitless aircraft:design:use_alt_mass,False,unitless -aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless +#aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless #aircraft:electrical:mass_scaler,1.0,unitless aircraft:engine:data_file,models/engines/CF6.deck,unitless diff --git a/c5_ferry_phase_info.py b/c5_ferry_phase_info.py index 3e84cf09c..c2b5ea55c 100644 --- a/c5_ferry_phase_info.py +++ b/c5_ferry_phase_info.py @@ -11,11 +11,11 @@ "order": 3, "solve_for_distance": False, "initial_mach": (0.3, "unitless"), - "final_mach": (0.77, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "final_mach": (0.75, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.77), "unitless"), "initial_altitude": (0.0, "ft"), - "final_altitude": (32000.0, "ft"), - "altitude_bounds": ((0.0, 32500.0), "ft"), + "final_altitude": (28000.0, "ft"), + "altitude_bounds": ((0.0, 28500.0), "ft"), "throttle_enforcement": "path_constraint", "fix_initial": True, "constrain_final": False, @@ -35,12 +35,12 @@ "num_segments": 3, "order": 3, "solve_for_distance": False, - "initial_mach": (0.77, "unitless"), - "final_mach": (0.77, "unitless"), - "mach_bounds": ((0.75, 0.79), "unitless"), - "initial_altitude": (32000.0, "ft"), - "final_altitude": (32000.0, "ft"), - "altitude_bounds": ((31500.0, 32500.0), "ft"), + "initial_mach": (0.75, "unitless"), + "final_mach": (0.75, "unitless"), + "mach_bounds": ((0.73, 0.77), "unitless"), + "initial_altitude": (28000.0, "ft"), + "final_altitude": (28000.0, "ft"), + "altitude_bounds": ((27500.0, 28500.0), "ft"), "throttle_enforcement": "boundary_constraint", "fix_initial": False, "constrain_final": False, @@ -60,12 +60,12 @@ "num_segments": 3, "order": 3, "solve_for_distance": False, - "initial_mach": (0.77, "unitless"), + "initial_mach": (0.75, "unitless"), "final_mach": (0.3, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), - "initial_altitude": (32000.0, "ft"), + "mach_bounds": ((0.27999999999999997, 0.77), "unitless"), + "initial_altitude": (28000.0, "ft"), "final_altitude": (0.0, "ft"), - "altitude_bounds": ((0.0, 32500.0), "ft"), + "altitude_bounds": ((0.0, 28500.0), "ft"), "throttle_enforcement": "path_constraint", "fix_initial": False, "constrain_final": True, @@ -78,6 +78,6 @@ "post_mission": { "include_landing": False, "constrain_range": True, - "target_range": (7001.03, "nmi"), + "target_range": (6821.57, "nmi"), }, } diff --git a/singlemission.py b/singlemission.py index f10979840..e17b0397a 100644 --- a/singlemission.py +++ b/singlemission.py @@ -35,3 +35,30 @@ # remove all plots and extras prob.run_aviary_problem(record_filename='c5_ferry.db') # prob.get_val() # look at final fuel burn + +""" +Ferry mission phase info: +Times (min): 0, 30, 810, 835 + Alt (ft): 0, 32000, 32000, 0 + Mach: 0.3, 0.77, 0.77, 0.3 +Notes: 32k in 30 mins too fast for aviary, + +Hard to find multiple payload/range values for FwFm (737), so use C-5 instead +Based on: + https://en.wikipedia.org/wiki/Lockheed_C-5_Galaxy#Specifications_(C-5M), + https://www.af.mil/About-Us/Fact-Sheets/Display/Article/1529718/c-5-abc-galaxy-and-c-5m-super-galaxy/ + +MTOW: 840,000 lb +Max Payload: 281,000 lb +Max Fuel: 341,446 lb +Empty Weight: 380,000 lb -> leaves 460,000 lb for fuel+payload (max fuel + max payload = 622,446 lb) + +Payload/range: + 281,000 lb payload -> 2,150 nmi range (AF.mil) [max payload case] + 120,000 lb payload -> 4,800 nmi range (AF.mil) [intermediate case] + 0 lb payload -> 7,000 nmi range (AF.mil) [ferry case] + +Flight characteristics: + Cruise at M0.77 at 33k ft + Max rate of climb: 2100 ft/min +""" From 4c96f15a69e840daf08f53bb473ccffb6d663439 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 24 Jul 2024 10:24:23 -0400 Subject: [PATCH 006/113] checkpt --- c5.csv | 4 ++-- c5_ferry_phase_info.py | 18 +++++++++--------- outputted_phase_info.py | 40 ++++++++++++++++++++-------------------- singlemission.py | 2 +- 4 files changed, 32 insertions(+), 32 deletions(-) diff --git a/c5.csv b/c5.csv index 1447bf4b0..910a4e83f 100644 --- a/c5.csv +++ b/c5.csv @@ -145,10 +145,10 @@ aircraft:wing:detailed_wing,False,unitless mission:constraints:max_mach,0.77,unitless mission:design:cruise_altitude,34000,ft mission:design:gross_mass,840000,lbm -mission:design:range,2300,NM +mission:design:range,7000,NM mission:design:thrust_takeoff_per_eng,51250,lbf mission:landing:lift_coefficient_max,3.0,unitless -mission:summary:cruise_mach,0.77,unitless +mission:design:mach,0.77,unitless #mission:summary:fuel_flow_scaler,1.0,unitless mission:takeoff:fuel_simple,6.32,lbm mission:takeoff:lift_coefficient_max,3.62,unitless diff --git a/c5_ferry_phase_info.py b/c5_ferry_phase_info.py index c2b5ea55c..bf173692e 100644 --- a/c5_ferry_phase_info.py +++ b/c5_ferry_phase_info.py @@ -21,9 +21,9 @@ "constrain_final": False, "fix_duration": False, "initial_bounds": ((0.0, 0.0), "min"), - "duration_bounds": ((15.0, 45.0), "min"), + "duration_bounds": ((25.0, 75.0), "min"), }, - "initial_guesses": {"time": ([0.0, 30.0], "min")}, + "initial_guesses": {"time": ([0.0, 50.0], "min")}, }, "cruise_1": { "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, @@ -45,10 +45,10 @@ "fix_initial": False, "constrain_final": False, "fix_duration": False, - "initial_bounds": ((15.0, 45.0), "min"), - "duration_bounds": ((390.0, 1170.0), "min"), + "initial_bounds": ((25.0, 75.0), "min"), + "duration_bounds": ((115.0, 345.0), "min"), }, - "initial_guesses": {"time": ([30.0, 780.0], "min")}, + "initial_guesses": {"time": ([50.0, 230.0], "min")}, }, "descent_1": { "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, @@ -70,14 +70,14 @@ "fix_initial": False, "constrain_final": True, "fix_duration": False, - "initial_bounds": ((405.0, 1215.0), "min"), - "duration_bounds": ((12.5, 37.5), "min"), + "initial_bounds": ((140.0, 420.0), "min"), + "duration_bounds": ((10.0, 30.0), "min"), }, - "initial_guesses": {"time": ([810.0, 25.0], "min")}, + "initial_guesses": {"time": ([280.0, 20.0], "min")}, }, "post_mission": { "include_landing": False, "constrain_range": True, - "target_range": (6821.57, "nmi"), + "target_range": (2325.25, "nmi"), }, } diff --git a/outputted_phase_info.py b/outputted_phase_info.py index 3e84cf09c..b78f6f884 100644 --- a/outputted_phase_info.py +++ b/outputted_phase_info.py @@ -11,19 +11,19 @@ "order": 3, "solve_for_distance": False, "initial_mach": (0.3, "unitless"), - "final_mach": (0.77, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "final_mach": (0.75, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.77), "unitless"), "initial_altitude": (0.0, "ft"), - "final_altitude": (32000.0, "ft"), - "altitude_bounds": ((0.0, 32500.0), "ft"), + "final_altitude": (28000.0, "ft"), + "altitude_bounds": ((0.0, 28500.0), "ft"), "throttle_enforcement": "path_constraint", "fix_initial": True, "constrain_final": False, "fix_duration": False, "initial_bounds": ((0.0, 0.0), "min"), - "duration_bounds": ((15.0, 45.0), "min"), + "duration_bounds": ((25.0, 75.0), "min"), }, - "initial_guesses": {"time": ([0.0, 30.0], "min")}, + "initial_guesses": {"time": ([0.0, 50.0], "min")}, }, "cruise_1": { "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, @@ -35,20 +35,20 @@ "num_segments": 3, "order": 3, "solve_for_distance": False, - "initial_mach": (0.77, "unitless"), - "final_mach": (0.77, "unitless"), - "mach_bounds": ((0.75, 0.79), "unitless"), - "initial_altitude": (32000.0, "ft"), - "final_altitude": (32000.0, "ft"), - "altitude_bounds": ((31500.0, 32500.0), "ft"), + "initial_mach": (0.75, "unitless"), + "final_mach": (0.75, "unitless"), + "mach_bounds": ((0.73, 0.77), "unitless"), + "initial_altitude": (28000.0, "ft"), + "final_altitude": (28000.0, "ft"), + "altitude_bounds": ((27500.0, 28500.0), "ft"), "throttle_enforcement": "boundary_constraint", "fix_initial": False, "constrain_final": False, "fix_duration": False, - "initial_bounds": ((15.0, 45.0), "min"), - "duration_bounds": ((390.0, 1170.0), "min"), + "initial_bounds": ((25.0, 75.0), "min"), + "duration_bounds": ((380.0, 1140.0), "min"), }, - "initial_guesses": {"time": ([30.0, 780.0], "min")}, + "initial_guesses": {"time": ([50.0, 760.0], "min")}, }, "descent_1": { "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, @@ -60,12 +60,12 @@ "num_segments": 3, "order": 3, "solve_for_distance": False, - "initial_mach": (0.77, "unitless"), + "initial_mach": (0.75, "unitless"), "final_mach": (0.3, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), - "initial_altitude": (32000.0, "ft"), + "mach_bounds": ((0.27999999999999997, 0.77), "unitless"), + "initial_altitude": (28000.0, "ft"), "final_altitude": (0.0, "ft"), - "altitude_bounds": ((0.0, 32500.0), "ft"), + "altitude_bounds": ((0.0, 28500.0), "ft"), "throttle_enforcement": "path_constraint", "fix_initial": False, "constrain_final": True, @@ -78,6 +78,6 @@ "post_mission": { "include_landing": False, "constrain_range": True, - "target_range": (7001.03, "nmi"), + "target_range": (6771.56, "nmi"), }, } diff --git a/singlemission.py b/singlemission.py index e17b0397a..4719db68c 100644 --- a/singlemission.py +++ b/singlemission.py @@ -20,7 +20,7 @@ # Link phases and variables prob.link_phases() - prob.add_driver("SLSQP", max_iter=50) + prob.add_driver("SLSQP", max_iter=100) prob.add_design_variables() From 6ab89ad360f3ee686bb851c6bd8f9a6da5f216c3 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 24 Jul 2024 10:31:49 -0400 Subject: [PATCH 007/113] checkpt --- c5_ferry_phase_info.py | 20 ++++++++++---------- 1 file changed, 10 insertions(+), 10 deletions(-) diff --git a/c5_ferry_phase_info.py b/c5_ferry_phase_info.py index bf173692e..6237e3a41 100644 --- a/c5_ferry_phase_info.py +++ b/c5_ferry_phase_info.py @@ -14,8 +14,8 @@ "final_mach": (0.75, "unitless"), "mach_bounds": ((0.27999999999999997, 0.77), "unitless"), "initial_altitude": (0.0, "ft"), - "final_altitude": (28000.0, "ft"), - "altitude_bounds": ((0.0, 28500.0), "ft"), + "final_altitude": (26000.0, "ft"), + "altitude_bounds": ((0.0, 26500.0), "ft"), "throttle_enforcement": "path_constraint", "fix_initial": True, "constrain_final": False, @@ -25,7 +25,7 @@ }, "initial_guesses": {"time": ([0.0, 50.0], "min")}, }, - "cruise_1": { + "climb_2": { "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, "user_options": { "optimize_mach": False, @@ -38,17 +38,17 @@ "initial_mach": (0.75, "unitless"), "final_mach": (0.75, "unitless"), "mach_bounds": ((0.73, 0.77), "unitless"), - "initial_altitude": (28000.0, "ft"), + "initial_altitude": (26000.0, "ft"), "final_altitude": (28000.0, "ft"), - "altitude_bounds": ((27500.0, 28500.0), "ft"), + "altitude_bounds": ((25500.0, 28500.0), "ft"), "throttle_enforcement": "boundary_constraint", "fix_initial": False, "constrain_final": False, "fix_duration": False, "initial_bounds": ((25.0, 75.0), "min"), - "duration_bounds": ((115.0, 345.0), "min"), + "duration_bounds": ((225.0, 675.0), "min"), }, - "initial_guesses": {"time": ([50.0, 230.0], "min")}, + "initial_guesses": {"time": ([50.0, 450.0], "min")}, }, "descent_1": { "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, @@ -70,14 +70,14 @@ "fix_initial": False, "constrain_final": True, "fix_duration": False, - "initial_bounds": ((140.0, 420.0), "min"), + "initial_bounds": ((250.0, 750.0), "min"), "duration_bounds": ((10.0, 30.0), "min"), }, - "initial_guesses": {"time": ([280.0, 20.0], "min")}, + "initial_guesses": {"time": ([500.0, 20.0], "min")}, }, "post_mission": { "include_landing": False, "constrain_range": True, - "target_range": (2325.25, "nmi"), + "target_range": (4158.78, "nmi"), }, } From 9b64e703b7cadc7986870d96bcbab38bbebc250c Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 24 Jul 2024 13:15:16 -0400 Subject: [PATCH 008/113] added c5 mission variants csvs and phaseinfos --- c5.csv | 3 +- c5_ferry.csv | 167 ++++++++++++++++++++++++++++++++++ c5_ferry_phase_info.py | 40 ++++---- c5_intermediate.csv | 167 ++++++++++++++++++++++++++++++++++ c5_intermediate_phase_info.py | 83 +++++++++++++++++ c5_maxpayload.csv | 167 ++++++++++++++++++++++++++++++++++ c5_maxpayload_phase_info.py | 83 +++++++++++++++++ multimission.py | 55 +++++++---- outputted_phase_info.py | 77 +--------------- singlemission.py | 72 +++++++++++++-- 10 files changed, 793 insertions(+), 121 deletions(-) create mode 100644 c5_ferry.csv create mode 100644 c5_intermediate.csv create mode 100644 c5_intermediate_phase_info.py create mode 100644 c5_maxpayload.csv create mode 100644 c5_maxpayload_phase_info.py diff --git a/c5.csv b/c5.csv index 910a4e83f..186bb7e4f 100644 --- a/c5.csv +++ b/c5.csv @@ -11,10 +11,9 @@ aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm #aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless aircraft:crew_and_payload:mass_per_passenger,180.0,lbm -#aircraft:crew_and_payload:cargo_mass,281000,lbm +aircraft:crew_and_payload:cargo_mass,281000,lbm #aircraft:crew_and_payload:num_passengers,82,unitless - #aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless aircraft:crew_and_payload:num_flight_crew,7,unitless #aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless diff --git a/c5_ferry.csv b/c5_ferry.csv new file mode 100644 index 000000000..6540463d5 --- /dev/null +++ b/c5_ferry.csv @@ -0,0 +1,167 @@ +# author: Chris Psenica +#aircraft:air_conditioning:mass_scaler,1.0,unitless +#aircraft:anti_icing:mass_scaler,1.0,unitless +#aircraft:apu:mass_scaler,1.0,unitless +#aircraft:avionics:mass_scaler,1.0,unitless +#aircraft:canard:area,0.0,ft**2 +#aircraft:canard:aspect_ratio,0.0,unitless +#aircraft:canard:thickness_to_chord,0.0,unitless +aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm +#aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless +#aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:mass_per_passenger,180.0,lbm + +aircraft:crew_and_payload:cargo_mass,0,lbm +#aircraft:crew_and_payload:num_passengers,82,unitless + +#aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:num_flight_crew,7,unitless +#aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless +#aircraft:crew_and_payload:wing_cargo,0.0,lbm +#aircraft:design:base_area,0.0,ft**2 +#aircraft:design:empty_mass_margin_scaler,1.0,unitless +#aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless +#aircraft:design:touchdown_mass,498554,lbm +aircraft:design:reserve_fuel_additional,0,lbm +#aircraft:design:subsonic_drag_coeff_factor,1.0,unitless +#aircraft:design:supersonic_drag_coeff_factor,1.0,unitless +aircraft:design:use_alt_mass,False,unitless +#aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless +#aircraft:electrical:mass_scaler,1.0,unitless + +aircraft:engine:data_file,models/engines/CF6.deck,unitless + +aircraft:engine:additional_mass_fraction,0.,unitless +aircraft:engine:constant_fuel_consumption,0.,lbm/h + +aircraft:engine:flight_idle_thrust_fraction,0.0,unitless +aircraft:engine:flight_idle_max_fraction,1.0,unitless +aircraft:engine:flight_idle_min_fraction,0.08,unitless +#aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless +#aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless +aircraft:engine:generate_flight_idle,False,unitless +aircraft:engine:geopotential_alt,False,unitless +aircraft:engine:ignore_negative_thrust,False,unitless +aircraft:engine:interpolation_method,slinear,unitless +aircraft:engine:mass_scaler,1.0,unitless +aircraft:engine:mass,8176,lbm +aircraft:engine:reference_mass,8176,lbm +aircraft:engine:reference_sls_thrust,51250.,lbf +aircraft:engine:scale_mass,True,unitless +aircraft:engine:scale_performance,True,unitless +aircraft:engine:scaled_sls_thrust,51250,lbf +#aircraft:engine:subsonic_fuel_flow_scaler,1.0,unitless +#aircraft:engine:supersonic_fuel_flow_scaler,1.0,unitless +#aircraft:engine:thrust_reversers_mass_scaler,1.0,unitless +aircraft:engine:num_fuselage_engines,0,unitless +aircraft:engine:num_engines,4,unitless +aircraft:engine:num_wing_engines,4,unitless +aircraft:engine:wing_locations,[0.3561541339,0.555929667],unitless +#aircraft:fins:area,0.0,ft**2 +#aircraft:fins:mass_scaler,1.0,unitless +#aircraft:fins:mass,0.0,lbm +#aircraft:fins:num_fins,0,unitless +#aircraft:fins:taper_ratio,10.0,unitless +aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm +#aircraft:fuel:density_ratio,1.0,unitless +#aircraft:fuel:fuel_system_mass_scaler,1.0,unitless +aircraft:fuel:fuselage_fuel_capacity,0.0,lbm +aircraft:fuel:num_tanks,12,unitless +aircraft:fuel:total_capacity,341446,lbm +#aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless +#aircraft:furnishings:mass_scaler,1.0,unitless +aircraft:fuselage:length,230.58,ft +#aircraft:fuselage:mass_scaler,1.0,unitless +aircraft:fuselage:max_height,26.83,ft +aircraft:fuselage:max_width,23.9,ft +aircraft:fuselage:military_cargo_floor,True,unitless +aircraft:fuselage:num_fuselages,1,unitless +aircraft:fuselage:passenger_compartment_length,143.75,ft +aircraft:fuselage:planform_area,4462.78,ft**2 +#aircraft:fuselage:wetted_area_scaler,1.0,unitless +aircraft:horizontal_tail:area,965.8,ft**2 +aircraft:horizontal_tail:aspect_ratio,4.2,unitless +#aircraft:horizontal_tail:mass_scaler,1.0,unitless +aircraft:horizontal_tail:taper_ratio,0.43,unitless +aircraft:horizontal_tail:thickness_to_chord,0.16,unitless +aircraft:horizontal_tail:vertical_tail_fraction,1.0,unitless +#aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless +#aircraft:hydraulics:mass_scaler,1.0,unitless +#aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 +#aircraft:instruments:mass_scaler,1.0,unitless +#aircraft:landing_gear:carrier_based,False,unitless +#aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless +#aircraft:landing_gear:main_gear_oleo_length,45,inch +#aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless +#aircraft:landing_gear:nose_gear_oleo_length,45,inch +aircraft:nacelle:avg_diameter,9.15,ft +aircraft:nacelle:avg_length,20.56,ft +#aircraft:nacelle:mass_scaler,1.0,unitless +#aircraft:nacelle:wetted_area_scaler,1.0,unitless +#aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 +#aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless +#aircraft:propulsion:misc_mass_scaler,1.0,unitless +aircraft:vertical_tail:area,537.9,ft**2 +aircraft:vertical_tail:aspect_ratio,0.958,unitless +#aircraft:vertical_tail:mass_scaler,1.0,unitless +aircraft:vertical_tail:num_tails,1,unitless +aircraft:vertical_tail:taper_ratio,0.846,unitless +aircraft:vertical_tail:thickness_to_chord,0.157,unitless +#aircraft:vertical_tail:wetted_area_scaler,1.0,unitless +aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless +aircraft:wing:airfoil_technology,1.0,unitless +aircraft:wing:area,6200,ft**2 +aircraft:wing:aspect_ratio,7.75,unitless +#aircraft:wing:bending_mass_scaler,1.0,unitless +#aircraft:wing:composite_fraction,0.1,unitless +aircraft:wing:control_surface_area,2323.7,ft**2 +aircraft:wing:control_surface_area_ratio,0.37479,unitless +aircraft:wing:load_distribution_control,2.0,unitless +aircraft:wing:load_fraction,1.0,unitless +#aircraft:wing:mass_scaler,1.0,unitless +aircraft:wing:max_camber_at_70_semispan,0.0,unitless +#aircraft:wing:misc_mass_scaler,1.0,unitless +#aircraft:wing:shear_control_mass_scaler,1.0,unitless +aircraft:wing:span_efficiency_reduction,False,unitless +aircraft:wing:span,222.75,ft +#aircraft:wing:strut_bracing_factor,0.0,unitless +#aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless +aircraft:wing:sweep,20.0,deg +aircraft:wing:taper_ratio,0.419,unitless +aircraft:wing:thickness_to_chord,0.1284,unitless +aircraft:wing:ultimate_load_factor,3.75,unitless +aircraft:wing:var_sweep_mass_penalty,0.0,unitless +#aircraft:wing:wetted_area_scaler,1.0,unitless +aircraft:wing:num_integration_stations,50,unitless +aircraft:wing:thickness_to_chord_dist,0.1239,0.108,0.013,unitless +aircraft:wing:load_path_sweep_dist,0.0,0.0,deg +aircraft:wing:input_station_dist,0.0,0.3298,0.884,unitless +aircraft:wing:chord_per_semispan,0.362,0.2667,0.0456,unitless +aircraft:wing:glove_and_bat,0.0,ft**2 +aircraft:wing:detailed_wing,False,unitless + + +mission:constraints:max_mach,0.77,unitless +mission:design:cruise_altitude,34000,ft +mission:design:gross_mass,840000,lbm +mission:design:range,7000.0,NM +mission:design:thrust_takeoff_per_eng,51250,lbf +mission:landing:lift_coefficient_max,3.0,unitless +mission:design:mach,0.77,unitless +#mission:summary:fuel_flow_scaler,1.0,unitless +mission:takeoff:fuel_simple,6.32,lbm +mission:takeoff:lift_coefficient_max,3.62,unitless +mission:takeoff:lift_over_drag,19.5,unitless +settings:equations_of_motion,height_energy +settings:mass_method,FLOPS + + +### missions definition +# mission_name: payload +# times: 0, 50, 280, 300 +# altitudes: 0, 30000, 30000, 0 +# machs: 0.30, 0.77, 0.77, 0.30 +# optimize_altitudes: F,F,F +# optimize_machs: F,F,F +# takeoff: F +# landing: F diff --git a/c5_ferry_phase_info.py b/c5_ferry_phase_info.py index 6237e3a41..6a472ed2f 100644 --- a/c5_ferry_phase_info.py +++ b/c5_ferry_phase_info.py @@ -11,11 +11,11 @@ "order": 3, "solve_for_distance": False, "initial_mach": (0.3, "unitless"), - "final_mach": (0.75, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.77), "unitless"), + "final_mach": (0.77, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), "initial_altitude": (0.0, "ft"), - "final_altitude": (26000.0, "ft"), - "altitude_bounds": ((0.0, 26500.0), "ft"), + "final_altitude": (29500.0, "ft"), + "altitude_bounds": ((0.0, 30000.0), "ft"), "throttle_enforcement": "path_constraint", "fix_initial": True, "constrain_final": False, @@ -35,20 +35,20 @@ "num_segments": 3, "order": 3, "solve_for_distance": False, - "initial_mach": (0.75, "unitless"), - "final_mach": (0.75, "unitless"), - "mach_bounds": ((0.73, 0.77), "unitless"), - "initial_altitude": (26000.0, "ft"), - "final_altitude": (28000.0, "ft"), - "altitude_bounds": ((25500.0, 28500.0), "ft"), + "initial_mach": (0.77, "unitless"), + "final_mach": (0.77, "unitless"), + "mach_bounds": ((0.75, 0.79), "unitless"), + "initial_altitude": (29500.0, "ft"), + "final_altitude": (32000.0, "ft"), + "altitude_bounds": ((29000.0, 32500.0), "ft"), "throttle_enforcement": "boundary_constraint", "fix_initial": False, "constrain_final": False, "fix_duration": False, "initial_bounds": ((25.0, 75.0), "min"), - "duration_bounds": ((225.0, 675.0), "min"), + "duration_bounds": ((381.0, 1143.0), "min"), }, - "initial_guesses": {"time": ([50.0, 450.0], "min")}, + "initial_guesses": {"time": ([50.0, 762.0], "min")}, }, "descent_1": { "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, @@ -60,24 +60,24 @@ "num_segments": 3, "order": 3, "solve_for_distance": False, - "initial_mach": (0.75, "unitless"), + "initial_mach": (0.77, "unitless"), "final_mach": (0.3, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.77), "unitless"), - "initial_altitude": (28000.0, "ft"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (32000.0, "ft"), "final_altitude": (0.0, "ft"), - "altitude_bounds": ((0.0, 28500.0), "ft"), + "altitude_bounds": ((0.0, 32500.0), "ft"), "throttle_enforcement": "path_constraint", "fix_initial": False, "constrain_final": True, "fix_duration": False, - "initial_bounds": ((250.0, 750.0), "min"), - "duration_bounds": ((10.0, 30.0), "min"), + "initial_bounds": ((406.0, 1218.0), "min"), + "duration_bounds": ((15.5, 46.5), "min"), }, - "initial_guesses": {"time": ([500.0, 20.0], "min")}, + "initial_guesses": {"time": ([812.0, 31.0], "min")}, }, "post_mission": { "include_landing": False, "constrain_range": True, - "target_range": (4158.78, "nmi"), + "target_range": (7001.59, "nmi"), }, } diff --git a/c5_intermediate.csv b/c5_intermediate.csv new file mode 100644 index 000000000..bb4565239 --- /dev/null +++ b/c5_intermediate.csv @@ -0,0 +1,167 @@ +# author: Chris Psenica +#aircraft:air_conditioning:mass_scaler,1.0,unitless +#aircraft:anti_icing:mass_scaler,1.0,unitless +#aircraft:apu:mass_scaler,1.0,unitless +#aircraft:avionics:mass_scaler,1.0,unitless +#aircraft:canard:area,0.0,ft**2 +#aircraft:canard:aspect_ratio,0.0,unitless +#aircraft:canard:thickness_to_chord,0.0,unitless +aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm +#aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless +#aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:mass_per_passenger,180.0,lbm + +aircraft:crew_and_payload:cargo_mass,120000.0,lbm +#aircraft:crew_and_payload:num_passengers,82,unitless + +#aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:num_flight_crew,7,unitless +#aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless +#aircraft:crew_and_payload:wing_cargo,0.0,lbm +#aircraft:design:base_area,0.0,ft**2 +#aircraft:design:empty_mass_margin_scaler,1.0,unitless +#aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless +#aircraft:design:touchdown_mass,498554,lbm +aircraft:design:reserve_fuel_additional,0,lbm +#aircraft:design:subsonic_drag_coeff_factor,1.0,unitless +#aircraft:design:supersonic_drag_coeff_factor,1.0,unitless +aircraft:design:use_alt_mass,False,unitless +#aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless +#aircraft:electrical:mass_scaler,1.0,unitless + +aircraft:engine:data_file,models/engines/CF6.deck,unitless + +aircraft:engine:additional_mass_fraction,0.,unitless +aircraft:engine:constant_fuel_consumption,0.,lbm/h + +aircraft:engine:flight_idle_thrust_fraction,0.0,unitless +aircraft:engine:flight_idle_max_fraction,1.0,unitless +aircraft:engine:flight_idle_min_fraction,0.08,unitless +#aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless +#aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless +aircraft:engine:generate_flight_idle,False,unitless +aircraft:engine:geopotential_alt,False,unitless +aircraft:engine:ignore_negative_thrust,False,unitless +aircraft:engine:interpolation_method,slinear,unitless +aircraft:engine:mass_scaler,1.0,unitless +aircraft:engine:mass,8176,lbm +aircraft:engine:reference_mass,8176,lbm +aircraft:engine:reference_sls_thrust,51250.,lbf +aircraft:engine:scale_mass,True,unitless +aircraft:engine:scale_performance,True,unitless +aircraft:engine:scaled_sls_thrust,51250,lbf +#aircraft:engine:subsonic_fuel_flow_scaler,1.0,unitless +#aircraft:engine:supersonic_fuel_flow_scaler,1.0,unitless +#aircraft:engine:thrust_reversers_mass_scaler,1.0,unitless +aircraft:engine:num_fuselage_engines,0,unitless +aircraft:engine:num_engines,4,unitless +aircraft:engine:num_wing_engines,4,unitless +aircraft:engine:wing_locations,[0.3561541339,0.555929667],unitless +#aircraft:fins:area,0.0,ft**2 +#aircraft:fins:mass_scaler,1.0,unitless +#aircraft:fins:mass,0.0,lbm +#aircraft:fins:num_fins,0,unitless +#aircraft:fins:taper_ratio,10.0,unitless +aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm +#aircraft:fuel:density_ratio,1.0,unitless +#aircraft:fuel:fuel_system_mass_scaler,1.0,unitless +aircraft:fuel:fuselage_fuel_capacity,0.0,lbm +aircraft:fuel:num_tanks,12,unitless +aircraft:fuel:total_capacity,341446,lbm +#aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless +#aircraft:furnishings:mass_scaler,1.0,unitless +aircraft:fuselage:length,230.58,ft +#aircraft:fuselage:mass_scaler,1.0,unitless +aircraft:fuselage:max_height,26.83,ft +aircraft:fuselage:max_width,23.9,ft +aircraft:fuselage:military_cargo_floor,True,unitless +aircraft:fuselage:num_fuselages,1,unitless +aircraft:fuselage:passenger_compartment_length,143.75,ft +aircraft:fuselage:planform_area,4462.78,ft**2 +#aircraft:fuselage:wetted_area_scaler,1.0,unitless +aircraft:horizontal_tail:area,965.8,ft**2 +aircraft:horizontal_tail:aspect_ratio,4.2,unitless +#aircraft:horizontal_tail:mass_scaler,1.0,unitless +aircraft:horizontal_tail:taper_ratio,0.43,unitless +aircraft:horizontal_tail:thickness_to_chord,0.16,unitless +aircraft:horizontal_tail:vertical_tail_fraction,1.0,unitless +#aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless +#aircraft:hydraulics:mass_scaler,1.0,unitless +#aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 +#aircraft:instruments:mass_scaler,1.0,unitless +#aircraft:landing_gear:carrier_based,False,unitless +#aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless +#aircraft:landing_gear:main_gear_oleo_length,45,inch +#aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless +#aircraft:landing_gear:nose_gear_oleo_length,45,inch +aircraft:nacelle:avg_diameter,9.15,ft +aircraft:nacelle:avg_length,20.56,ft +#aircraft:nacelle:mass_scaler,1.0,unitless +#aircraft:nacelle:wetted_area_scaler,1.0,unitless +#aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 +#aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless +#aircraft:propulsion:misc_mass_scaler,1.0,unitless +aircraft:vertical_tail:area,537.9,ft**2 +aircraft:vertical_tail:aspect_ratio,0.958,unitless +#aircraft:vertical_tail:mass_scaler,1.0,unitless +aircraft:vertical_tail:num_tails,1,unitless +aircraft:vertical_tail:taper_ratio,0.846,unitless +aircraft:vertical_tail:thickness_to_chord,0.157,unitless +#aircraft:vertical_tail:wetted_area_scaler,1.0,unitless +aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless +aircraft:wing:airfoil_technology,1.0,unitless +aircraft:wing:area,6200,ft**2 +aircraft:wing:aspect_ratio,7.75,unitless +#aircraft:wing:bending_mass_scaler,1.0,unitless +#aircraft:wing:composite_fraction,0.1,unitless +aircraft:wing:control_surface_area,2323.7,ft**2 +aircraft:wing:control_surface_area_ratio,0.37479,unitless +aircraft:wing:load_distribution_control,2.0,unitless +aircraft:wing:load_fraction,1.0,unitless +#aircraft:wing:mass_scaler,1.0,unitless +aircraft:wing:max_camber_at_70_semispan,0.0,unitless +#aircraft:wing:misc_mass_scaler,1.0,unitless +#aircraft:wing:shear_control_mass_scaler,1.0,unitless +aircraft:wing:span_efficiency_reduction,False,unitless +aircraft:wing:span,222.75,ft +#aircraft:wing:strut_bracing_factor,0.0,unitless +#aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless +aircraft:wing:sweep,20.0,deg +aircraft:wing:taper_ratio,0.419,unitless +aircraft:wing:thickness_to_chord,0.1284,unitless +aircraft:wing:ultimate_load_factor,3.75,unitless +aircraft:wing:var_sweep_mass_penalty,0.0,unitless +#aircraft:wing:wetted_area_scaler,1.0,unitless +aircraft:wing:num_integration_stations,50,unitless +aircraft:wing:thickness_to_chord_dist,0.1239,0.108,0.013,unitless +aircraft:wing:load_path_sweep_dist,0.0,0.0,deg +aircraft:wing:input_station_dist,0.0,0.3298,0.884,unitless +aircraft:wing:chord_per_semispan,0.362,0.2667,0.0456,unitless +aircraft:wing:glove_and_bat,0.0,ft**2 +aircraft:wing:detailed_wing,False,unitless + + +mission:constraints:max_mach,0.77,unitless +mission:design:cruise_altitude,34000,ft +mission:design:gross_mass,840000,lbm +mission:design:range,4800.0,NM +mission:design:thrust_takeoff_per_eng,51250,lbf +mission:landing:lift_coefficient_max,3.0,unitless +mission:design:mach,0.77,unitless +#mission:summary:fuel_flow_scaler,1.0,unitless +mission:takeoff:fuel_simple,6.32,lbm +mission:takeoff:lift_coefficient_max,3.62,unitless +mission:takeoff:lift_over_drag,19.5,unitless +settings:equations_of_motion,height_energy +settings:mass_method,FLOPS + + +### missions definition +# mission_name: payload +# times: 0, 50, 280, 300 +# altitudes: 0, 30000, 30000, 0 +# machs: 0.30, 0.77, 0.77, 0.30 +# optimize_altitudes: F,F,F +# optimize_machs: F,F,F +# takeoff: F +# landing: F diff --git a/c5_intermediate_phase_info.py b/c5_intermediate_phase_info.py new file mode 100644 index 000000000..a8b462673 --- /dev/null +++ b/c5_intermediate_phase_info.py @@ -0,0 +1,83 @@ +phase_info = { + "pre_mission": {"include_takeoff": False, "optimize_mass": True}, + "climb_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.3, "unitless"), + "final_mach": (0.77, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (0.0, "ft"), + "final_altitude": (29500.0, "ft"), + "altitude_bounds": ((0.0, 30000.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": True, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((0.0, 0.0), "min"), + "duration_bounds": ((25.0, 75.0), "min"), + }, + "initial_guesses": {"time": ([0.0, 50.0], "min")}, + }, + "climb_2": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.77, "unitless"), + "final_mach": (0.77, "unitless"), + "mach_bounds": ((0.75, 0.79), "unitless"), + "initial_altitude": (29500.0, "ft"), + "final_altitude": (32000.0, "ft"), + "altitude_bounds": ((29000.0, 32500.0), "ft"), + "throttle_enforcement": "boundary_constraint", + "fix_initial": False, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((25.0, 75.0), "min"), + "duration_bounds": ((255.0, 765.0), "min"), + }, + "initial_guesses": {"time": ([50.0, 510.0], "min")}, + }, + "descent_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.77, "unitless"), + "final_mach": (0.3, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (32000.0, "ft"), + "final_altitude": (0.0, "ft"), + "altitude_bounds": ((0.0, 32500.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": False, + "constrain_final": True, + "fix_duration": False, + "initial_bounds": ((280.0, 840.0), "min"), + "duration_bounds": ((15.0, 45.0), "min"), + }, + "initial_guesses": {"time": ([560.0, 30.0], "min")}, + }, + "post_mission": { + "include_landing": False, + "constrain_range": True, + "target_range": (4839.41, "nmi"), + }, +} diff --git a/c5_maxpayload.csv b/c5_maxpayload.csv new file mode 100644 index 000000000..07a6fb381 --- /dev/null +++ b/c5_maxpayload.csv @@ -0,0 +1,167 @@ +# author: Chris Psenica +#aircraft:air_conditioning:mass_scaler,1.0,unitless +#aircraft:anti_icing:mass_scaler,1.0,unitless +#aircraft:apu:mass_scaler,1.0,unitless +#aircraft:avionics:mass_scaler,1.0,unitless +#aircraft:canard:area,0.0,ft**2 +#aircraft:canard:aspect_ratio,0.0,unitless +#aircraft:canard:thickness_to_chord,0.0,unitless +aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm +#aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless +#aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:mass_per_passenger,180.0,lbm + +aircraft:crew_and_payload:cargo_mass,281000.0,lbm +#aircraft:crew_and_payload:num_passengers,82,unitless + +#aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:num_flight_crew,7,unitless +#aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless +#aircraft:crew_and_payload:wing_cargo,0.0,lbm +#aircraft:design:base_area,0.0,ft**2 +#aircraft:design:empty_mass_margin_scaler,1.0,unitless +#aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless +#aircraft:design:touchdown_mass,498554,lbm +aircraft:design:reserve_fuel_additional,0,lbm +#aircraft:design:subsonic_drag_coeff_factor,1.0,unitless +#aircraft:design:supersonic_drag_coeff_factor,1.0,unitless +aircraft:design:use_alt_mass,False,unitless +#aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless +#aircraft:electrical:mass_scaler,1.0,unitless + +aircraft:engine:data_file,models/engines/CF6.deck,unitless + +aircraft:engine:additional_mass_fraction,0.,unitless +aircraft:engine:constant_fuel_consumption,0.,lbm/h + +aircraft:engine:flight_idle_thrust_fraction,0.0,unitless +aircraft:engine:flight_idle_max_fraction,1.0,unitless +aircraft:engine:flight_idle_min_fraction,0.08,unitless +#aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless +#aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless +aircraft:engine:generate_flight_idle,False,unitless +aircraft:engine:geopotential_alt,False,unitless +aircraft:engine:ignore_negative_thrust,False,unitless +aircraft:engine:interpolation_method,slinear,unitless +aircraft:engine:mass_scaler,1.0,unitless +aircraft:engine:mass,8176,lbm +aircraft:engine:reference_mass,8176,lbm +aircraft:engine:reference_sls_thrust,51250.,lbf +aircraft:engine:scale_mass,True,unitless +aircraft:engine:scale_performance,True,unitless +aircraft:engine:scaled_sls_thrust,51250,lbf +#aircraft:engine:subsonic_fuel_flow_scaler,1.0,unitless +#aircraft:engine:supersonic_fuel_flow_scaler,1.0,unitless +#aircraft:engine:thrust_reversers_mass_scaler,1.0,unitless +aircraft:engine:num_fuselage_engines,0,unitless +aircraft:engine:num_engines,4,unitless +aircraft:engine:num_wing_engines,4,unitless +aircraft:engine:wing_locations,[0.3561541339,0.555929667],unitless +#aircraft:fins:area,0.0,ft**2 +#aircraft:fins:mass_scaler,1.0,unitless +#aircraft:fins:mass,0.0,lbm +#aircraft:fins:num_fins,0,unitless +#aircraft:fins:taper_ratio,10.0,unitless +aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm +#aircraft:fuel:density_ratio,1.0,unitless +#aircraft:fuel:fuel_system_mass_scaler,1.0,unitless +aircraft:fuel:fuselage_fuel_capacity,0.0,lbm +aircraft:fuel:num_tanks,12,unitless +aircraft:fuel:total_capacity,341446,lbm +#aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless +#aircraft:furnishings:mass_scaler,1.0,unitless +aircraft:fuselage:length,230.58,ft +#aircraft:fuselage:mass_scaler,1.0,unitless +aircraft:fuselage:max_height,26.83,ft +aircraft:fuselage:max_width,23.9,ft +aircraft:fuselage:military_cargo_floor,True,unitless +aircraft:fuselage:num_fuselages,1,unitless +aircraft:fuselage:passenger_compartment_length,143.75,ft +aircraft:fuselage:planform_area,4462.78,ft**2 +#aircraft:fuselage:wetted_area_scaler,1.0,unitless +aircraft:horizontal_tail:area,965.8,ft**2 +aircraft:horizontal_tail:aspect_ratio,4.2,unitless +#aircraft:horizontal_tail:mass_scaler,1.0,unitless +aircraft:horizontal_tail:taper_ratio,0.43,unitless +aircraft:horizontal_tail:thickness_to_chord,0.16,unitless +aircraft:horizontal_tail:vertical_tail_fraction,1.0,unitless +#aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless +#aircraft:hydraulics:mass_scaler,1.0,unitless +#aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 +#aircraft:instruments:mass_scaler,1.0,unitless +#aircraft:landing_gear:carrier_based,False,unitless +#aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless +#aircraft:landing_gear:main_gear_oleo_length,45,inch +#aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless +#aircraft:landing_gear:nose_gear_oleo_length,45,inch +aircraft:nacelle:avg_diameter,9.15,ft +aircraft:nacelle:avg_length,20.56,ft +#aircraft:nacelle:mass_scaler,1.0,unitless +#aircraft:nacelle:wetted_area_scaler,1.0,unitless +#aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 +#aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless +#aircraft:propulsion:misc_mass_scaler,1.0,unitless +aircraft:vertical_tail:area,537.9,ft**2 +aircraft:vertical_tail:aspect_ratio,0.958,unitless +#aircraft:vertical_tail:mass_scaler,1.0,unitless +aircraft:vertical_tail:num_tails,1,unitless +aircraft:vertical_tail:taper_ratio,0.846,unitless +aircraft:vertical_tail:thickness_to_chord,0.157,unitless +#aircraft:vertical_tail:wetted_area_scaler,1.0,unitless +aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless +aircraft:wing:airfoil_technology,1.0,unitless +aircraft:wing:area,6200,ft**2 +aircraft:wing:aspect_ratio,7.75,unitless +#aircraft:wing:bending_mass_scaler,1.0,unitless +#aircraft:wing:composite_fraction,0.1,unitless +aircraft:wing:control_surface_area,2323.7,ft**2 +aircraft:wing:control_surface_area_ratio,0.37479,unitless +aircraft:wing:load_distribution_control,2.0,unitless +aircraft:wing:load_fraction,1.0,unitless +#aircraft:wing:mass_scaler,1.0,unitless +aircraft:wing:max_camber_at_70_semispan,0.0,unitless +#aircraft:wing:misc_mass_scaler,1.0,unitless +#aircraft:wing:shear_control_mass_scaler,1.0,unitless +aircraft:wing:span_efficiency_reduction,False,unitless +aircraft:wing:span,222.75,ft +#aircraft:wing:strut_bracing_factor,0.0,unitless +#aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless +aircraft:wing:sweep,20.0,deg +aircraft:wing:taper_ratio,0.419,unitless +aircraft:wing:thickness_to_chord,0.1284,unitless +aircraft:wing:ultimate_load_factor,3.75,unitless +aircraft:wing:var_sweep_mass_penalty,0.0,unitless +#aircraft:wing:wetted_area_scaler,1.0,unitless +aircraft:wing:num_integration_stations,50,unitless +aircraft:wing:thickness_to_chord_dist,0.1239,0.108,0.013,unitless +aircraft:wing:load_path_sweep_dist,0.0,0.0,deg +aircraft:wing:input_station_dist,0.0,0.3298,0.884,unitless +aircraft:wing:chord_per_semispan,0.362,0.2667,0.0456,unitless +aircraft:wing:glove_and_bat,0.0,ft**2 +aircraft:wing:detailed_wing,False,unitless + + +mission:constraints:max_mach,0.77,unitless +mission:design:cruise_altitude,34000,ft +mission:design:gross_mass,840000,lbm +mission:design:range,2150.0,NM +mission:design:thrust_takeoff_per_eng,51250,lbf +mission:landing:lift_coefficient_max,3.0,unitless +mission:design:mach,0.77,unitless +#mission:summary:fuel_flow_scaler,1.0,unitless +mission:takeoff:fuel_simple,6.32,lbm +mission:takeoff:lift_coefficient_max,3.62,unitless +mission:takeoff:lift_over_drag,19.5,unitless +settings:equations_of_motion,height_energy +settings:mass_method,FLOPS + + +### missions definition +# mission_name: payload +# times: 0, 50, 280, 300 +# altitudes: 0, 30000, 30000, 0 +# machs: 0.30, 0.77, 0.77, 0.30 +# optimize_altitudes: F,F,F +# optimize_machs: F,F,F +# takeoff: F +# landing: F diff --git a/c5_maxpayload_phase_info.py b/c5_maxpayload_phase_info.py new file mode 100644 index 000000000..a52acec96 --- /dev/null +++ b/c5_maxpayload_phase_info.py @@ -0,0 +1,83 @@ +phase_info = { + "pre_mission": {"include_takeoff": False, "optimize_mass": True}, + "climb_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.3, "unitless"), + "final_mach": (0.77, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (0.0, "ft"), + "final_altitude": (29500.0, "ft"), + "altitude_bounds": ((0.0, 30000.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": True, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((0.0, 0.0), "min"), + "duration_bounds": ((25.0, 75.0), "min"), + }, + "initial_guesses": {"time": ([0.0, 50.0], "min")}, + }, + "climb_2": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.77, "unitless"), + "final_mach": (0.77, "unitless"), + "mach_bounds": ((0.75, 0.79), "unitless"), + "initial_altitude": (29500.0, "ft"), + "final_altitude": (32000.0, "ft"), + "altitude_bounds": ((29000.0, 32500.0), "ft"), + "throttle_enforcement": "boundary_constraint", + "fix_initial": False, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((25.0, 75.0), "min"), + "duration_bounds": ((105.0, 315.0), "min"), + }, + "initial_guesses": {"time": ([50.0, 210.0], "min")}, + }, + "descent_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.77, "unitless"), + "final_mach": (0.3, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (32000.0, "ft"), + "final_altitude": (0.0, "ft"), + "altitude_bounds": ((0.0, 32500.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": False, + "constrain_final": True, + "fix_duration": False, + "initial_bounds": ((130.0, 390.0), "min"), + "duration_bounds": ((15.0, 45.0), "min"), + }, + "initial_guesses": {"time": ([260.0, 30.0], "min")}, + }, + "post_mission": { + "include_landing": False, + "constrain_range": True, + "target_range": (2272.47, "nmi"), + }, +} diff --git a/multimission.py b/multimission.py index b64870317..2524cf330 100644 --- a/multimission.py +++ b/multimission.py @@ -6,24 +6,24 @@ Phase info: defines a particular mission, will have multiple phase infos """ import aviary.api as av -from aviary.examples.example_phase_info import phase_info -from copy import deepcopy import openmdao.api as om +import dymos as dm +from c5_ferry_phase_info import phase_info as c5_ferry_phase_info +from c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info +from c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info -# TODO: modify one of these to represent a different mission (e.g. change cruise length) -phase_info1 = deepcopy(phase_info) -phase_info2 = deepcopy(phase_info) +planes = ['c5_maxpayload.csv', 'c5_intermediate.csv'] +phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] if __name__ == '__main__': - super_prob = om.Problem.model() + super_prob = om.Problem() prob1 = av.AviaryProblem() prob2 = av.AviaryProblem() # Load aircraft and options data from user # Allow for user overrides here - # TODO: modify one of these to represent a different payload case - prob1.load_inputs('models/test_aircraft/aircraft_for_bench_FwFm.csv', phase_info1) - prob2.load_inputs('models/test_aircraft/aircraft_for_bench_FwFm.csv', phase_info2) + prob1.load_inputs(planes[0], phase_infos[0]) + prob2.load_inputs(planes[1], phase_infos[1]) # Preprocess inputs prob1.check_and_preprocess_inputs() @@ -42,18 +42,27 @@ prob1.link_phases() prob2.link_phases() + super_prob.model.add_subsystem('prob1', prob1) + super_prob.model.add_subsystem('prob2', prob2) + super_prob.model.add_subsystem('compound', + om.ExecComp('compound = a + b'), + promotes=['compound', 'a', 'b']) + super_prob.model.connect('prob1.mission.design.gross_mass', 'a') + super_prob.model.connect('prob2.mission.design.gross_mass', 'b') + super_prob.model.connect('prob1.mission.design.gross_mass', + 'prob2.mission.design.gross_mass') super_prob.add_driver("SLSQP", max_iter=100) - super_prob.add_parameter('mission.design.gross_mass') + # super_prob.add_parameter('mission.design.gross_mass') # use submodelcomp to instantiate both problems inside of the super problem # https://openmdao.org/newdocs/versions/latest/features/building_blocks/components/submodel_comp.html?highlight=subproblem # promote the correct inputs and outputs from the submodels - # add and execComp that sums the fuel burn output + # add an execComp that sums the fuel burn output # Load optimization problem formulation # Detail which variables the optimizer can control - super_prob.add_objective() # output from execcomp goes here) + super_prob.model.add_objective('compound') # output from execcomp goes here) super_prob.setup() @@ -61,16 +70,30 @@ prob2.set_initial_guesses() # remove all plots and extras - super_prob.run_aviary_problem(record_filename='reserve_mission_fixedrange.db') - super_prob.get_val() # look at final fuel burn + dm.run_problem(super_prob) + # super_prob.run_aviary_problem(record_filename='reserve_mission_fixedrange.db') + # super_prob.get_val() # look at final fuel burn """ Ferry mission phase info: -Times (min): 0, 30, 810, 835 - Alt (ft): 0, 32000, 32000, 0 +Times (min): 0, 50, 812, 843 + Alt (ft): 0, 29500, 32000, 0 Mach: 0.3, 0.77, 0.77, 0.3 +Est. Range: 7001 nmi +Notes: 32k in 30 mins too fast for aviary, climb to low alt then slow rise +Intermediate mission phase info: +Times (min): 0, 50, 560, 590 + Alt (ft): 0, 29500, 32000, 0 + Mach: 0.3, 0.77, 0.77, 0.3 +Est. Range: 4839 nmi + +Max Payload mission phase info: +Times (min): 0, 50, 260, 290 + Alt (ft): 0, 29500, 32000, 0 + Mach: 0.3, 0.77, 0.77, 0.3 +Est. Range: 2272 nmi Hard to find multiple payload/range values for FwFm (737), so use C-5 instead Based on: diff --git a/outputted_phase_info.py b/outputted_phase_info.py index b78f6f884..9e9fd754f 100644 --- a/outputted_phase_info.py +++ b/outputted_phase_info.py @@ -1,83 +1,8 @@ phase_info = { "pre_mission": {"include_takeoff": False, "optimize_mass": True}, - "climb_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.3, "unitless"), - "final_mach": (0.75, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.77), "unitless"), - "initial_altitude": (0.0, "ft"), - "final_altitude": (28000.0, "ft"), - "altitude_bounds": ((0.0, 28500.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": True, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((0.0, 0.0), "min"), - "duration_bounds": ((25.0, 75.0), "min"), - }, - "initial_guesses": {"time": ([0.0, 50.0], "min")}, - }, - "cruise_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.75, "unitless"), - "final_mach": (0.75, "unitless"), - "mach_bounds": ((0.73, 0.77), "unitless"), - "initial_altitude": (28000.0, "ft"), - "final_altitude": (28000.0, "ft"), - "altitude_bounds": ((27500.0, 28500.0), "ft"), - "throttle_enforcement": "boundary_constraint", - "fix_initial": False, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((25.0, 75.0), "min"), - "duration_bounds": ((380.0, 1140.0), "min"), - }, - "initial_guesses": {"time": ([50.0, 760.0], "min")}, - }, - "descent_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.75, "unitless"), - "final_mach": (0.3, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.77), "unitless"), - "initial_altitude": (28000.0, "ft"), - "final_altitude": (0.0, "ft"), - "altitude_bounds": ((0.0, 28500.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": False, - "constrain_final": True, - "fix_duration": False, - "initial_bounds": ((405.0, 1215.0), "min"), - "duration_bounds": ((12.5, 37.5), "min"), - }, - "initial_guesses": {"time": ([810.0, 25.0], "min")}, - }, "post_mission": { "include_landing": False, "constrain_range": True, - "target_range": (6771.56, "nmi"), + "target_range": (0.0, "nmi"), }, } diff --git a/singlemission.py b/singlemission.py index 4719db68c..b63687287 100644 --- a/singlemission.py +++ b/singlemission.py @@ -1,12 +1,56 @@ import aviary.api as av -from c5_ferry_phase_info import phase_info +import sys +from c5_ferry_phase_info import phase_info as c5_ferry_phase_info +from c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info +from c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info + + +def modify_plane(orig_filename, payloads, ranges): + if len(sys.argv) > 1: + plane_name = orig_filename.split(".csv")[0] + mission = sys.argv[1].lower() + temp_filename = f"{plane_name}_{mission}.csv" + with open(orig_filename, "r") as orig_plane: + orig_lines = orig_plane.readlines() + with open(temp_filename, "w") as temp_plane: + try: + payload, misrange = payloads[mission], ranges[mission] + except KeyError: + payload, misrange = "", "" + for line in orig_lines: + if "aircraft:crew_and_payload:cargo_mass" in line and payload != "": + line = ",".join( + [line.split(",")[0], + str(payload), + line.split(",")[2]]) + + elif "mission:design:range" in line and misrange != "": + line = ",".join( + [line.split(",")[0], + str(misrange), + line.split(",")[2]]) + + temp_plane.write(line) + else: + return orig_filename + return temp_filename, mission + if __name__ == '__main__': prob = av.AviaryProblem() + plane_file = 'c5.csv' + payloads = {"ferry": 0, "intermediate": 120e3, "maxpayload": 281e3} + ranges = {"ferry": 7e3, "intermediate": 4.8e3, "maxpayload": 2.15e3} + plane_file, mission_name = modify_plane(plane_file, payloads, ranges) + phase_info = c5_maxpayload_phase_info + if mission_name == "intermediate": + phase_info = c5_intermediate_phase_info + elif mission_name == "ferry": + phase_info = c5_ferry_phase_info # Load aircraft and options data from user # Allow for user overrides here - prob.load_inputs('c5.csv', phase_info) + prob.load_inputs(plane_file, phase_info) # Preprocess inputs prob.check_and_preprocess_inputs() @@ -20,7 +64,7 @@ # Link phases and variables prob.link_phases() - prob.add_driver("SLSQP", max_iter=100) + prob.add_driver("SLSQP", max_iter=50) prob.add_design_variables() @@ -33,15 +77,29 @@ prob.set_initial_guesses() # remove all plots and extras - prob.run_aviary_problem(record_filename='c5_ferry.db') + prob.run_aviary_problem(record_filename=f'{plane_file.split(".csv")[0]}.db') # prob.get_val() # look at final fuel burn + prob.get_val('mission.summary.fuel_burned') """ Ferry mission phase info: -Times (min): 0, 30, 810, 835 - Alt (ft): 0, 32000, 32000, 0 +Times (min): 0, 50, 812, 843 + Alt (ft): 0, 29500, 32000, 0 + Mach: 0.3, 0.77, 0.77, 0.3 +Est. Range: 7001 nmi +Notes: 32k in 30 mins too fast for aviary, climb to low alt then slow rise + +Intermediate mission phase info: +Times (min): 0, 50, 560, 590 + Alt (ft): 0, 29500, 32000, 0 + Mach: 0.3, 0.77, 0.77, 0.3 +Est. Range: 4839 nmi + +Max Payload mission phase info: +Times (min): 0, 50, 260, 290 + Alt (ft): 0, 29500, 32000, 0 Mach: 0.3, 0.77, 0.77, 0.3 -Notes: 32k in 30 mins too fast for aviary, +Est. Range: 2272 nmi Hard to find multiple payload/range values for FwFm (737), so use C-5 instead Based on: From 16034f49ae060a1795451732552ee14a91c921d8 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 24 Jul 2024 14:57:01 -0400 Subject: [PATCH 009/113] multiple missions optimize, but no affect on results yet --- multimission.py | 117 ++++++++++++++++++++++++----------------------- singlemission.py | 6 ++- 2 files changed, 63 insertions(+), 60 deletions(-) diff --git a/multimission.py b/multimission.py index 2524cf330..2e98144bc 100644 --- a/multimission.py +++ b/multimission.py @@ -1,5 +1,5 @@ """ -Goal: use single aircraft description but optimize it for multiple missions simultaneously, +Goal: use single aircraft description but optimize it for multiple missions simultaneously, i.e. all missions are on the range-payload line instead of having excess performance Aircraft csv: defines plane, but also defines payload (passengers, cargo) which can vary with mission These will have to be specified in some alternate way such as a list correspond to mission # @@ -14,65 +14,66 @@ planes = ['c5_maxpayload.csv', 'c5_intermediate.csv'] phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] +weights = [1, 1] +num_missions = len(weights) if __name__ == '__main__': super_prob = om.Problem() - prob1 = av.AviaryProblem() - prob2 = av.AviaryProblem() - - # Load aircraft and options data from user - # Allow for user overrides here - prob1.load_inputs(planes[0], phase_infos[0]) - prob2.load_inputs(planes[1], phase_infos[1]) - - # Preprocess inputs - prob1.check_and_preprocess_inputs() - prob2.check_and_preprocess_inputs() - - prob1.add_pre_mission_systems() - prob2.add_pre_mission_systems() - - prob1.add_phases() - prob2.add_phases() - - prob1.add_post_mission_systems() - prob2.add_post_mission_systems() - - # Link phases and variables - prob1.link_phases() - prob2.link_phases() - - super_prob.model.add_subsystem('prob1', prob1) - super_prob.model.add_subsystem('prob2', prob2) - super_prob.model.add_subsystem('compound', - om.ExecComp('compound = a + b'), - promotes=['compound', 'a', 'b']) - super_prob.model.connect('prob1.mission.design.gross_mass', 'a') - super_prob.model.connect('prob2.mission.design.gross_mass', 'b') - super_prob.model.connect('prob1.mission.design.gross_mass', - 'prob2.mission.design.gross_mass') - super_prob.add_driver("SLSQP", max_iter=100) - - # super_prob.add_parameter('mission.design.gross_mass') - - # use submodelcomp to instantiate both problems inside of the super problem - # https://openmdao.org/newdocs/versions/latest/features/building_blocks/components/submodel_comp.html?highlight=subproblem - # promote the correct inputs and outputs from the submodels - # add an execComp that sums the fuel burn output - - # Load optimization problem formulation - # Detail which variables the optimizer can control - super_prob.model.add_objective('compound') # output from execcomp goes here) + probs = [] + + # define individual aviary problems + for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): + prob = av.AviaryProblem() + prob.load_inputs(plane, phase_info) + prob.check_and_preprocess_inputs() + prob.add_pre_mission_systems() + prob.add_phases() + prob.add_post_mission_systems() + prob.link_phases() + probs.append(prob) + + subcomp = om.SubmodelComp(problem=prob, + inputs=['mission:design:gross_mass'], + outputs=['mission:summary:fuel_burned']) + super_prob.model.add_subsystem(f'subcomp_{i}', subcomp) + + # creating variable strings that will represent fuel burn from each mission + fuel_burned_vars = [f"fuel_{i}" for i in range(num_missions)] + weighted_str = "+".join([f"{fuel}*{weight}" + for fuel, weight in zip(fuel_burned_vars, weights)]) + # weighted_str looks like: fuel_0 * weight[0] + fuel_1 * weight[1] + + # adding compound execComp to super problem + super_prob.model.add_subsystem('compound', om.ExecComp( + "compound = "+weighted_str), promotes=["compound", *fuel_burned_vars]) + + # connecting each subcomponent's fuel burn to super problem's unique fuel variables + for i in range(num_missions): + super_prob.model.connect(f"subcomp_{i}.mission:summary:fuel_burned", f"fuel_{i}") + + # create an output within superprob that connects to each subcomponents gross mass input + IVC = super_prob.model.add_subsystem('IVC', om.IndepVarComp(), promotes=['*']) + IVC.add_output('gross_mass', val=500e3, units='lbm') + + # specify gross mass as a design var + super_prob.model.add_design_var('gross_mass', lower=100e3, upper=1000e3, units='lbm') + + # connect gross mass output of super problem to each subcomponent's input gross mass + for i in range(num_missions): + super_prob.model.connect('gross_mass', f"subcomp_{i}.mission:design:gross_mass") + + super_prob.driver = om.ScipyOptimizeDriver() + super_prob.driver.options['optimizer'] = 'SLSQP' + + super_prob.model.add_objective('compound') # output from execcomp goes here super_prob.setup() - prob1.set_initial_guesses() - prob2.set_initial_guesses() + # set initial guesses for each aviary problem + for prob in probs: + prob.set_initial_guesses() - # remove all plots and extras dm.run_problem(super_prob) - # super_prob.run_aviary_problem(record_filename='reserve_mission_fixedrange.db') - # super_prob.get_val() # look at final fuel burn """ @@ -81,7 +82,7 @@ Alt (ft): 0, 29500, 32000, 0 Mach: 0.3, 0.77, 0.77, 0.3 Est. Range: 7001 nmi -Notes: 32k in 30 mins too fast for aviary, climb to low alt then slow rise +Notes: 32k in 30 mins too fast for aviary, climb to low alt then slow rise Intermediate mission phase info: Times (min): 0, 50, 560, 590 @@ -96,9 +97,9 @@ Est. Range: 2272 nmi Hard to find multiple payload/range values for FwFm (737), so use C-5 instead -Based on: - https://en.wikipedia.org/wiki/Lockheed_C-5_Galaxy#Specifications_(C-5M), - https://www.af.mil/About-Us/Fact-Sheets/Display/Article/1529718/c-5-abc-galaxy-and-c-5m-super-galaxy/ +Based on: + https://en.wikipedia.org/wiki/Lockheed_C-5_Galaxy#Specifications_(C-5M), + https://www.af.mil/About-Us/Fact-Sheets/Display/Article/1529718/c-5-abc-galaxy-and-c-5m-super-galaxy/ MTOW: 840,000 lb Max Payload: 281,000 lb @@ -110,7 +111,7 @@ 120,000 lb payload -> 4,800 nmi range (AF.mil) [intermediate case] 0 lb payload -> 7,000 nmi range (AF.mil) [ferry case] -Flight characteristics: - Cruise at M0.77 at 33k ft +Flight characteristics: + Cruise at M0.77 at 33k ft Max rate of climb: 2100 ft/min """ diff --git a/singlemission.py b/singlemission.py index b63687287..bf5cd91b6 100644 --- a/singlemission.py +++ b/singlemission.py @@ -77,9 +77,11 @@ def modify_plane(orig_filename, payloads, ranges): prob.set_initial_guesses() # remove all plots and extras - prob.run_aviary_problem(record_filename=f'{plane_file.split(".csv")[0]}.db') + prob.run_aviary_problem( + record_filename=f'{plane_file.split(".csv")[0]}.db', suppress_solver_print=True) # prob.get_val() # look at final fuel burn - prob.get_val('mission.summary.fuel_burned') + print( + f"Fuel burned: {prob.get_val(av.Mission.Summary.FUEL_BURNED,units='lbm')[0]:.3f} lbm") """ Ferry mission phase info: From 754ab91657744593156298c901052d1c3c64d11f Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Thu, 25 Jul 2024 08:45:05 -0400 Subject: [PATCH 010/113] removed indepedentvarcomp to handle common inputs --- multimission.py | 19 ++++++++----------- 1 file changed, 8 insertions(+), 11 deletions(-) diff --git a/multimission.py b/multimission.py index 2e98144bc..e7d4c7d14 100644 --- a/multimission.py +++ b/multimission.py @@ -35,7 +35,10 @@ subcomp = om.SubmodelComp(problem=prob, inputs=['mission:design:gross_mass'], outputs=['mission:summary:fuel_burned']) - super_prob.model.add_subsystem(f'subcomp_{i}', subcomp) + # promoting gross mass to be used as a design var + # all problems have same name for gross mass so they are connected + super_prob.model.add_subsystem(f'subcomp_{i}', subcomp, promotes_inputs=[ + 'mission:design:gross_mass']) # creating variable strings that will represent fuel burn from each mission fuel_burned_vars = [f"fuel_{i}" for i in range(num_missions)] @@ -48,19 +51,13 @@ "compound = "+weighted_str), promotes=["compound", *fuel_burned_vars]) # connecting each subcomponent's fuel burn to super problem's unique fuel variables + # fuel_0, fuel_1, ... don't have units assigned, #TODO find a solution to specify units for i in range(num_missions): super_prob.model.connect(f"subcomp_{i}.mission:summary:fuel_burned", f"fuel_{i}") - # create an output within superprob that connects to each subcomponents gross mass input - IVC = super_prob.model.add_subsystem('IVC', om.IndepVarComp(), promotes=['*']) - IVC.add_output('gross_mass', val=500e3, units='lbm') - # specify gross mass as a design var - super_prob.model.add_design_var('gross_mass', lower=100e3, upper=1000e3, units='lbm') - - # connect gross mass output of super problem to each subcomponent's input gross mass - for i in range(num_missions): - super_prob.model.connect('gross_mass', f"subcomp_{i}.mission:design:gross_mass") + super_prob.model.add_design_var( + 'mission:design:gross_mass', lower=100e3, upper=1000e3, units='lbm') super_prob.driver = om.ScipyOptimizeDriver() super_prob.driver.options['optimizer'] = 'SLSQP' @@ -82,7 +79,7 @@ Alt (ft): 0, 29500, 32000, 0 Mach: 0.3, 0.77, 0.77, 0.3 Est. Range: 7001 nmi -Notes: 32k in 30 mins too fast for aviary, climb to low alt then slow rise +Notes: 32k in 30 mins too fast for aviary, climb to low alt then slow rise through cruise Intermediate mission phase info: Times (min): 0, 50, 560, 590 From 9c284ba12e4508ad903c0911d9d6f504f3a18d46 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Thu, 25 Jul 2024 15:09:05 -0400 Subject: [PATCH 011/113] attempt to import multiple missions as dymos trajectories for multi mission support --- aviary/interface/methods_for_level1.py | 9 +- aviary/interface/methods_for_level2.py | 334 +- cannonball_copy.py | 195 +- multi_mission_importTraj_N2.html | 14840 +++++++++++++++++++++++ multimission.py | 12 +- multitraj.py | 153 + 6 files changed, 15312 insertions(+), 231 deletions(-) create mode 100644 multi_mission_importTraj_N2.html create mode 100644 multitraj.py diff --git a/aviary/interface/methods_for_level1.py b/aviary/interface/methods_for_level1.py index 3cb1815d8..74ef2becf 100644 --- a/aviary/interface/methods_for_level1.py +++ b/aviary/interface/methods_for_level1.py @@ -94,7 +94,9 @@ def run_aviary(aircraft_filename, phase_info, optimizer=None, prob.set_initial_guesses() prob.failed = prob.run_aviary_problem( - record_filename, restart_filename=restart_filename, run_driver=run_driver, make_plots=make_plots, optimization_history_filename=optimization_history_filename) + record_filename, restart_filename=restart_filename, run_driver=run_driver, + make_plots=make_plots, + optimization_history_filename=optimization_history_filename) return prob @@ -149,9 +151,8 @@ def run_level_1( def _setup_level1_parser(parser): def_outdir = os.path.join(os.getcwd(), "output") - parser.add_argument( - 'input_deck', metavar='indeck', type=str, nargs=1, help='Name of vehicle input deck file' - ) + parser.add_argument('input_deck', metavar='indeck', type=str, + nargs=1, help='Name of vehicle input deck file') parser.add_argument( "-o", "--outdir", default=def_outdir, help="Directory to write outputs" ) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index b251abab1..6b324ae9c 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -240,7 +240,9 @@ def __init__(self, analysis_scheme=AnalysisScheme.COLLOCATION, **kwargs): self.regular_phases = [] self.reserve_phases = [] - def load_inputs(self, aviary_inputs, phase_info=None, engine_builders=None, meta_data=BaseMetaData, verbosity=None): + def load_inputs( + self, aviary_inputs, phase_info=None, engine_builders=None, + meta_data=BaseMetaData, verbosity=None): """ This method loads the aviary_values inputs and options that the user specifies. They could specify files to load and values to @@ -330,10 +332,14 @@ def load_inputs(self, aviary_inputs, phase_info=None, engine_builders=None, meta self.aviary_inputs = aviary_inputs if mission_method is TWO_DEGREES_OF_FREEDOM: - aviary_inputs.set_val(Mission.Summary.CRUISE_MASS_FINAL, - val=self.initial_guesses['cruise_mass_final'], units='lbm') - aviary_inputs.set_val(Mission.Summary.GROSS_MASS, - val=self.initial_guesses['actual_takeoff_mass'], units='lbm') + aviary_inputs.set_val( + Mission.Summary.CRUISE_MASS_FINAL, val=self.initial_guesses + ['cruise_mass_final'], + units='lbm') + aviary_inputs.set_val( + Mission.Summary.GROSS_MASS, val=self.initial_guesses + ['actual_takeoff_mass'], + units='lbm') # Commonly referenced values self.cruise_alt = aviary_inputs.get_val( @@ -350,8 +356,10 @@ def load_inputs(self, aviary_inputs, phase_info=None, engine_builders=None, meta elif mission_method is HEIGHT_ENERGY: self.problem_type = aviary_inputs.get_val(Settings.PROBLEM_TYPE) - aviary_inputs.set_val(Mission.Summary.GROSS_MASS, - val=self.initial_guesses['actual_takeoff_mass'], units='lbm') + aviary_inputs.set_val( + Mission.Summary.GROSS_MASS, val=self.initial_guesses + ['actual_takeoff_mass'], + units='lbm') if 'target_range' in self.post_mission_info: aviary_inputs.set_val(Mission.Design.RANGE, wrapped_convert_units( phase_info['post_mission']['target_range'], 'NM'), units='NM') @@ -429,7 +437,8 @@ def check_and_preprocess_inputs(self): for idx, phase_name in enumerate(self.phase_info): if 'user_options' in self.phase_info[phase_name]: if 'target_distance' in self.phase_info[phase_name]["user_options"]: - target_distance = self.phase_info[phase_name]["user_options"]["target_distance"] + target_distance = self.phase_info[phase_name]["user_options"][ + "target_distance"] if target_distance[0] <= 0: raise ValueError( f"Invalid target_distance in [{phase_name}].[user_options]. " @@ -443,16 +452,20 @@ def check_and_preprocess_inputs(self): if (self.analysis_scheme is AnalysisScheme.COLLOCATION) and (self.mission_method is EquationsOfMotion.TWO_DEGREES_OF_FREEDOM): try: # if the user provided an option, use it - analytic = self.phase_info[phase_name]["user_options"]['analytic'] + analytic = self.phase_info[phase_name]["user_options"][ + 'analytic'] except KeyError: # if it isn't specified, only the default 2DOF cruise for collocation is analytic if 'cruise' in phase_name: - analytic = self.phase_info[phase_name]["user_options"]['analytic'] = True + analytic = self.phase_info[phase_name]["user_options"][ + 'analytic'] = True else: - analytic = self.phase_info[phase_name]["user_options"]['analytic'] = False + analytic = self.phase_info[phase_name]["user_options"][ + 'analytic'] = False if 'target_duration' in self.phase_info[phase_name]["user_options"]: - target_duration = self.phase_info[phase_name]["user_options"]["target_duration"] + target_duration = self.phase_info[phase_name]["user_options"][ + "target_duration"] if target_duration[0] <= 0: raise ValueError( f"Invalid target_duration in phase_info[{phase_name}][user_options]. " @@ -463,8 +476,8 @@ def check_and_preprocess_inputs(self): # Set duration_bounds and initial_guesses for time: self.phase_info[phase_name]["user_options"].update({ "duration_bounds": ((target_duration[0], target_duration[0]), target_duration[1])}) - self.phase_info[phase_name].update({ - "initial_guesses": {"time": ((target_duration[0], target_duration[0]), target_duration[1])}}) + self.phase_info[phase_name].update({"initial_guesses": {"time": ( + (target_duration[0], target_duration[0]), target_duration[1])}}) # Set Fixed_duration to true: self.phase_info[phase_name]["user_options"].update({ "fix_duration": True}) @@ -571,8 +584,9 @@ def add_pre_mission_systems(self): # Propulsion isn't included in core pre-mission group to avoid override step in # configure() - instead add it now - pre_mission.add_subsystem('core_propulsion', - subsystems['propulsion'].build_pre_mission(self.aviary_inputs),) + pre_mission.add_subsystem( + 'core_propulsion', subsystems['propulsion'].build_pre_mission( + self.aviary_inputs),) default_subsystems = [subsystems['geometry'], subsystems['aerodynamics'], @@ -747,14 +761,16 @@ def _add_premission_external_subsystems(self): # Define the expression for computing the sum of masses expr = 'subsystem_mass = ' + ' + '.join(formatted_names) - promotes_inputs_list = [(formatted_name, original_name) - for formatted_name, original_name in zip(formatted_names, mass_names)] + promotes_inputs_list = [ + (formatted_name, original_name) for formatted_name, + original_name in zip(formatted_names, mass_names)] # Create the ExecComp - self.pre_mission.add_subsystem('external_comp_sum', om.ExecComp(expr, units='kg'), - promotes_inputs=promotes_inputs_list, - promotes_outputs=[ - ('subsystem_mass', Aircraft.Design.EXTERNAL_SUBSYSTEMS_MASS)]) + self.pre_mission.add_subsystem( + 'external_comp_sum', om.ExecComp(expr, units='kg'), + promotes_inputs=promotes_inputs_list, + promotes_outputs=[('subsystem_mass', Aircraft.Design. + EXTERNAL_SUBSYSTEMS_MASS)]) def _add_groundroll_eq_constraint(self, phase): """ @@ -842,7 +858,8 @@ def _get_phase(self, phase_name, phase_idx): phase_builder = TwoDOFPhase phase_object = phase_builder.from_phase_info( - phase_name, phase_options, default_mission_subsystems, meta_data=self.meta_data) + phase_name, phase_options, default_mission_subsystems, + meta_data=self.meta_data) phase = phase_object.build_phase(aviary_options=self.aviary_inputs) @@ -972,9 +989,8 @@ def _get_phase(self, phase_name, phase_idx): if 'cruise' not in phase_name and self.mission_method is TWO_DEGREES_OF_FREEDOM: phase.add_control( - Dynamic.Mission.THROTTLE, targets=Dynamic.Mission.THROTTLE, units='unitless', - opt=False, - ) + Dynamic.Mission.THROTTLE, targets=Dynamic.Mission.THROTTLE, + units='unitless', opt=False,) return phase @@ -993,9 +1009,8 @@ def add_phases(self, phase_info_parameterization=None): traj: The Dymos Trajectory object containing the added mission phases. """ if phase_info_parameterization is not None: - self.phase_info, self.post_mission_info = phase_info_parameterization(self.phase_info, - self.post_mission_info, - self.aviary_inputs) + self.phase_info, self.post_mission_info = phase_info_parameterization( + self.phase_info, self.post_mission_info, self.aviary_inputs) phase_info = self.phase_info @@ -1035,12 +1050,11 @@ def add_phases(self, phase_info_parameterization=None): ('altitude_initial', Mission.Design.CRUISE_ALTITUDE)]) self.model.add_subsystem( - 'actual_descent_fuel', - om.ExecComp('actual_descent_fuel = traj_cruise_mass_final - traj_mass_final', - actual_descent_fuel={'units': 'lbm'}, - traj_cruise_mass_final={'units': 'lbm'}, - traj_mass_final={'units': 'lbm'}, - )) + 'actual_descent_fuel', om.ExecComp( + 'actual_descent_fuel = traj_cruise_mass_final - traj_mass_final', + actual_descent_fuel={'units': 'lbm'}, + traj_cruise_mass_final={'units': 'lbm'}, + traj_mass_final={'units': 'lbm'},)) self.model.connect('start_of_descent_mass', 'traj.SGMCruise_mass_trigger') self.model.connect( @@ -1093,7 +1107,8 @@ def add_subsystem_timeseries_outputs(phase, phase_name): if self.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): traj = setup_trajectory_params( - self.model, traj, self.aviary_inputs, phases, meta_data=self.meta_data, external_parameters=external_parameters) + self.model, traj, self.aviary_inputs, phases, + meta_data=self.meta_data, external_parameters=external_parameters) self.traj = traj @@ -1158,8 +1173,9 @@ def add_post_mission_systems(self, include_landing=True): mass_final={'units': 'lbm'}, fuel_burned={'units': 'lbm'}) - self.post_mission.add_subsystem('fuel_burned', ecomp, - promotes=[('fuel_burned', Mission.Summary.FUEL_BURNED)]) + self.post_mission.add_subsystem( + 'fuel_burned', ecomp, + promotes=[('fuel_burned', Mission.Summary.FUEL_BURNED)]) if self.analysis_scheme is AnalysisScheme.SHOOTING: # shooting method currently doesn't have timeseries @@ -1187,22 +1203,25 @@ def add_post_mission_systems(self, include_landing=True): mass_final={'units': 'lbm'}, reserve_fuel_burned={'units': 'lbm'}) - self.post_mission.add_subsystem('reserve_fuel_burned', ecomp, - promotes=[('reserve_fuel_burned', Mission.Summary.RESERVE_FUEL_BURNED)]) + self.post_mission.add_subsystem('reserve_fuel_burned', ecomp, promotes=[ + ('reserve_fuel_burned', Mission.Summary.RESERVE_FUEL_BURNED)]) if self.analysis_scheme is AnalysisScheme.SHOOTING: # shooting method currently doesn't have timeseries self.post_mission.promotes('reserve_fuel_burned', [ ('initial_mass', Mission.Landing.TOUCHDOWN_MASS), ]) - self.model.connect(f"traj.{self.reserve_phases[-1]}.states:mass", - "reserve_fuel_burned.mass_final", src_indices=[-1]) + self.model.connect( + f"traj.{self.reserve_phases[-1]}.states:mass", + "reserve_fuel_burned.mass_final", src_indices=[-1]) else: # timeseries has to be used because Breguet cruise phases don't have states - self.model.connect(f"traj.{self.reserve_phases[0]}.timeseries.mass", - "reserve_fuel_burned.initial_mass", src_indices=[0]) - self.model.connect(f"traj.{self.reserve_phases[-1]}.timeseries.mass", - "reserve_fuel_burned.mass_final", src_indices=[-1]) + self.model.connect( + f"traj.{self.reserve_phases[0]}.timeseries.mass", + "reserve_fuel_burned.initial_mass", src_indices=[0]) + self.model.connect( + f"traj.{self.reserve_phases[-1]}.timeseries.mass", + "reserve_fuel_burned.mass_final", src_indices=[-1]) self._add_fuel_reserve_component() @@ -1229,22 +1248,24 @@ def add_post_mission_systems(self, include_landing=True): for phase_name in self.phase_info: if 'target_distance' in self.phase_info[phase_name]["user_options"]: target_distance = wrapped_convert_units( - self.phase_info[phase_name]["user_options"]["target_distance"], 'nmi') + self.phase_info[phase_name]["user_options"] + ["target_distance"], + 'nmi') self.post_mission.add_subsystem( - f"{phase_name}_distance_constraint", - om.ExecComp( + f"{phase_name}_distance_constraint", om.ExecComp( "distance_resid = target_distance - (final_distance - initial_distance)", distance_resid={'units': 'nmi'}, target_distance={'val': target_distance, 'units': 'nmi'}, final_distance={'units': 'nmi'}, - initial_distance={'units': 'nmi'}, - )) + initial_distance={'units': 'nmi'},)) self.model.connect( f"traj.{phase_name}.timeseries.distance", - f"{phase_name}_distance_constraint.final_distance", src_indices=[-1]) + f"{phase_name}_distance_constraint.final_distance", + src_indices=[-1]) self.model.connect( f"traj.{phase_name}.timeseries.distance", - f"{phase_name}_distance_constraint.initial_distance", src_indices=[0]) + f"{phase_name}_distance_constraint.initial_distance", + src_indices=[0]) self.model.add_constraint( f"{phase_name}_distance_constraint.distance_resid", equals=0.0, ref=1e2) @@ -1252,22 +1273,23 @@ def add_post_mission_systems(self, include_landing=True): if 'target_duration' in self.phase_info[phase_name]["user_options"] and \ self.phase_info[phase_name]["user_options"].get("analytic", False): target_duration = wrapped_convert_units( - self.phase_info[phase_name]["user_options"]["target_duration"], 'min') + self.phase_info[phase_name]["user_options"] + ["target_duration"], + 'min') self.post_mission.add_subsystem( - f"{phase_name}_duration_constraint", - om.ExecComp( + f"{phase_name}_duration_constraint", om.ExecComp( "duration_resid = target_duration - (final_time - initial_time)", duration_resid={'units': 'min'}, target_duration={'val': target_duration, 'units': 'min'}, final_time={'units': 'min'}, - initial_time={'units': 'min'}, - )) + initial_time={'units': 'min'},)) self.model.connect( f"traj.{phase_name}.timeseries.time", f"{phase_name}_duration_constraint.final_time", src_indices=[-1]) self.model.connect( f"traj.{phase_name}.timeseries.time", - f"{phase_name}_duration_constraint.initial_time", src_indices=[0]) + f"{phase_name}_duration_constraint.initial_time", + src_indices=[0]) self.model.add_constraint( f"{phase_name}_duration_constraint.duration_resid", equals=0.0, ref=1e2) @@ -1424,7 +1446,8 @@ def link_phases(self): elif self.mission_method is SOLVED_2DOF: self.traj.link_phases(phases, [Dynamic.Mission.MASS], connected=True) self.traj.link_phases( - phases, [Dynamic.Mission.DISTANCE], units='ft', ref=1.e3, connected=False) + phases, [Dynamic.Mission.DISTANCE], + units='ft', ref=1.e3, connected=False) self.traj.link_phases(phases, ["time"], connected=False) if len(phases) > 2: @@ -1457,7 +1480,10 @@ def link_phases(self): # if either phase is rotation, we need to connect velocity # ascent to accel also requires velocity - if 'rotation' in (phase1, phase2) or ('ascent', 'accel') == (phase1, phase2): + if 'rotation' in ( + phase1, phase2) or ( + 'ascent', 'accel') == ( + phase1, phase2): states_to_link[Dynamic.Mission.VELOCITY] = true_unless_mpi # if the first phase is rotation, we also need alpha if phase1 == 'rotation': @@ -1490,7 +1516,8 @@ def link_phases(self): self.traj.add_linkage_constraint( phase1, phase2, 'time', prefix+'time', connected=True) self.traj.add_linkage_constraint( - phase1, phase2, 'distance', prefix+'distance', connected=True) + phase1, phase2, 'distance', prefix + 'distance', + connected=True) self.traj.add_linkage_constraint( phase1, phase2, 'mass', 'mass', connected=False, ref=1.0e5) @@ -1569,7 +1596,9 @@ def connect_with_common_params(self, source, target): for source, target in connect_map.items(): connect_with_common_params(self, source, target) - def add_driver(self, optimizer=None, use_coloring=None, max_iter=50, verbosity=Verbosity.BRIEF): + def add_driver( + self, optimizer=None, use_coloring=None, max_iter=50, + verbosity=Verbosity.BRIEF): """ Add an optimization driver to the Aviary problem. @@ -1755,8 +1784,8 @@ def add_design_variables(self): elif self.problem_type is ProblemType.ALTERNATE: self.model.add_design_var( Mission.Summary.GROSS_MASS, - lower=0, - upper=None, + lower=10., + upper=900e3, units='lbm', ref=175e3, ) @@ -1821,7 +1850,8 @@ def add_objective(self, objective_type=None, ref=None): if objective_type == 'mass': if self.analysis_scheme is AnalysisScheme.COLLOCATION: self.model.add_objective( - f"traj.{final_phase_name}.timeseries.{Dynamic.Mission.MASS}", index=-1, ref=ref) + f"traj.{final_phase_name}.timeseries.{Dynamic.Mission.MASS}", + index=-1, ref=ref) else: last_phase = self.traj._phases.items()[final_phase_name] last_phase.add_objective( @@ -1837,8 +1867,9 @@ def add_objective(self, objective_type=None, ref=None): elif objective_type == "fuel": self.model.add_objective(Mission.Objectives.FUEL, ref=ref) else: - raise ValueError(f"{objective_type} is not a valid objective.\nobjective_type must" - " be one of mass, time, hybrid_objective, fuel_burned, or fuel") + raise ValueError( + f"{objective_type} is not a valid objective.\nobjective_type must" + " be one of mass, time, hybrid_objective, fuel_burned, or fuel") else: # If no 'objective_type' is specified, we handle based on 'problem_type' # If 'ref' is not specified, assign a default value @@ -1891,25 +1922,32 @@ def _add_bus_variables_and_connect(self): for phase_name in phases: phase = getattr(self.traj.phases, phase_name) - phase.add_parameter(mission_var_name, opt=False, static_target=True, - units=base_units, shape=shape, targets=targets) + phase.add_parameter( + mission_var_name, opt=False, + static_target=True, units=base_units, + shape=shape, targets=targets) - self.model.connect(f'pre_mission.{bus_variable}', - f'traj.{phase_name}.parameters:{mission_var_name}') + self.model.connect( + f'pre_mission.{bus_variable}', + f'traj.{phase_name}.parameters:{mission_var_name}') else: phases = base_phases - self.traj.add_parameter(mission_var_name, opt=False, static_target=True, - units=base_units, shape=shape, targets={ - phase_name: [mission_var_name] for phase_name in phases}) + self.traj.add_parameter( + mission_var_name, opt=False, static_target=True, + units=base_units, shape=shape, + targets={phase_name: [mission_var_name] + for phase_name in phases}) self.model.connect( - f'pre_mission.{bus_variable}', f'traj.parameters:'+mission_var_name) + f'pre_mission.{bus_variable}', + f'traj.parameters:' + mission_var_name) if 'post_mission_name' in bus_variables[bus_variable]: - self.model.connect(f'pre_mission.{external_subsystem.name}.{bus_variable}', - f'post_mission.{external_subsystem.name}.{bus_variables[bus_variable]["post_mission_name"]}') + self.model.connect( + f'pre_mission.{external_subsystem.name}.{bus_variable}', + f'post_mission.{external_subsystem.name}.{bus_variables[bus_variable]["post_mission_name"]}') def setup(self, **kwargs): """ @@ -2127,8 +2165,8 @@ def _add_guesses(self, phase_name, phase, guesses): state_keys = ["mass", Dynamic.Mission.DISTANCE] else: control_keys = ["velocity_rate", "throttle"] - state_keys = ["altitude", "mass", - Dynamic.Mission.DISTANCE, Dynamic.Mission.VELOCITY, "flight_path_angle", "alpha"] + state_keys = ["altitude", "mass", Dynamic.Mission.DISTANCE, + Dynamic.Mission.VELOCITY, "flight_path_angle", "alpha"] if self.mission_method is TWO_DEGREES_OF_FREEDOM and phase_name == 'ascent': # Alpha is a control for ascent. control_keys.append('alpha') @@ -2159,8 +2197,10 @@ def _add_guesses(self, phase_name, phase, guesses): # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds if 'time' not in guesses: - initial_bounds = self.phase_info[phase_name]['user_options']['initial_bounds'] - duration_bounds = self.phase_info[phase_name]['user_options']['duration_bounds'] + initial_bounds = self.phase_info[phase_name]['user_options'][ + 'initial_bounds'] + duration_bounds = self.phase_info[phase_name]['user_options'][ + 'duration_bounds'] # Add a check for the initial and duration bounds, raise an error if they are not consistent if initial_bounds[1] != duration_bounds[1]: raise ValueError( @@ -2186,11 +2226,17 @@ def _add_guesses(self, phase_name, phase, guesses): val, guess_key, phase), units=units) except KeyError: try: - self.set_val(f'traj.{phase_name}.polynomial_controls:{guess_key}', self._process_guess_var( - val, guess_key, phase), units=units) + self.set_val( + f'traj.{phase_name}.polynomial_controls:{guess_key}', + self._process_guess_var( + val, guess_key, phase), + units=units) except KeyError: - self.set_val(f'traj.{phase_name}.bspline_controls:{guess_key}', self._process_guess_var( - val, guess_key, phase), units=units) + self.set_val( + f'traj.{phase_name}.bspline_controls:{guess_key}', + self._process_guess_var( + val, guess_key, phase), + units=units) if self.mission_method is SOLVED_2DOF: continue @@ -2204,8 +2250,10 @@ def _add_guesses(self, phase_name, phase, guesses): elif guess_key in prob_keys: self.set_val(guess_key, val, units=units) elif ":" in guess_key: - self.set_val(f'traj.{phase_name}.{guess_key}', self._process_guess_var( - val, guess_key, phase), units=units) + self.set_val( + f'traj.{phase_name}.{guess_key}', self._process_guess_var( + val, guess_key, phase), + units=units) else: # raise error if the guess key is not recognized raise ValueError( @@ -2265,10 +2313,10 @@ def _add_guesses(self, phase_name, phase, guesses): Dynamic.Mission.DISTANCE, ys=ys) ) - def run_aviary_problem(self, - record_filename="problem_history.db", - optimization_history_filename=None, - restart_filename=None, suppress_solver_print=True, run_driver=True, simulate=False, make_plots=True): + def run_aviary_problem(self, record_filename="problem_history.db", + optimization_history_filename=None, restart_filename=None, + suppress_solver_print=True, run_driver=True, simulate=False, + make_plots=True): """ This function actually runs the Aviary problem, which could be a simulation, optimization, or a driver execution, depending on the arguments provided. @@ -2304,8 +2352,9 @@ def run_aviary_problem(self, # and run mission, and dynamics if run_driver: - failed = dm.run_problem(self, run_driver=run_driver, simulate=simulate, make_plots=make_plots, - solution_record_file=record_filename, restart=restart_filename) + failed = dm.run_problem( + self, run_driver=run_driver, simulate=simulate, make_plots=make_plots, + solution_record_file=record_filename, restart=restart_filename) else: # prevent UserWarning that is displayed when an event is triggered warnings.filterwarnings('ignore', category=UserWarning) @@ -2339,12 +2388,14 @@ def _add_vrotate_comp(self): 'vrot_comp.mass', src_indices=om.slicer[0, ...]) vrot_eq_comp = self.model.add_subsystem("vrot_eq_comp", om.EQConstraintComp()) - vrot_eq_comp.add_eq_output("v_rotate_error", eq_units="kn", - lhs_name="v_rot_computed", rhs_name="groundroll_v_final", add_constraint=True) + vrot_eq_comp.add_eq_output( + "v_rotate_error", eq_units="kn", lhs_name="v_rot_computed", + rhs_name="groundroll_v_final", add_constraint=True) self.model.connect('vrot_comp.Vrot', 'vrot_eq_comp.v_rot_computed') - self.model.connect('traj.groundroll.timeseries.velocity', - 'vrot_eq_comp.groundroll_v_final', src_indices=om.slicer[-1, ...]) + self.model.connect( + 'traj.groundroll.timeseries.velocity', 'vrot_eq_comp.groundroll_v_final', + src_indices=om.slicer[-1, ...]) def _save_to_csv_file(self, filename): with open(filename, 'w', newline='') as csvfile: @@ -2382,7 +2433,8 @@ def _add_height_energy_landing_systems(self): last_flight_phase_name = list(self.phase_info.keys())[-1] control_type_string = 'control_values' - if self.phase_info[last_flight_phase_name]['user_options'].get('use_polynomial_control', True): + if self.phase_info[last_flight_phase_name]['user_options'].get( + 'use_polynomial_control', True): if not use_new_dymos_syntax: control_type_string = 'polynomial_control_values' @@ -2395,8 +2447,8 @@ def _add_height_energy_landing_systems(self): def _add_post_mission_takeoff_systems(self): first_flight_phase_name = list(self.phase_info.keys())[0] - connect_takeoff_to_climb = not self.phase_info[first_flight_phase_name]['user_options'].get( - 'add_initial_mass_constraint', True) + connect_takeoff_to_climb = not self.phase_info[first_flight_phase_name][ + 'user_options'].get('add_initial_mass_constraint', True) if connect_takeoff_to_climb: self.model.connect(Mission.Takeoff.FINAL_MASS, @@ -2405,11 +2457,13 @@ def _add_post_mission_takeoff_systems(self): f'traj.{first_flight_phase_name}.initial_states:distance') control_type_string = 'control_values' - if self.phase_info[first_flight_phase_name]['user_options'].get('use_polynomial_control', True): + if self.phase_info[first_flight_phase_name]['user_options'].get( + 'use_polynomial_control', True): if not use_new_dymos_syntax: control_type_string = 'polynomial_control_values' - if self.phase_info[first_flight_phase_name]['user_options'].get('optimize_mach', False): + if self.phase_info[first_flight_phase_name]['user_options'].get( + 'optimize_mach', False): # Create an ExecComp to compute the difference in mach mach_diff_comp = om.ExecComp( 'mach_resid_for_connecting_takeoff = final_mach - initial_mach') @@ -2418,23 +2472,27 @@ def _add_post_mission_takeoff_systems(self): # Connect the inputs to the mach difference component self.model.connect(Mission.Takeoff.FINAL_MACH, 'mach_diff_comp.final_mach') - self.model.connect(f'traj.{first_flight_phase_name}.{control_type_string}:mach', - 'mach_diff_comp.initial_mach', src_indices=[0]) + self.model.connect( + f'traj.{first_flight_phase_name}.{control_type_string}:mach', + 'mach_diff_comp.initial_mach', src_indices=[0]) # Add constraint for mach difference self.model.add_constraint( 'mach_diff_comp.mach_resid_for_connecting_takeoff', equals=0.0) - if self.phase_info[first_flight_phase_name]['user_options'].get('optimize_altitude', False): + if self.phase_info[first_flight_phase_name]['user_options'].get( + 'optimize_altitude', False): # Similar steps for altitude difference alt_diff_comp = om.ExecComp( - 'altitude_resid_for_connecting_takeoff = final_altitude - initial_altitude', units='ft') + 'altitude_resid_for_connecting_takeoff = final_altitude - initial_altitude', + units='ft') self.model.add_subsystem('alt_diff_comp', alt_diff_comp) self.model.connect(Mission.Takeoff.FINAL_ALTITUDE, 'alt_diff_comp.final_altitude') - self.model.connect(f'traj.{first_flight_phase_name}.{control_type_string}:altitude', - 'alt_diff_comp.initial_altitude', src_indices=[0]) + self.model.connect( + f'traj.{first_flight_phase_name}.{control_type_string}:altitude', + 'alt_diff_comp.initial_altitude', src_indices=[0]) self.model.add_constraint( 'alt_diff_comp.altitude_resid_for_connecting_takeoff', equals=0.0) @@ -2507,34 +2565,36 @@ def _add_fuel_reserve_component(self, post_mission=True, RESERVE_FUEL_FRACTION = self.aviary_inputs.get_val( Aircraft.Design.RESERVE_FUEL_FRACTION, units='unitless') if RESERVE_FUEL_FRACTION != 0: - reserve_fuel_frac = om.ExecComp('reserve_fuel_frac_mass = reserve_fuel_fraction * (takeoff_mass - final_mass)', - reserve_fuel_frac_mass={"units": "lbm"}, - reserve_fuel_fraction={ - "units": "unitless", "val": RESERVE_FUEL_FRACTION}, - final_mass={"units": "lbm"}, - takeoff_mass={"units": "lbm"}) - - reserve_calc_location.add_subsystem("reserve_fuel_frac", reserve_fuel_frac, - promotes_inputs=[("takeoff_mass", Mission.Summary.GROSS_MASS), - ("final_mass", - Mission.Landing.TOUCHDOWN_MASS), - ("reserve_fuel_fraction", Aircraft.Design.RESERVE_FUEL_FRACTION)], - promotes_outputs=["reserve_fuel_frac_mass"]) + reserve_fuel_frac = om.ExecComp( + 'reserve_fuel_frac_mass = reserve_fuel_fraction * (takeoff_mass - final_mass)', + reserve_fuel_frac_mass={"units": "lbm"}, + reserve_fuel_fraction={"units": "unitless", + "val": RESERVE_FUEL_FRACTION}, + final_mass={"units": "lbm"}, + takeoff_mass={"units": "lbm"}) + + reserve_calc_location.add_subsystem( + "reserve_fuel_frac", reserve_fuel_frac, + promotes_inputs=[("takeoff_mass", Mission.Summary.GROSS_MASS), + ("final_mass", Mission.Landing.TOUCHDOWN_MASS), + ("reserve_fuel_fraction", Aircraft.Design. + RESERVE_FUEL_FRACTION)], + promotes_outputs=["reserve_fuel_frac_mass"]) RESERVE_FUEL_ADDITIONAL = self.aviary_inputs.get_val( Aircraft.Design.RESERVE_FUEL_ADDITIONAL, units='lbm') - reserve_fuel = om.ExecComp('reserve_fuel = reserve_fuel_frac_mass + reserve_fuel_additional + reserve_fuel_burned', - reserve_fuel={"units": "lbm", 'shape': 1}, - reserve_fuel_frac_mass={"units": "lbm", "val": 0}, - reserve_fuel_additional={ - "units": "lbm", "val": RESERVE_FUEL_ADDITIONAL}, - reserve_fuel_burned={"units": "lbm", "val": 0}) - - reserve_calc_location.add_subsystem("reserve_fuel", reserve_fuel, - promotes_inputs=["reserve_fuel_frac_mass", - ("reserve_fuel_additional", - Aircraft.Design.RESERVE_FUEL_ADDITIONAL), - ("reserve_fuel_burned", Mission.Summary.RESERVE_FUEL_BURNED)], - promotes_outputs=[ - ("reserve_fuel", reserves_name)] - ) + reserve_fuel = om.ExecComp( + 'reserve_fuel = reserve_fuel_frac_mass + reserve_fuel_additional + reserve_fuel_burned', + reserve_fuel={"units": "lbm", 'shape': 1}, + reserve_fuel_frac_mass={"units": "lbm", "val": 0}, + reserve_fuel_additional={"units": "lbm", "val": RESERVE_FUEL_ADDITIONAL}, + reserve_fuel_burned={"units": "lbm", "val": 0}) + + reserve_calc_location.add_subsystem( + "reserve_fuel", reserve_fuel, + promotes_inputs=["reserve_fuel_frac_mass", + ("reserve_fuel_additional", Aircraft.Design. + RESERVE_FUEL_ADDITIONAL), + ("reserve_fuel_burned", + Mission.Summary.RESERVE_FUEL_BURNED)], + promotes_outputs=[("reserve_fuel", reserves_name)]) diff --git a/cannonball_copy.py b/cannonball_copy.py index 2124345ec..9f1d81303 100644 --- a/cannonball_copy.py +++ b/cannonball_copy.py @@ -17,7 +17,6 @@ Could also add a "fuel" parameter which can then be minimized. """ -# Working version class CannonballSizing(om.ExplicitComponent): @@ -119,6 +118,7 @@ def compute(self, inputs, outputs): outputs['ke'] = 0.5*m*v**2 +# ODEs are unique to each traj created def createTrajectory(ke_max): traj = dm.Trajectory() transcription = dm.Radau(num_segments=5, order=3, compressed=True) @@ -142,7 +142,7 @@ def createTrajectory(ke_max): phase.add_parameter('price', units='USD', static_target=True, val=10) phase.add_parameter('CD', units=None, static_target=True, val=0.5) - descent.add_objective('r', loc='final', scaler=-1.0) # negative means to maximize + # descent.add_objective('r', loc='final', scaler=-1.0) # negative means to maximize for param in ('CD', 'm', 'S', 'price'): traj.add_parameter(param, static_target=True) @@ -160,28 +160,43 @@ def createTrajectory(ke_max): p.driver.options['optimizer'] = 'SLSQP' p.driver.declare_coloring() -p.model.add_subsystem('size_comp', CannonballSizing(), +kes = [4e5, 5e5, 6e5] +# 2:1 ratio (or 1:2) causes results that essentially don't optimize the 1 mission, +# 1.01 works, 1.009 doesn't +# 2:1:1 works?! - may be related some normalization/bounds issue +weights = [2.1, 1.5, 1.1] +num_trajs = len(kes) + +p.model.add_subsystem(f"sizing_comp", CannonballSizing(), promotes_inputs=['radius', 'dens']) + p.model.set_input_defaults('dens', val=7.87, units='g/cm**3') p.model.add_design_var('radius', lower=0.01, upper=0.10, ref0=0.01, ref=0.10, units='m') -kes = [4e5, 5e5] trajs, ascents, descents = [], [], [] -for ke in kes: - a, b, c = createTrajectory(ke) - trajs.append(a) - ascents.append(b) - descents.append(c) -# traj, ascent, descent = createTrajectory(4e5) -p.model.add_subsystem('traj', trajs[1]) -ascent = ascents[1] -descent = descents[1] - -# Issue Connections -p.model.connect('size_comp.mass', 'traj.parameters:m') -p.model.connect('size_comp.price', 'traj.parameters:price') -p.model.connect('size_comp.S', 'traj.parameters:S') +for i, ke in enumerate(kes): + traj, ascent, descent = createTrajectory(ke) + p.model.add_subsystem(f"traj_{i}", traj) + + # Issue Connections + p.model.connect(f"sizing_comp.mass", f"traj_{i}.parameters:m") + p.model.connect(f"sizing_comp.S", f"traj_{i}.parameters:S") + p.model.connect(f"sizing_comp.price", f"traj_{i}.parameters:price") + trajs.append(traj) + ascents.append(ascent) + descents.append(descent) + +ranges = [f"r{i}" for i in range(num_trajs)] +weighted_sum_str = "+".join([f"{weight}*{r}" for r, weight in zip(ranges, weights)]) +p.model.add_subsystem('compoundComp', om.ExecComp("compound_range="+weighted_sum_str), + promotes=['compound_range', *ranges]) + +for i in range(num_trajs): + p.model.connect(f"traj_{i}.descent.states:r", ranges[i], src_indices=-1) + +p.model.add_objective('compound_range', scaler=-1) + # A linear solver at the top level can improve performance. p.model.linear_solver = om.DirectSolver() @@ -190,23 +205,25 @@ def createTrajectory(ke_max): p.set_val('radius', 0.05, units='m') p.set_val('dens', 7.87, units='g/cm**3') -p.set_val('traj.parameters:CD', 0.5) +for i, (ascent, descent) in enumerate(zip(ascents, descents)): + p.set_val(f"traj_{i}.parameters:CD", 0.5) -p.set_val('traj.ascent.t_initial', 0.0) -p.set_val('traj.ascent.t_duration', 10.0) -# list is initial and final, based on phase info some are fixed others are not -p.set_val('traj.ascent.states:r', ascent.interp('r', [0, 100])) -p.set_val('traj.ascent.states:h', ascent.interp('h', [0, 100])) -p.set_val('traj.ascent.states:v', ascent.interp('v', [200, 150])) -p.set_val('traj.ascent.states:gam', ascent.interp('gam', [25, 0]), units='deg') + p.set_val(f"traj_{i}.ascent.t_initial", 0.0) + p.set_val(f"traj_{i}.ascent.t_duration", 10.0) + # list is initial and final, based on phase info some are fixed others are not + p.set_val(f"traj_{i}.ascent.states:r", ascent.interp('r', [0, 100])) + p.set_val(f'traj_{i}.ascent.states:h', ascent.interp('h', [0, 100])) + p.set_val(f'traj_{i}.ascent.states:v', ascent.interp('v', [200, 150])) + p.set_val(f'traj_{i}.ascent.states:gam', ascent.interp('gam', [25, 0]), units='deg') -p.set_val('traj.descent.t_initial', 10.0) -p.set_val('traj.descent.t_duration', 10.0) + p.set_val(f'traj_{i}.descent.t_initial', 10.0) + p.set_val(f'traj_{i}.descent.t_duration', 10.0) -p.set_val('traj.descent.states:r', descent.interp('r', [100, 200])) -p.set_val('traj.descent.states:h', descent.interp('h', [100, 0])) -p.set_val('traj.descent.states:v', descent.interp('v', [150, 200])) -p.set_val('traj.descent.states:gam', descent.interp('gam', [0, -45]), units='deg') + p.set_val(f'traj_{i}.descent.states:r', descent.interp('r', [100, 200])) + p.set_val(f'traj_{i}.descent.states:h', descent.interp('h', [100, 0])) + p.set_val(f'traj_{i}.descent.states:v', descent.interp('v', [150, 200])) + p.set_val(f'traj_{i}.descent.states:gam', + descent.interp('gam', [0, -45]), units='deg') dm.run_problem(p, simulate=True) @@ -215,60 +232,66 @@ def createTrajectory(ke_max): def plotstuff(): - rad = p.get_val('radius', units='m')[0] - print(f'optimal radius: {rad} m ') - mass = p.get_val('size_comp.mass', units='kg')[0] - print(f'cannonball mass: {mass} kg ') - price = p.get_val('size_comp.price', units='USD')[0] - print(f'cannonball price: ${price:.2f}') - area = p.get_val('size_comp.S', units='cm**2')[0] - print(f'cannonball aerodynamic reference area: {area} cm**2 ') - angle = p.get_val('traj.ascent.timeseries.gam', units='deg')[0, 0] - print(f'launch angle: {angle} deg') - max_range = p.get_val('traj.descent.timeseries.r')[-1, 0] - print(f'maximum range: {max_range} m') - - fig, axes = plt.subplots(nrows=1, ncols=1, figsize=(10, 6)) - time_imp = {'ascent': p.get_val('traj.ascent.timeseries.time'), - 'descent': p.get_val('traj.descent.timeseries.time')} - time_exp = {'ascent': sim.get_val('traj.ascent.timeseries.time'), - 'descent': sim.get_val('traj.descent.timeseries.time')} - r_imp = {'ascent': p.get_val('traj.ascent.timeseries.r'), - 'descent': p.get_val('traj.descent.timeseries.r')} - r_exp = {'ascent': sim.get_val('traj.ascent.timeseries.r'), - 'descent': sim.get_val('traj.descent.timeseries.r')} - h_imp = {'ascent': p.get_val('traj.ascent.timeseries.h'), - 'descent': p.get_val('traj.descent.timeseries.h')} - h_exp = {'ascent': sim.get_val('traj.ascent.timeseries.h'), - 'descent': sim.get_val('traj.descent.timeseries.h')} - - axes.plot(r_imp['ascent'], h_imp['ascent'], 'bo') - axes.plot(r_imp['descent'], h_imp['descent'], 'ro') - axes.plot(r_exp['ascent'], h_exp['ascent'], 'b--') - axes.plot(r_exp['descent'], h_exp['descent'], 'r--') - - axes.set_xlabel('range (m)') - axes.set_ylabel('altitude (m)') - axes.grid(True) - - fig, axes = plt.subplots(nrows=4, ncols=1, figsize=(10, 6)) - states = ['r', 'h', 'v', 'gam'] - for i, state in enumerate(states): - x_imp = {'ascent': sol.get_val(f'traj.ascent.timeseries.{state}'), - 'descent': sol.get_val(f'traj.descent.timeseries.{state}')} - - x_exp = {'ascent': sim.get_val(f'traj.ascent.timeseries.{state}'), - 'descent': sim.get_val(f'traj.descent.timeseries.{state}')} - - axes[i].set_ylabel(state) - axes[i].grid(True) - - axes[i].plot(time_imp['ascent'], x_imp['ascent'], 'bo') - axes[i].plot(time_imp['descent'], x_imp['descent'], 'ro') - axes[i].plot(time_exp['ascent'], x_exp['ascent'], 'b--') - axes[i].plot(time_exp['descent'], x_exp['descent'], 'r--') - - plt.show() + print("\n\n=================================================") + print( + f"Optimized {num_trajs} trajectories with weights: {', '.join(map(str,weights))}") + rad = p.get_val('radius', units='cm')[0] + mass = p.get_val('sizing_comp.mass', units='kg')[0] + price = p.get_val('sizing_comp.price', units='USD')[0] + area = p.get_val('sizing_comp.S', units='cm**2')[0] + print("\nOptimal Cannonball Description:") + print( + f"\tRadius: {rad:.2f} cm, Mass: {mass:.2f} kg, Price: ${price:.2f}, Area: {area:.2f} sqcm") + + print("\nOptimal Trajectory Descriptions:") + for i, ke in enumerate(kes): + angle = p.get_val(f'traj_{i}.ascent.timeseries.gam', units='deg')[0, 0] + max_range = p.get_val(f'traj_{i}.descent.timeseries.r')[-1, 0] + + print( + f"\tKE: {ke/1e3:.2f} KJ, Launch Angle: {angle:.2f} deg, Max Range: {max_range:.2f} m") + + # fig, axes = plt.subplots(nrows=1, ncols=1, figsize=(10, 6)) + # time_imp = {'ascent': p.get_val('traj_0.ascent.timeseries.time'), + # 'descent': p.get_val('traj_0.descent.timeseries.time')} + # time_exp = {'ascent': sim.get_val('traj_0.ascent.timeseries.time'), + # 'descent': sim.get_val('traj_0.descent.timeseries.time')} + # r_imp = {'ascent': p.get_val('traj_0.ascent.timeseries.r'), + # 'descent': p.get_val('traj_0.descent.timeseries.r')} + # r_exp = {'ascent': sim.get_val('traj_0.ascent.timeseries.r'), + # 'descent': sim.get_val('traj_0.descent.timeseries.r')} + # h_imp = {'ascent': p.get_val('traj_0.ascent.timeseries.h'), + # 'descent': p.get_val('traj_0.descent.timeseries.h')} + # h_exp = {'ascent': sim.get_val('traj_0.ascent.timeseries.h'), + # 'descent': sim.get_val('traj_0.descent.timeseries.h')} + + # axes.plot(r_imp['ascent'], h_imp['ascent'], 'bo') + # axes.plot(r_imp['descent'], h_imp['descent'], 'ro') + # axes.plot(r_exp['ascent'], h_exp['ascent'], 'b--') + # axes.plot(r_exp['descent'], h_exp['descent'], 'r--') + + # axes.set_xlabel('range (m)') + # axes.set_ylabel('altitude (m)') + # axes.grid(True) + + # fig, axes = plt.subplots(nrows=4, ncols=1, figsize=(10, 6)) + # states = ['r', 'h', 'v', 'gam'] + # for i, state in enumerate(states): + # x_imp = {'ascent': sol.get_val(f'traj_0.ascent.timeseries.{state}'), + # 'descent': sol.get_val(f'traj_0.descent.timeseries.{state}')} + + # x_exp = {'ascent': sim.get_val(f'traj_0.ascent.timeseries.{state}'), + # 'descent': sim.get_val(f'traj_0.descent.timeseries.{state}')} + + # axes[i].set_ylabel(state) + # axes[i].grid(True) + + # axes[i].plot(time_imp['ascent'], x_imp['ascent'], 'bo') + # axes[i].plot(time_imp['descent'], x_imp['descent'], 'ro') + # axes[i].plot(time_exp['ascent'], x_exp['ascent'], 'b--') + # axes[i].plot(time_exp['descent'], x_exp['descent'], 'r--') + + # plt.show() plotstuff() diff --git a/multi_mission_importTraj_N2.html b/multi_mission_importTraj_N2.html new file mode 100644 index 000000000..c1b62f22d --- /dev/null +++ b/multi_mission_importTraj_N2.html @@ -0,0 +1,14840 @@ + + + +OpenMDAO Model Hierarchy and N2 diagram + + + + + + + + + + + + + + + + + +
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+ + + + + + + diff --git a/multimission.py b/multimission.py index e7d4c7d14..c5da0f2b2 100644 --- a/multimission.py +++ b/multimission.py @@ -32,13 +32,13 @@ prob.link_phases() probs.append(prob) - subcomp = om.SubmodelComp(problem=prob, - inputs=['mission:design:gross_mass'], - outputs=['mission:summary:fuel_burned']) + subcomp = om.SubmodelComp( + problem=prob, inputs=['mission:design:gross_mass', 'aircraft:wing:span'], + outputs=['mission:summary:fuel_burned']) # promoting gross mass to be used as a design var # all problems have same name for gross mass so they are connected super_prob.model.add_subsystem(f'subcomp_{i}', subcomp, promotes_inputs=[ - 'mission:design:gross_mass']) + 'mission:design:gross_mass', 'aircraft:wing:span']) # creating variable strings that will represent fuel burn from each mission fuel_burned_vars = [f"fuel_{i}" for i in range(num_missions)] @@ -59,6 +59,10 @@ super_prob.model.add_design_var( 'mission:design:gross_mass', lower=100e3, upper=1000e3, units='lbm') + # this throws error: output not found for this design var + # super_prob.model.add_design_var( + # 'aircraft:design:span', lower=100., upper=300., units='ft') + super_prob.driver = om.ScipyOptimizeDriver() super_prob.driver.options['optimizer'] = 'SLSQP' diff --git a/multitraj.py b/multitraj.py new file mode 100644 index 000000000..6a833de6c --- /dev/null +++ b/multitraj.py @@ -0,0 +1,153 @@ +""" +Goal: use single aircraft description but optimize it for multiple missions simultaneously, +i.e. all missions are on the range-payload line instead of having excess performance +Aircraft csv: defines plane, but also defines payload (passengers, cargo) which can vary with mission + These will have to be specified in some alternate way such as a list correspond to mission # +Phase info: defines a particular mission, will have multiple phase infos +""" +import warnings +import aviary.api as av +import openmdao.api as om +import dymos as dm +from aviary.variable_info.enums import ProblemType +from c5_ferry_phase_info import phase_info as c5_ferry_phase_info +from c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info +from c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info +from aviary.variable_info.variable_meta_data import _MetaData as MetaData + +planes = ['c5_maxpayload.csv', 'c5_intermediate.csv'] +phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] +weights = [1, 1] +num_missions = len(weights) + +# "comp?.a can be used to reference multiple comp1.a comp2.a etc" + + +def setupprob(super_prob): + # Aviary's problem setup wrapper uses these ignored warnings to suppress + # some warnings related to variable promotion. Replicating that here with + # setup for the super problem + with warnings.catch_warnings(): + warnings.simplefilter("ignore", om.OpenMDAOWarning) + warnings.simplefilter("ignore", om.PromotionWarning) + super_prob.setup() + + +if __name__ == '__main__': + super_prob = om.Problem() + probs = [] + prefix = "problem_" + + # define individual aviary problems + for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): + prob = av.AviaryProblem() + prob.load_inputs(plane, phase_info) + prob.check_and_preprocess_inputs() + prob.add_pre_mission_systems() + traj = prob.add_phases() # save dymos traj to add to super problem as a subsystem + prob.add_post_mission_systems() + prob.link_phases() + prob.problem_type = ProblemType.ALTERNATE # adds summary gross mass as design var + prob.add_design_variables() + probs.append(prob) + + group = om.Group() # this group will contain all the promoted aviary vars + group.add_subsystem("pre", prob.pre_mission) + group.add_subsystem("traj", traj) + group.add_subsystem("post", prob.post_mission) + + # setting defaults for these variables to suppress errors + longlst = [ + 'mission:summary:gross_mass', 'aircraft:wing:sweep', + 'aircraft:wing:thickness_to_chord', 'aircraft:wing:area', + 'aircraft:wing:taper_ratio', 'mission:design:gross_mass'] + for var in longlst: + group.set_input_defaults( + var, val=MetaData[var]['default_value'], + units=MetaData[var]['units']) + + # add group and promote design gross mass (common input amongst multiple missions) + # in this way it represents the MTOW + super_prob.model.add_subsystem(prefix+f'{i}', group, promotes=[ + 'mission:design:gross_mass']) + + # add design gross mass as a design var + super_prob.model.add_design_var( + 'mission:design:gross_mass', lower=100e3, upper=1000e3) + + for i in range(num_missions): + # connecting each subcomponent's fuel burn to super problem's unique fuel variables + super_prob.model.connect( + prefix+f"{i}.mission:summary:fuel_burned", f"fuel_{i}") + + # create constraint to force each mission's summary gross mass to not + # exceed the common mission design gross mass (aka MTOW) + super_prob.model.add_subsystem(f'MTOW_constraint{i}', om.ExecComp( + 'mtow_resid = design_gross_mass - summary_gross_mass'), + promotes=[('summary_gross_mass', prefix+f'{i}.mission:summary:gross_mass'), + ('design_gross_mass', 'mission:design:gross_mass')]) + + super_prob.model.add_constraint(f'MTOW_constraint{i}.mtow_resid', lower=0.) + + # creating variable strings that will represent fuel burn from each mission + fuel_burned_vars = [f"fuel_{i}" for i in range(num_missions)] + weighted_str = "+".join([f"{fuel}*{weight}" + for fuel, weight in zip(fuel_burned_vars, weights)]) + # weighted_str looks like: fuel_0 * weight[0] + fuel_1 * weight[1] + + # adding compound execComp to super problem + super_prob.model.add_subsystem('compound_fuel_burn_objective', om.ExecComp( + "compound = "+weighted_str), promotes=["compound", *fuel_burned_vars]) + + super_prob.driver = om.ScipyOptimizeDriver() + super_prob.driver.options['optimizer'] = 'SLSQP' + super_prob.model.add_objective('compound') # output from execcomp goes here + + setupprob(super_prob) + om.n2(super_prob, outfile="multi_mission_importTraj_N2.html") # create N2 diagram + # for prob in probs: + # # prob.setup() + # prob.set_initial_guesses() + + # dm.run_problem(super_prob) + + +""" +Ferry mission phase info: +Times (min): 0, 50, 812, 843 + Alt (ft): 0, 29500, 32000, 0 + Mach: 0.3, 0.77, 0.77, 0.3 +Est. Range: 7001 nmi +Notes: 32k in 30 mins too fast for aviary, climb to low alt then slow rise through cruise + +Intermediate mission phase info: +Times (min): 0, 50, 560, 590 + Alt (ft): 0, 29500, 32000, 0 + Mach: 0.3, 0.77, 0.77, 0.3 +Est. Range: 4839 nmi + +Max Payload mission phase info: +Times (min): 0, 50, 260, 290 + Alt (ft): 0, 29500, 32000, 0 + Mach: 0.3, 0.77, 0.77, 0.3 +Est. Range: 2272 nmi + +Hard to find multiple payload/range values for FwFm (737), so use C-5 instead +Based on: + https://en.wikipedia.org/wiki/Lockheed_C-5_Galaxy#Specifications_(C-5M), + https://www.af.mil/About-Us/Fact-Sheets/Display/Article/1529718/c-5-abc-galaxy-and-c-5m-super-galaxy/ + +MTOW: 840,000 lb +Max Payload: 281,000 lb +Max Fuel: 341,446 lb +Empty Weight: 380,000 lb -> leaves 460,000 lb for fuel+payload (max fuel + max payload = 622,446 lb) + +Payload/range: + 281,000 lb payload -> 2,150 nmi range (AF.mil) [max payload case] + 120,000 lb payload -> 4,800 nmi range (AF.mil) [intermediate case] + 0 lb payload -> 7,000 nmi range (AF.mil) [ferry case] + +Flight characteristics: + Cruise at M0.77 at 33k ft + Max rate of climb: 2100 ft/min +""" From aebe4d2befcd6b60b77a186ab81957e0f79ed5f6 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Fri, 26 Jul 2024 14:51:59 -0400 Subject: [PATCH 012/113] aviary style cannonball problem --- AvCannonball.html | 14840 ++++++++++++++++++++++++++++++++++++++++++++ avcannonball.py | 268 + cannonball.py | 14 +- multimission.py | 3 +- 4 files changed, 15121 insertions(+), 4 deletions(-) create mode 100644 AvCannonball.html create mode 100644 avcannonball.py diff --git a/AvCannonball.html b/AvCannonball.html new file mode 100644 index 000000000..12372760f --- /dev/null +++ b/AvCannonball.html @@ -0,0 +1,14840 @@ + + + +OpenMDAO Model Hierarchy and N2 diagram + + + + + + + + + + + + + + + + + +
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+
+
+ + + + + + + diff --git a/avcannonball.py b/avcannonball.py new file mode 100644 index 000000000..4961ae85b --- /dev/null +++ b/avcannonball.py @@ -0,0 +1,268 @@ +from dymos.models.atmosphere.atmos_1976 import USatm1976Data +from scipy.interpolate import interp1d +import openmdao.api as om +import dymos as dm +import numpy as np +import sys + + +class CannonballProblem(om.Problem): + def __init__(self): + super().__init__() + self.model = CannonballGroup() + self.pre_mission = PreMissionGroup() + self.post_mission = PostMissionGroup() + self.traj = None + self.model.add_subsystem('pre', self.pre_mission, + promotes_inputs=['*']) + self.model.add_subsystem('post', self.post_mission) + + def add_trajectory(self, ke_max=1e2): + # traj = self.model.add_subsystem('traj', dm.Trajectory(), promotes=['*']) + traj = dm.Trajectory() + transcription = dm.Radau(num_segments=5, order=3, compressed=True) + ascent = dm.Phase(ode_class=CannonballODE, transcription=transcription) + traj.add_phase('ascent', ascent) + + transcription = dm.GaussLobatto(num_segments=5, order=3, compressed=True) + descent = dm.Phase(ode_class=CannonballODE, transcription=transcription) + traj.add_phase('descent', descent) + + for phase in (ascent, descent): + is_ascent = phase.name == "ascent" + phase.set_time_options(fix_initial=True if is_ascent else False, + duration_bounds=(1, 100), duration_ref=100, units='s') + phase.set_state_options('r', fix_initial=is_ascent, fix_final=False) + phase.set_state_options('h', fix_initial=is_ascent, fix_final=not is_ascent) + phase.set_state_options('gam', fix_initial=False, fix_final=is_ascent) + phase.set_state_options('v', fix_initial=False, fix_final=False) + phase.add_parameter('S', units='m**2', static_target=True, val=0.005) + phase.add_parameter('m', units='kg', static_target=True, val=1.0) + phase.add_parameter('price', units='USD', static_target=True, val=10) + phase.add_parameter('CD', units=None, static_target=True, val=0.5) + + # descent.add_objective('r', loc='final', scaler=-1.0) # negative means to maximize + for param in ('CD', 'm', 'S', 'price'): + traj.add_parameter(param, static_target=True) + + # Link Phases (link time and all state variables) + traj.link_phases(phases=['ascent', 'descent'], vars=['*']) + # have to set muzzle energy here before setup for sim to run properly + ascent.add_boundary_constraint('ke', loc='initial', + upper=ke_max, lower=0, ref=100000) + self.traj = traj + self.model.add_subsystem('traj', traj) + self.phases = [ascent, descent] + + def setDefaults(self): + self.model.set_input_defaults('dens', val=7.87, units='g/cm**3') + + def addDesVar(self): + self.model.add_design_var('radius', lower=0.01, upper=0.10, + ref0=0.01, ref=0.10, units='m') + + def linkPhases(self): + self.model.connect('sizing_comp.mass', 'traj.parameters:m') + self.model.connect('sizing_comp.S', 'traj.parameters:S') + self.model.connect('sizing_comp.price', 'traj.parameters:price') + + def setInitialVals(self): + self.set_val('radius', 0.05, units='m') + self.set_val('dens', 7.87, units='g/cm**3') + + self.set_val("traj.parameters:CD", 0.5) + + self.set_val("traj.ascent.t_initial", 0.0) + self.set_val("traj.ascent.t_duration", 10.0) + # list is initial and final, based on phase info some are fixed others are not + ascent, descent = self.phases + self.set_val("traj.ascent.states:r", ascent.interp('r', [0, 100])) + self.set_val('traj.ascent.states:h', ascent.interp('h', [0, 100])) + self.set_val('traj.ascent.states:v', ascent.interp('v', [200, 150])) + self.set_val('traj.ascent.states:gam', + ascent.interp('gam', [25, 0]), units='deg') + + self.set_val('traj.descent.t_initial', 10.0) + self.set_val('traj.descent.t_duration', 10.0) + + self.set_val('traj.descent.states:r', descent.interp('r', [100, 200])) + self.set_val('traj.descent.states:h', descent.interp('h', [100, 0])) + self.set_val('traj.descent.states:v', descent.interp('v', [150, 200])) + self.set_val('traj.descent.states:gam', + descent.interp('gam', [0, -45]), units='deg') + + +class CannonballGroup(om.Group): + def __init__(self): + super().__init__() + + +class PreMissionGroup(om.Group): + def __init__(self): + super().__init__() + self.sizingcomp = CannonballSizing() + self.add_subsystem('sizing_comp', self.sizingcomp, + promotes_inputs=['*']) + + +class PostMissionGroup(om.Group): + pass + + +class CannonballODE(om.ExplicitComponent): + def initialize(self): + self.options.declare('num_nodes', types=int) + + def setup(self): + nn = self.options['num_nodes'] + # static params + self.add_input('m', units='kg') + self.add_input('S', units='m**2') + self.add_input('CD', 0.5) + + # time varying inputs + self.add_input('h', units='m', shape=nn) + self.add_input('v', units='m/s', shape=nn) + self.add_input('gam', units='rad', shape=nn) + + # state rates + self.add_output('v_dot', shape=nn, units='m/s**2', + tags=['dymos.state_rate_source:v']) + self.add_output('gam_dot', shape=nn, units='rad/s', + tags=['dymos.state_rate_source:gam']) + self.add_output('h_dot', shape=nn, units='m/s', + tags=['dymos.state_rate_source:h']) + self.add_output('r_dot', shape=nn, units='m/s', + tags=['dymos.state_rate_source:r']) + self.add_output('ke', shape=nn, units='J') + + # Ask OpenMDAO to compute the partial derivatives using complex-step + # with a partial coloring algorithm for improved performance, and use + # a graph coloring algorithm to automatically detect the sparsity pattern. + self.declare_coloring(wrt='*', method='cs') + + alt_data = USatm1976Data.alt * om.unit_conversion('ft', 'm')[0] + rho_data = USatm1976Data.rho * om.unit_conversion('slug/ft**3', 'kg/m**3')[0] + self.rho_interp = interp1d(np.array(alt_data, dtype=complex), + np.array(rho_data, dtype=complex), + kind='linear') + + def compute(self, inputs, outputs): + + gam = inputs['gam'] + v = inputs['v'] + h = inputs['h'] + m = inputs['m'] + S = inputs['S'] + CD = inputs['CD'] + + GRAVITY = 9.80665 # m/s**2 + + # handle complex-step gracefully from the interpolant + if np.iscomplexobj(h): + rho = self.rho_interp(inputs['h']) + else: + rho = self.rho_interp(inputs['h']).real + + q = 0.5*rho*inputs['v']**2 + qS = q * S + D = qS * CD + cgam = np.cos(gam) + sgam = np.sin(gam) + outputs['v_dot'] = - D/m-GRAVITY*sgam + outputs['gam_dot'] = -(GRAVITY/v)*cgam + outputs['h_dot'] = v*sgam + outputs['r_dot'] = v*cgam + outputs['ke'] = 0.5*m*v**2 + + +class CannonballSizing(om.ExplicitComponent): + def setup(self): + self.add_input(name='radius', val=1.0, units='m') + self.add_input(name='dens', val=7870., units='kg/m**3') + + self.add_output(name='mass', shape=(1,), units='kg') + self.add_output(name='S', shape=(1,), units='m**2') + self.add_output(name='price', shape=(1,), units='USD') + + self.declare_partials(of='mass', wrt='dens') + self.declare_partials(of='mass', wrt='radius') + self.declare_partials(of='S', wrt='radius') + self.declare_partials(of='price', wrt='radius') + self.declare_partials(of='price', wrt='dens') + + def compute(self, inputs, outputs): + radius = inputs['radius'] + dens = inputs['dens'] + outputs['mass'] = (4/3.) * dens * np.pi * radius ** 3 + outputs['S'] = np.pi * radius ** 2 + outputs['price'] = (4/3.) * dens * np.pi * radius ** 3 * 10 # $10 per kg + + def compute_partials(self, inputs, partials): + radius = inputs['radius'] + dens = inputs['dens'] + partials['mass', 'dens'] = (4/3.) * np.pi * radius ** 3 + partials['mass', 'radius'] = 4. * dens * np.pi * radius ** 2 + partials['S', 'radius'] = 2 * np.pi * radius + partials['price', 'dens'] = (4/3.) * np.pi * radius ** 3 * 10 + partials['price', 'radius'] = 4. * dens * np.pi * radius ** 2 * 10 + + +# if run as python avcannonball.py n2, it will create an N2 +makeN2 = False +if len(sys.argv) > 1: + if "n2" in sys.argv[1].lower(): + makeN2 = True + +# handling of multiple KEs +kes = [4e3] +weights = [1] +# if fewer weights present than KEs, use same weight +if len(kes) > len(weights): + weights = [1]*len(kes) +elif len(kes) < len(weights): + raise Exception("Cannot have more weights than cannons!") +num_trajs = len(kes) + +probs = [] +super_prob = om.Problem() + +for i, ke in enumerate(kes): + prob = CannonballProblem() + prob.add_trajectory(ke_max=ke) + prob.setDefaults() + + group = om.Group() + group.add_subsystem('pre', prob.pre_mission) + group.add_subsystem('traj', prob.traj) + group.add_subsystem('post', prob.post_mission) + super_prob.model.add_subsystem(f'probgroup_{i}', group) + probs.append(prob) + +ranges = [f"r{i}" for i in range(num_trajs)] # looks like: [r0, r1, ...] +# weighted_sum_str looks like: 1*r0+1*r1+... +weighted_sum_str = "+".join([f"{weight}*{r}" for r, weight in zip(ranges, weights)]) +super_prob.model.add_subsystem('compoundComp', om.ExecComp( + "compound_range=" + weighted_sum_str), + promotes=['compound_range', *ranges]) + +for i in range(num_trajs): + super_prob.model.connect( + f'probgroup_{i}.traj.descent.states:r', ranges[i], + src_indices=-1) + +super_prob.model.add_objective('compound_range', scaler=-1) # maximize range + +super_prob.driver = om.ScipyOptimizeDriver() +super_prob.driver.options['optimizer'] = 'SLSQP' +super_prob.driver.declare_coloring() +super_prob.model.linear_solver = om.DirectSolver() +super_prob.setup() + +for prob in probs: + prob.setup() + prob.setInitialVals() + +if makeN2: + om.n2(super_prob, outfile='AvCannonball.html') +dm.run_problem(super_prob) diff --git a/cannonball.py b/cannonball.py index 9f1d81303..9d1fc49d3 100644 --- a/cannonball.py +++ b/cannonball.py @@ -1,4 +1,3 @@ -from os import stat import numpy as np from scipy.interpolate import interp1d import matplotlib.pyplot as plt @@ -191,9 +190,18 @@ def createTrajectory(ke_max): weighted_sum_str = "+".join([f"{weight}*{r}" for r, weight in zip(ranges, weights)]) p.model.add_subsystem('compoundComp', om.ExecComp("compound_range="+weighted_sum_str), promotes=['compound_range', *ranges]) - for i in range(num_trajs): - p.model.connect(f"traj_{i}.descent.states:r", ranges[i], src_indices=-1) + p.model.connect(f"traj_{i}.descent.states:r", f'r{i}', src_indices=-1) +# p.model.add_subsystem('compoundComp', +# om.ExecComp("compound_range=dot(ranges,weights)", +# weights={'val': weights}, +# ranges={'val': np.ones(num_trajs), 'units': 'm'}), +# promotes=['compound_range', 'ranges', 'weights']) + +# gg = [f'traj_{i}.descent.states:r' for i in range(num_trajs)] +# p.model.connect(gg, 'ranges', src_indices=-1) +# for i in range(num_trajs): +# p.model.connect(f"traj_{i}.descent.states:r", f'ranges[{i}]', src_indices=-1) p.model.add_objective('compound_range', scaler=-1) diff --git a/multimission.py b/multimission.py index c5da0f2b2..4506c0cb4 100644 --- a/multimission.py +++ b/multimission.py @@ -75,7 +75,8 @@ prob.set_initial_guesses() dm.run_problem(super_prob) - + print(super_prob.check_partials()) + # om.n2(super_prob) """ Ferry mission phase info: From 4abb769078f4b5235d494980967171944e0a5749 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Fri, 26 Jul 2024 18:15:53 -0400 Subject: [PATCH 013/113] working cannonball model with trajectory/pre mission copying --- AvCannonball.html | 2 +- avcannonball.py | 317 +++++++++++++++++++++++++++++++++++----------- cannonball.py | 4 +- 3 files changed, 246 insertions(+), 77 deletions(-) diff --git a/AvCannonball.html b/AvCannonball.html index 12372760f..ba97bc8b3 100644 --- a/AvCannonball.html +++ b/AvCannonball.html @@ -3255,7 +3255,7 @@

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diff --git a/avcannonball.py b/avcannonball.py index 4961ae85b..b80a0fda9 100644 --- a/avcannonball.py +++ b/avcannonball.py @@ -1,5 +1,6 @@ from dymos.models.atmosphere.atmos_1976 import USatm1976Data from scipy.interpolate import interp1d +import matplotlib.pyplot as plt import openmdao.api as om import dymos as dm import numpy as np @@ -13,12 +14,11 @@ def __init__(self): self.pre_mission = PreMissionGroup() self.post_mission = PostMissionGroup() self.traj = None - self.model.add_subsystem('pre', self.pre_mission, - promotes_inputs=['*']) - self.model.add_subsystem('post', self.post_mission) + self.model.add_subsystem('pre_mission', self.pre_mission, + promotes=['*']) + self.model.add_subsystem('post_mission', self.post_mission) def add_trajectory(self, ke_max=1e2): - # traj = self.model.add_subsystem('traj', dm.Trajectory(), promotes=['*']) traj = dm.Trajectory() transcription = dm.Radau(num_segments=5, order=3, compressed=True) ascent = dm.Phase(ode_class=CannonballODE, transcription=transcription) @@ -55,20 +55,20 @@ def add_trajectory(self, ke_max=1e2): self.phases = [ascent, descent] def setDefaults(self): - self.model.set_input_defaults('dens', val=7.87, units='g/cm**3') + self.model.set_input_defaults('density', val=7.87, units='g/cm**3') def addDesVar(self): self.model.add_design_var('radius', lower=0.01, upper=0.10, ref0=0.01, ref=0.10, units='m') - def linkPhases(self): - self.model.connect('sizing_comp.mass', 'traj.parameters:m') - self.model.connect('sizing_comp.S', 'traj.parameters:S') - self.model.connect('sizing_comp.price', 'traj.parameters:price') + def connectPreTraj(self): + self.model.connect('mass', 'traj.parameters:m') + self.model.connect('S', 'traj.parameters:S') + self.model.connect('price', 'traj.parameters:price') def setInitialVals(self): self.set_val('radius', 0.05, units='m') - self.set_val('dens', 7.87, units='g/cm**3') + self.set_val('density', 7.87, units='g/cm**3') self.set_val("traj.parameters:CD", 0.5) @@ -102,7 +102,7 @@ def __init__(self): super().__init__() self.sizingcomp = CannonballSizing() self.add_subsystem('sizing_comp', self.sizingcomp, - promotes_inputs=['*']) + promotes=['*']) class PostMissionGroup(om.Group): @@ -179,33 +179,33 @@ def compute(self, inputs, outputs): class CannonballSizing(om.ExplicitComponent): def setup(self): self.add_input(name='radius', val=1.0, units='m') - self.add_input(name='dens', val=7870., units='kg/m**3') + self.add_input(name='density', val=7870., units='kg/m**3') self.add_output(name='mass', shape=(1,), units='kg') self.add_output(name='S', shape=(1,), units='m**2') self.add_output(name='price', shape=(1,), units='USD') - self.declare_partials(of='mass', wrt='dens') + self.declare_partials(of='mass', wrt='density') self.declare_partials(of='mass', wrt='radius') self.declare_partials(of='S', wrt='radius') self.declare_partials(of='price', wrt='radius') - self.declare_partials(of='price', wrt='dens') + self.declare_partials(of='price', wrt='density') def compute(self, inputs, outputs): radius = inputs['radius'] - dens = inputs['dens'] - outputs['mass'] = (4/3.) * dens * np.pi * radius ** 3 + density = inputs['density'] + outputs['mass'] = (4/3.) * density * np.pi * radius ** 3 outputs['S'] = np.pi * radius ** 2 - outputs['price'] = (4/3.) * dens * np.pi * radius ** 3 * 10 # $10 per kg + outputs['price'] = (4/3.) * density * np.pi * radius ** 3 * 10 # $10 per kg def compute_partials(self, inputs, partials): radius = inputs['radius'] - dens = inputs['dens'] - partials['mass', 'dens'] = (4/3.) * np.pi * radius ** 3 - partials['mass', 'radius'] = 4. * dens * np.pi * radius ** 2 + density = inputs['density'] + partials['mass', 'density'] = (4/3.) * np.pi * radius ** 3 + partials['mass', 'radius'] = 4. * density * np.pi * radius ** 2 partials['S', 'radius'] = 2 * np.pi * radius - partials['price', 'dens'] = (4/3.) * np.pi * radius ** 3 * 10 - partials['price', 'radius'] = 4. * dens * np.pi * radius ** 2 * 10 + partials['price', 'density'] = (4/3.) * np.pi * radius ** 3 * 10 + partials['price', 'radius'] = 4. * density * np.pi * radius ** 2 * 10 # if run as python avcannonball.py n2, it will create an N2 @@ -214,55 +214,224 @@ def compute_partials(self, inputs, partials): if "n2" in sys.argv[1].lower(): makeN2 = True -# handling of multiple KEs -kes = [4e3] -weights = [1] -# if fewer weights present than KEs, use same weight -if len(kes) > len(weights): - weights = [1]*len(kes) -elif len(kes) < len(weights): - raise Exception("Cannot have more weights than cannons!") -num_trajs = len(kes) - -probs = [] -super_prob = om.Problem() - -for i, ke in enumerate(kes): - prob = CannonballProblem() - prob.add_trajectory(ke_max=ke) - prob.setDefaults() - - group = om.Group() - group.add_subsystem('pre', prob.pre_mission) - group.add_subsystem('traj', prob.traj) - group.add_subsystem('post', prob.post_mission) - super_prob.model.add_subsystem(f'probgroup_{i}', group) - probs.append(prob) - -ranges = [f"r{i}" for i in range(num_trajs)] # looks like: [r0, r1, ...] -# weighted_sum_str looks like: 1*r0+1*r1+... -weighted_sum_str = "+".join([f"{weight}*{r}" for r, weight in zip(ranges, weights)]) -super_prob.model.add_subsystem('compoundComp', om.ExecComp( - "compound_range=" + weighted_sum_str), - promotes=['compound_range', *ranges]) - -for i in range(num_trajs): - super_prob.model.connect( - f'probgroup_{i}.traj.descent.states:r', ranges[i], - src_indices=-1) - -super_prob.model.add_objective('compound_range', scaler=-1) # maximize range - -super_prob.driver = om.ScipyOptimizeDriver() -super_prob.driver.options['optimizer'] = 'SLSQP' -super_prob.driver.declare_coloring() -super_prob.model.linear_solver = om.DirectSolver() -super_prob.setup() - -for prob in probs: - prob.setup() - prob.setInitialVals() - -if makeN2: - om.n2(super_prob, outfile='AvCannonball.html') -dm.run_problem(super_prob) + +def runAvCannonball(kes=[4e3], weights=[1]): + # handling of multiple KEs + # if fewer weights present than KEs, use same weight + if len(kes) > len(weights): + weights = [1]*len(kes) + elif len(kes) < len(weights): + raise Exception("Cannot have more weights than cannons!") + num_trajs = len(kes) + + probs = [] + super_prob = om.Problem() + + # create sub problems and add them to super in a group + # group prevents spillage of promoted vars into super + prefix = "group" # prefix for each om.Group + for i, ke in enumerate(kes): + prob = CannonballProblem() + prob.add_trajectory(ke_max=ke) + prob.setDefaults() + prob.addDesVar() # doesn't seem to do anything + prob.connectPreTraj() # doesn't seem to actually do anything + + group = om.Group() + group.add_subsystem('pre_mission', prob.pre_mission) + group.add_subsystem('traj', prob.traj) + group.add_subsystem('post_mission', prob.post_mission) + # promoting radius and density keeps it constant for all missions + super_prob.model.add_subsystem(prefix+f'_{i}', group, + promotes_inputs=['radius', 'density']) + probs.append(prob) + + # create an execComp with a compound range function to maximize range + # for all cannons with a weighted function + ranges = [f"r{i}" for i in range(num_trajs)] # looks like: [r0, r1, ...] + # weighted_sum_str looks like: 1*r0+1*r1+... + weighted_sum_str = "+".join([f"{weight}*{r}" for r, weight in zip(ranges, weights)]) + super_prob.model.add_subsystem('compoundComp', om.ExecComp( + "compound_range=" + weighted_sum_str), + promotes=['compound_range', *ranges]) + + # controlling radius to affect mass/ballistic coeff + super_prob.model.add_design_var('radius', lower=0.01, upper=0.10, + ref0=0.01, ref=0.10, units='m') + + for i in range(num_trajs): + # connect end of trajectory range to compound range input + super_prob.model.connect( + prefix+f'_{i}.traj.descent.states:r', ranges[i], + src_indices=-1) + + # connect pre-mission parameters to trajectory counter parts + # this connection would happen within each problem's internal function, + # but since we're extracting the components into a larger problem, + # these connections have to be made at the super problem level + super_prob.model.connect( + prefix+f'_{i}.mass', prefix+f'_{i}.traj.parameters:m') + super_prob.model.connect( + prefix+f'_{i}.S', prefix+f'_{i}.traj.parameters:S') + super_prob.model.connect( + prefix+f'_{i}.price', prefix+f'_{i}.traj.parameters:price') + + super_prob.model.add_objective('compound_range', scaler=-1) # maximize range + + super_prob.driver = om.ScipyOptimizeDriver() + super_prob.driver.options['optimizer'] = 'SLSQP' + super_prob.driver.declare_coloring() + super_prob.model.linear_solver = om.DirectSolver() + super_prob.setup() + + for i, prob in enumerate(probs): + reference = prefix+f"_{i}" + super_prob.set_val(reference+'.radius', 0.05, units='m') + super_prob.set_val(reference+'.density', 7.87, units='g/cm**3') + + super_prob.set_val(reference+".traj.parameters:CD", 0.5) + + super_prob.set_val(reference+".traj.ascent.t_initial", 0.0) + super_prob.set_val(reference+".traj.ascent.t_duration", 10.0) + # list is initial and final, based on phase info some are fixed others are not + ascent, descent = prob.phases + super_prob.set_val(reference+".traj.ascent.states:r", + ascent.interp('r', [0, 100])) + super_prob.set_val(reference+'.traj.ascent.states:h', + ascent.interp('h', [0, 100])) + super_prob.set_val(reference+'.traj.ascent.states:v', + ascent.interp('v', [200, 150])) + super_prob.set_val(reference+'.traj.ascent.states:gam', + ascent.interp('gam', [25, 0]), units='deg') + + super_prob.set_val(reference+'.traj.descent.t_initial', 10.0) + super_prob.set_val(reference+'.traj.descent.t_duration', 10.0) + + super_prob.set_val(reference+'.traj.descent.states:r', + descent.interp('r', [100, 200])) + super_prob.set_val(reference+'.traj.descent.states:h', + descent.interp('h', [100, 0])) + super_prob.set_val(reference+'.traj.descent.states:v', + descent.interp('v', [150, 200])) + super_prob.set_val(reference+'.traj.descent.states:gam', + descent.interp('gam', [0, -45]), units='deg') + + if makeN2: + om.n2(super_prob, outfile='AvCannonball.html') + + dm.run_problem(super_prob) + return super_prob, prefix, num_trajs, kes, weights + + +def printOutput(super_prob, prefix, num_trajs, kes, weights): + # formatted output + print("\n\n=================================================") + print( + f"Optimized {num_trajs} trajectories with weights: {', '.join(map(str,weights))}") + rad = super_prob.get_val('radius', units='cm')[0] + + mass0 = super_prob.get_val(prefix+'_0.mass', units='kg')[0] + price0 = super_prob.get_val(prefix+'_0.price', units='USD')[0] + area0 = super_prob.get_val(prefix+'_0.S', units='cm**2')[0] + + # mass, price, S are outputs from sizing. These should be common amongst all + # trajectories, however since they're outputs they cannot be promoted upto + # super problem without unique names. This loop checks their values with + # value of the first trajectory to ensure they are the same. + if num_trajs > 1: + for i in range(num_trajs-1): + mass = super_prob.get_val(prefix+f'_{i+1}.mass', units='kg')[0] + price = super_prob.get_val(prefix+f'_{i+1}.price', units='USD')[0] + area = super_prob.get_val(prefix+f'_{i+1}.S', units='cm**2')[0] + if mass != mass0 or price != price0 or area != area0: + raise Exception( + "Masses, Prices, and/or Areas are not equivalent between trajectories.") + + print("\nOptimal Cannonball Description:") + print( + f"\tRadius: {rad:.2f} cm, Mass: {mass0:.2f} kg, Price: ${price0:.2f}, Area: {area0:.2f} sqcm") + + print("\nOptimal Trajectory Descriptions:") + ranges = 0 + for i, ke in enumerate(kes): + angle = super_prob.get_val( + prefix+f'_{i}.traj.ascent.timeseries.gam', units='deg')[0, 0] + max_range = super_prob.get_val( + prefix+f'_{i}.traj.descent.timeseries.r')[-1, 0] + + print( + f"\tKE: {ke/1e3:.2f} KJ, Launch Angle: {angle:.2f} deg, Max Range: {max_range:.2f} m") + ranges += weights[i]*max_range + print(f"System range: {ranges}") + + +def plotOutput(super_prob, prefix, num_trajs, kes, weights, show=True): + if show: + _, ax = plt.subplots() + timevals = [] + hvals = [] + rvals = [] + for i in range(num_trajs): + tv = [] + hv = [] + rv = [] + for phase in ('ascent', 'descent'): + tv.append(super_prob.get_val( + prefix+f'_{i}.traj.{phase}.timeseries.time')) + hv.append(super_prob.get_val( + prefix+f'_{i}.traj.{phase}.timeseries.h')) + rv.append(super_prob.get_val( + prefix+f'_{i}.traj.{phase}.timeseries.r')) + + timevals.append(np.vstack(tv)) + hvals.append(np.vstack(hv)) + rvals.append(np.vstack(rv)) + if show: + ax.plot(rvals[-1], hvals[-1]) + + if show: + plt.grid() + plt.legend([f"Weights = {weight}" for weight in weights]) + plt.title(f"Cannonballs With KEs: {kes} J") + plt.show() + return timevals, rvals, hvals + + +if __name__ == '__main__': + testing_weights = [[3, 2, 2], [2, 2, 3]] + kes = [4e5, 5e5, 6e5] + legendlst = [] + rs, hs = [], [] + for i, weighting in enumerate(testing_weights): + super_prob, prefix, num_trajs, kes, weights = runAvCannonball( + kes=kes, weights=weighting) + printOutput(super_prob, prefix, num_trajs, kes, weights) + tvals, rvals, hvals = plotOutput( + super_prob, prefix, num_trajs, kes, weights, show=False) + + for r, h, weight in zip(rvals, hvals, weighting): + rs.append(r) + hs.append(h) + legendlst.append(f"Group: {weighting}, Weight: {weight}") + + _, ax = plt.subplots() + for r, h in zip(rs, hs): + ax.plot(r, h) + plt.grid() + plt.legend(legendlst) + plt.title(f"Cannonballs With KEs: {kes} J") + plt.show() + + +""" +Findings: +- connections between trajectory parameters and pre-mission parameters have to be made at + super problem level, running the cannonballproblem method to form those connections has seemingly + no effect, causing divide by zero errors b/c the trajectory value is not set + +- design var has to be set in super problem, cannonballproblem design var is not manipulated by optimizer, + giving a result with the default value for ball radius + +- initial values have to be set at super problem level, running cannonballproblem's initial value function + throws error that setval cannot run before setup (even though superproblem setup was run). +""" diff --git a/cannonball.py b/cannonball.py index 9d1fc49d3..ac49ea051 100644 --- a/cannonball.py +++ b/cannonball.py @@ -159,11 +159,11 @@ def createTrajectory(ke_max): p.driver.options['optimizer'] = 'SLSQP' p.driver.declare_coloring() -kes = [4e5, 5e5, 6e5] +kes = [4e5, 5e5] # 2:1 ratio (or 1:2) causes results that essentially don't optimize the 1 mission, # 1.01 works, 1.009 doesn't # 2:1:1 works?! - may be related some normalization/bounds issue -weights = [2.1, 1.5, 1.1] +weights = [1, 1] num_trajs = len(kes) p.model.add_subsystem(f"sizing_comp", CannonballSizing(), From de3598e0bfc4e0980f8a6d39994ac2d855fcc9ac Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Mon, 29 Jul 2024 11:43:59 -0400 Subject: [PATCH 014/113] updated next steps for multimission --- AvCannonball.html | 2 +- AvCannonball_noconnect.html | 14840 ++++++++++++++++++++++++++++++++++ avcannonball.py | 84 +- multitraj.py | 13 +- 4 files changed, 14915 insertions(+), 24 deletions(-) create mode 100644 AvCannonball_noconnect.html diff --git a/AvCannonball.html b/AvCannonball.html index ba97bc8b3..e29612ed5 100644 --- a/AvCannonball.html +++ b/AvCannonball.html @@ -3255,7 +3255,7 @@

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+ + + + + + + diff --git a/avcannonball.py b/avcannonball.py index b80a0fda9..9d2efb363 100644 --- a/avcannonball.py +++ b/avcannonball.py @@ -208,14 +208,7 @@ def compute_partials(self, inputs, partials): partials['price', 'radius'] = 4. * density * np.pi * radius ** 2 * 10 -# if run as python avcannonball.py n2, it will create an N2 -makeN2 = False -if len(sys.argv) > 1: - if "n2" in sys.argv[1].lower(): - makeN2 = True - - -def runAvCannonball(kes=[4e3], weights=[1]): +def runAvCannonball(kes=[4e3], weights=[1], makeN2=False): # handling of multiple KEs # if fewer weights present than KEs, use same weight if len(kes) > len(weights): @@ -397,41 +390,90 @@ def plotOutput(super_prob, prefix, num_trajs, kes, weights, show=True): return timevals, rvals, hvals -if __name__ == '__main__': - testing_weights = [[3, 2, 2], [2, 2, 3]] - kes = [4e5, 5e5, 6e5] +def multiTestCase(makeN2=False): + testing_weights = [[2, 1.2], [1.2, 2]] + kes = [1e5, 6e5] legendlst = [] rs, hs = [], [] - for i, weighting in enumerate(testing_weights): + for weighting in testing_weights: super_prob, prefix, num_trajs, kes, weights = runAvCannonball( - kes=kes, weights=weighting) + kes=kes, weights=weighting, makeN2=makeN2) printOutput(super_prob, prefix, num_trajs, kes, weights) tvals, rvals, hvals = plotOutput( super_prob, prefix, num_trajs, kes, weights, show=False) - for r, h, weight in zip(rvals, hvals, weighting): + for r, h, weight, ke in zip(rvals, hvals, weighting, kes): rs.append(r) hs.append(h) - legendlst.append(f"Group: {weighting}, Weight: {weight}") + legendlst.append(f"KE: {ke/1e3} kJ, Weight: {weight} of {weighting}") _, ax = plt.subplots() for r, h in zip(rs, hs): ax.plot(r, h) plt.grid() - plt.legend(legendlst) - plt.title(f"Cannonballs With KEs: {kes} J") + plt.legend(legendlst, loc='upper left') + titlestr = ", ".join([str(ke/1e3) for ke in kes]) + plt.title(f"Cannonballs With KEs: {titlestr} kJ") plt.show() +if __name__ == '__main__': + # if run as python avcannonball.py n2, it will create an N2 + makeN2 = False + singlerun = True + if len(sys.argv) > 1: + if "n2" in sys.argv: + makeN2 = True + if "multi" in sys.argv: + # runs multiple weightings to see what impact system optimization makes + multiTestCase(makeN2) + singlerun = False + + if singlerun: + # singular weighting run + super_prob, prefix, num_trajs, kes, weights = runAvCannonball( + kes=[4e5, 6e5], weights=[2, 1.5], makeN2=makeN2) + printOutput(super_prob, prefix, num_trajs, kes, weights) + plotOutput(super_prob, prefix, num_trajs, kes, weights) + + """ Findings: -- connections between trajectory parameters and pre-mission parameters have to be made at - super problem level, running the cannonballproblem method to form those connections has seemingly - no effect, causing divide by zero errors b/c the trajectory value is not set +- connections between trajectory parameters and pre-mission parameters (and post-mission for aviary) + have to be made at super problem level, running the cannonballproblem method to form those connections + has seemingly no effect, causing divide by zero errors b/c the trajectory value is not set - design var has to be set in super problem, cannonballproblem design var is not manipulated by optimizer, giving a result with the default value for ball radius - initial values have to be set at super problem level, running cannonballproblem's initial value function throws error that setval cannot run before setup (even though superproblem setup was run). -""" + +What works: +- copying instances of pre, traj, and post mission subsystems and adding to a super problem +- internal linkages between trajectory phases works without super problem references +- compound objective between multiple trajectories works +- connections between 2 problems to maintain same physical size of cannonball (i.e. airplane) +- optimization runs, gives sensible results + +To apply to Aviary: +- link_phases (includes connections to post/pre and traj) +- add_design_vars - sizing components, subsystem level variables + (aviary currently adds aero, prop des vars along with any external subsystem) +- set_initial_guesses + +Next setps: +- multi_mission specific add des var that adds them at super prob level + - aviary's design var can still be run at the aviaryProblem level it just won't have any effect + +- multi_mission link phases that does post/pre to traj connection + - aviary's link phases can still be run it just won't create trajectory to pre mission var connections + - be careful with connections vs. promotions + +- initial guesses, what's the best solution? + - possible ideas: + - use aviary's existing functions to create initial values, but use set val outside on super prob + - would require minimal mods to aviary to not run set val when a flag is passed + - write a fully seperate initial guesses function + - would be problematic to maintain with changes/new additions + """ diff --git a/multitraj.py b/multitraj.py index 6a833de6c..8b3adde98 100644 --- a/multitraj.py +++ b/multitraj.py @@ -5,6 +5,7 @@ These will have to be specified in some alternate way such as a list correspond to mission # Phase info: defines a particular mission, will have multiple phase infos """ +import sys import warnings import aviary.api as av import openmdao.api as om @@ -38,6 +39,11 @@ def setupprob(super_prob): probs = [] prefix = "problem_" + makeN2 = False + if len(sys.argv) > 1: + if "n2" in sys.argv: + makeN2 = True + # define individual aviary problems for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): prob = av.AviaryProblem() @@ -46,7 +52,7 @@ def setupprob(super_prob): prob.add_pre_mission_systems() traj = prob.add_phases() # save dymos traj to add to super problem as a subsystem prob.add_post_mission_systems() - prob.link_phases() + prob.link_phases() # this is half working / connect statements from outside of traj to inside are failing prob.problem_type = ProblemType.ALTERNATE # adds summary gross mass as design var prob.add_design_variables() probs.append(prob) @@ -104,7 +110,10 @@ def setupprob(super_prob): super_prob.model.add_objective('compound') # output from execcomp goes here setupprob(super_prob) - om.n2(super_prob, outfile="multi_mission_importTraj_N2.html") # create N2 diagram + if makeN2: + om.n2(super_prob, outfile="multi_mission_importTraj_N2.html") # create N2 diagram + + # cannot use this b/c initial guesses (i.e. setval func) has to be called on super prob level # for prob in probs: # # prob.setup() # prob.set_initial_guesses() From 4ffdbcafee95116eb30926824a92711e6ff2b0b9 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Mon, 29 Jul 2024 13:09:19 -0400 Subject: [PATCH 015/113] checkpt --- avcannonball.py | 2 ++ cannonball.py | 3 +++ multitraj.py | 19 +++++++++++++++++++ 3 files changed, 24 insertions(+) diff --git a/avcannonball.py b/avcannonball.py index 9d2efb363..70e8052ef 100644 --- a/avcannonball.py +++ b/avcannonball.py @@ -1,3 +1,5 @@ +# Cannonball Multi Mission Example with Aviary-esque setup +# Each mission is defined as a "CannonballProblem", akin to AviaryProblem from dymos.models.atmosphere.atmos_1976 import USatm1976Data from scipy.interpolate import interp1d import matplotlib.pyplot as plt diff --git a/cannonball.py b/cannonball.py index ac49ea051..fc2fe1b9a 100644 --- a/cannonball.py +++ b/cannonball.py @@ -1,3 +1,6 @@ +# Cannonball Multi Mission Example +# A single openMDAO problem is populated with Sizing (pre-mission) +# and Trajectory subsystems (any number of missions) import numpy as np from scipy.interpolate import interp1d import matplotlib.pyplot as plt diff --git a/multitraj.py b/multitraj.py index 8b3adde98..a143aa24d 100644 --- a/multitraj.py +++ b/multitraj.py @@ -24,6 +24,25 @@ # "comp?.a can be used to reference multiple comp1.a comp2.a etc" +class MultiMissionProblem(om.Problem): + def __init__(self): + super().__init__() + self.model.add_subsystem() + + def add_design_variable(): + pass + + def link_pre_post_traj(): + pass + + def set_initial_values(): + pass + + +def add_design_var(): + pass + + def setupprob(super_prob): # Aviary's problem setup wrapper uses these ignored warnings to suppress # some warnings related to variable promotion. Replicating that here with From 9bc6c305ae05f4da195b6609ad132157e3155fb3 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Tue, 30 Jul 2024 08:54:55 -0400 Subject: [PATCH 016/113] checkpt on min time to climb example --- avcannonball.py | 7 +- checkdiff_0.txt | 115 ++++++++++++++++++ checkdiff_1.txt | 115 ++++++++++++++++++ min_time_climb.py | 290 ++++++++++++++++++++++++++++++++++++++++++++++ 4 files changed, 524 insertions(+), 3 deletions(-) create mode 100644 checkdiff_0.txt create mode 100644 checkdiff_1.txt create mode 100644 min_time_climb.py diff --git a/avcannonball.py b/avcannonball.py index 70e8052ef..bb48ec9de 100644 --- a/avcannonball.py +++ b/avcannonball.py @@ -393,7 +393,7 @@ def plotOutput(super_prob, prefix, num_trajs, kes, weights, show=True): def multiTestCase(makeN2=False): - testing_weights = [[2, 1.2], [1.2, 2]] + testing_weights = [[2, 1.2], [1.2, 2], [1, 1]] kes = [1e5, 6e5] legendlst = [] rs, hs = [], [] @@ -410,8 +410,9 @@ def multiTestCase(makeN2=False): legendlst.append(f"KE: {ke/1e3} kJ, Weight: {weight} of {weighting}") _, ax = plt.subplots() - for r, h in zip(rs, hs): - ax.plot(r, h) + colors = ['r--', 'r-', 'b--', 'b-', 'g--', 'g-'] # same color for each cannonball + for r, h, col in zip(rs, hs, colors): + ax.plot(r, h, col) plt.grid() plt.legend(legendlst, loc='upper left') titlestr = ", ".join([str(ke/1e3) for ke in kes]) diff --git a/checkdiff_0.txt b/checkdiff_0.txt new file mode 100644 index 000000000..73765b1a6 --- /dev/null +++ b/checkdiff_0.txt @@ -0,0 +1,115 @@ +time to climb: 255.4723 + +{'h': [array([[ 100. ], + [ 385.84286893], + [ 2524.05538825], + [ 6330.19786708], + [ 8398.09721022], + [ 8398.09721022], + [ 9496.91321874], + [ 8224.65719818], + [ 7524.51936893], + [ 7967.69790418], + [ 7967.69790418], + [ 7685.19578827], + [ 9594.55531382], + [14749.31150762], + [16000. ]]), array([[ 100. ], + [ 385.84286893], + [ 2524.05538825], + [ 6330.19786708], + [ 8398.09721022], + [ 8398.09721022], + [ 9496.91321874], + [ 8224.65719818], + [ 7524.51936893], + [ 7967.69790418], + [ 7967.69790418], + [ 7685.19578827], + [ 9594.55531382], + [14749.31150762], + [16000. ]])], 'r': [array([[ 0. ], + [ 2512.93182958], + [ 9270.65900027], + [16562.87651865], + [20107.2482066 ], + [20107.2482066 ], + [23842.87063336], + [32631.84519492], + [43410.06296693], + [49556.7344816 ], + [49556.7344816 ], + [55970.23796015], + [68204.10399411], + [77757.98698928], + [81884.92516855]]), array([[ 0. ], + [ 2512.93182958], + [ 9270.65900027], + [16562.87651865], + [20107.2482066 ], + [20107.2482066 ], + [23842.87063336], + [32631.84519492], + [43410.06296693], + [49556.7344816 ], + [49556.7344816 ], + [55970.23796015], + [68204.10399411], + [77757.98698928], + [81884.92516855]])], 'thrust': [array([[28040.14632377], + [30685.43462476], + [29491.23905419], + [21324.01785314], + [16249.20034523], + [16249.20034523], + [14664.76010049], + [21846.64091725], + [26953.27860842], + [26642.24161996], + [26642.24161996], + [29154.81655621], + [23634.90073868], + [ 8283.02344799], + [ 6125.4488035 ]]), array([[28040.14632377], + [30685.43462476], + [29491.23905419], + [21324.01785314], + [16249.20034523], + [16249.20034523], + [14664.76010049], + [21846.64091725], + [26953.27860842], + [26642.24161996], + [26642.24161996], + [29154.81655621], + [23634.90073868], + [ 8283.02344799], + [ 6125.4488035 ]])], 'v': [array([[135.964 ], + [206.74599571], + [288.82701778], + [289.73862165], + [267.15878958], + [267.15878958], + [274.87468561], + [362.50881292], + [412.28028855], + [422.61189319], + [422.61189319], + [447.73120108], + [436.16635522], + [323.37066419], + [295.06331582]]), array([[135.964 ], + [206.74599571], + [288.82701778], + [289.73862165], + [267.15878958], + [267.15878958], + [274.87468561], + [362.50881292], + [412.28028855], + [422.61189319], + [422.61189319], + [447.73120108], + [436.16635522], + [323.37066419], + [295.06331582]])]} \ No newline at end of file diff --git a/checkdiff_1.txt b/checkdiff_1.txt new file mode 100644 index 000000000..bc9e3b06e --- /dev/null +++ b/checkdiff_1.txt @@ -0,0 +1,115 @@ +time to climb: 275.9943 + +{'h': [array([[ 100. ], + [ 100.00014197], + [ 928.14250857], + [ 4480.12875143], + [ 5854.4279326 ], + [ 5854.4279326 ], + [ 5753.74074866], + [ 6447.30263607], + [ 7351.40997855], + [ 7374.41870514], + [ 7374.41870514], + [ 7253.93701586], + [ 9040.49548007], + [14442.70128356], + [16000. ]]), array([[ 100. ], + [ 100.00014197], + [ 928.14250857], + [ 4480.12875143], + [ 5854.4279326 ], + [ 5854.4279326 ], + [ 5753.74074866], + [ 6447.30263607], + [ 7351.40997855], + [ 7374.41870514], + [ 7374.41870514], + [ 7253.93701586], + [ 9040.49548007], + [14442.70128356], + [16000. ]])], 'r': [array([[ 0. ], + [ 2968.68666017], + [12073.2967696 ], + [21409.53672779], + [26092.61326574], + [26092.61326574], + [31572.04020064], + [42731.10842357], + [54452.94145834], + [61010.61290372], + [61010.61290372], + [67904.86290601], + [81412.77032767], + 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[238.02678694], + [340.85855179], + [313.48707194], + [327.58435172], + [327.58435172], + [358.34086544], + [381.72767454], + [402.72069599], + [423.91555025], + [423.91555025], + [446.68626447], + [445.20261297], + [330.9922242 ], + [295.06331582]]), array([[135.964 ], + [238.02678694], + [340.85855179], + [313.48707194], + [327.58435172], + [327.58435172], + [358.34086544], + [381.72767454], + [402.72069599], + [423.91555025], + [423.91555025], + [446.68626447], + [445.20261297], + [330.9922242 ], + [295.06331582]])]} \ No newline at end of file diff --git a/min_time_climb.py b/min_time_climb.py new file mode 100644 index 000000000..1700c6a4b --- /dev/null +++ b/min_time_climb.py @@ -0,0 +1,290 @@ +import openmdao.api as om +import dymos as dm +from dymos.examples.min_time_climb.min_time_climb_ode import MinTimeClimbODE +import matplotlib.pyplot as plt +import numpy as np +import sys + + +def min_time_climb(height=20e3, + optimizer='SLSQP', num_seg=3, transcription='gauss-lobatto', + transcription_order=5, force_alloc_complex=False, add_rate=False, + time_name='time'): + + p = om.Problem(model=om.Group()) + + p.driver = om.ScipyOptimizeDriver() + p.driver.options['optimizer'] = optimizer + p.driver.declare_coloring() + + if optimizer == 'SNOPT': + p.driver.opt_settings['Major iterations limit'] = 1000 + p.driver.opt_settings['iSumm'] = 6 + p.driver.opt_settings['Major feasibility tolerance'] = 1.0E-6 + p.driver.opt_settings['Major optimality tolerance'] = 1.0E-6 + p.driver.opt_settings['Function precision'] = 1.0E-12 + p.driver.opt_settings['Linesearch tolerance'] = 0.1 + p.driver.opt_settings['Major step limit'] = 0.5 + elif optimizer == 'IPOPT': + p.driver.opt_settings['tol'] = 1.0E-5 + p.driver.opt_settings['print_level'] = 0 + p.driver.opt_settings['mu_strategy'] = 'monotone' + p.driver.opt_settings['bound_mult_init_method'] = 'mu-based' + p.driver.opt_settings['mu_init'] = 0.01 + + t = {'gauss-lobatto': dm.GaussLobatto( + num_segments=num_seg, order=transcription_order), + 'radau-ps': dm.Radau(num_segments=num_seg, order=transcription_order)} + + traj = dm.Trajectory() + + phase = dm.Phase(ode_class=MinTimeClimbODE, transcription=t[transcription]) + traj.add_phase('phase0', phase) + + p.model.add_subsystem('traj', traj) + + phase.set_time_options(fix_initial=True, duration_bounds=(50, 400), + duration_ref=100.0, name=time_name) + + phase.add_state('r', fix_initial=True, lower=0, upper=1.0E6, + ref=1.0E3, defect_ref=1.0E3, units='m', + rate_source='flight_dynamics.r_dot') + + phase.add_state('h', fix_initial=True, lower=1, upper=height, + ref=height, defect_ref=height, units='m', + rate_source='flight_dynamics.h_dot', targets=['h']) + + phase.add_state('v', fix_initial=True, lower=10.0, + ref=1.0E2, defect_ref=1.0E2, units='m/s', + rate_source='flight_dynamics.v_dot', targets=['v']) + + phase.add_state('gam', fix_initial=True, lower=-1.5, upper=1.5, + ref=1.0, defect_ref=1.0, units='rad', + rate_source='flight_dynamics.gam_dot', targets=['gam']) + + phase.add_state('m', fix_initial=True, lower=10.0, upper=1.0E5, + ref=10_000, defect_ref=10_000, units='kg', + rate_source='prop.m_dot', targets=['m']) + + phase.add_control('alpha', units='deg', lower=-8.0, upper=8.0, scaler=1.0, + rate_continuity=True, rate_continuity_scaler=100.0, + rate2_continuity=False, targets=['alpha']) + + phase.add_parameter('S', val=49.2386, units='m**2', opt=False, targets=['S']) + phase.add_parameter('Isp', val=1600.0, units='s', opt=False, targets=['Isp']) + phase.add_parameter('throttle', val=1.0, opt=False, targets=['throttle']) + + phase.add_boundary_constraint('h', loc='final', equals=height, scaler=1.0E-3) + phase.add_boundary_constraint('aero.mach', loc='final', equals=1.0) + phase.add_boundary_constraint('gam', loc='final', equals=0.0) + + phase.add_path_constraint(name='h', lower=100.0, upper=height, ref=height) + phase.add_path_constraint(name='aero.mach', lower=0.1, upper=1.8) + + # Unnecessary but included to test capability + phase.add_path_constraint(name='alpha', lower=-8, upper=8) + phase.add_path_constraint(name=f'{time_name}', lower=0, upper=400) + phase.add_path_constraint(name=f'{time_name}_phase', lower=0, upper=400) + + # Minimize time at the end of the phase + phase.add_objective(time_name, loc='final', ref=1.0) + + # test mixing wildcard ODE variable expansion and unit overrides + phase.add_timeseries_output(['aero.*', 'prop.thrust', 'prop.m_dot'], + units={'aero.f_lift': 'lbf', 'prop.thrust': 'lbf'}) + + # test adding rate as timeseries output + if add_rate: + phase.add_timeseries_rate_output('aero.mach') + + p.model.linear_solver = om.DirectSolver() + + p.setup(check=True, force_alloc_complex=force_alloc_complex) + + p['traj.phase0.t_initial'] = 0.0 + p['traj.phase0.t_duration'] = 350.0 + + p['traj.phase0.states:r'] = phase.interp('r', [0.0, 111319.54]) + p['traj.phase0.states:h'] = phase.interp('h', [100.0, 20000.0]) + p['traj.phase0.states:v'] = phase.interp('v', [135.964, 283.159]) + p['traj.phase0.states:gam'] = phase.interp('gam', [0.0, 0.0]) + p['traj.phase0.states:m'] = phase.interp('m', [19030.468, 16841.431]) + p['traj.phase0.controls:alpha'] = phase.interp('alpha', [0.0, 0.0]) + + dm.run_problem(p, simulate=True) + + return p + + +def checkDeviation(filenum=0): + heights = [16e3]*2 + times_to_climb = [] + timeseries_pts = {'h': [], 'r': [], 'thrust': [], 'v': []} + prefix = 'traj.phase0.timeseries.' + + for height in heights: + p = min_time_climb(height=height) + sol = om.CaseReader('dymos_solution.db').get_case('final') + sim = om.CaseReader('dymos_simulation.db').get_case('final') + times_to_climb.append(p.get_val('traj.phase0.timeseries.time', + units='s')[-1][0]) + for var, varlst in timeseries_pts.items(): + varlst.append(sol.get_val(prefix+var)) + + print("\n\n=======================================") + with open(f'checkdiff_{filenum}.txt', 'w') as fp: + fp.write(f'time to climb: {times_to_climb[0]: .4f}\n\n') + fp.write(str(timeseries_pts)) + + for key in timeseries_pts.keys(): + timeseries_pts[key] = np.array( + timeseries_pts[key][1:]) - timeseries_pts[key][0] + print(f"Max difference in {key}: {np.max(timeseries_pts[key]):.2f}") + + print(f"Time to climb: {times_to_climb[0]:.2f}") + print(f"Standard deviation of time to climb in {len(heights)}" + + f" cases: {np.std(times_to_climb):.2f}") + for key in timeseries_pts.keys(): + print(f"Standard deviation of {key} in {len(heights)} cases:" + + f" {np.std(timeseries_pts[key]):.2f}") + + +def multiHeightTest(): + heights = [8e3, 10e3] + prefix = 'traj.phase0.timeseries.' + plotvars = {'r': ['h'], 'time': ['v', 'thrust', 'm_dot', 'alpha']} + varnames = {prefix+x: [prefix+y for y in ylst] for x, ylst in plotvars.items()} + numplots = sum([len(item) for item in plotvars.values()]) + data = {f'h{i}': {} for i in range(len(heights))} + + for j, height in enumerate(heights): + p = min_time_climb(height=height) + wing_area = p.get_val('traj.phase0.parameters:S', units='m**2')[0] + sol = om.CaseReader('dymos_solution.db').get_case('final') + sim = om.CaseReader('dymos_simulation.db').get_case('final') + + print("\n\n=======================================") + print(f"Time to climb {height/1e3} km: " + + f"{p.get_val('traj.phase0.timeseries.time',units='s')[-1][0]:.2f}" + + f" s with wing area: {wing_area} sqm") + + for xname in varnames.keys(): + xsol = sol.get_val(xname) + xsim = sim.get_val(xname) + if not xname in data.keys(): + data[f'h{j}'][xname] = {'x': (xsol, xsim), 'y': []} + for yname in varnames[xname]: + if not 'yname' in data[f'h{j}'][xname].keys(): + data[f'h{j}'][xname]['yname'] = [yname] + else: + data[f'h{j}'][xname]['yname'].append(yname) + ysol = sol.get_val(yname) + ysim = sim.get_val(yname) + data[f'h{j}'][xname]['y'].append((ysol, ysim)) + + colors = ['r', 'b'] + for j in range(len(heights)): + datadict = data[f'h{j}'] + i = 1 + for xname in datadict.keys(): + xsol, xsim = datadict[xname]['x'] + for (ysol, ysim), yname in zip(datadict[xname]['y'], datadict[xname]['yname']): + ax = plt.subplot(int(numplots/2), numplots-int(numplots/2), i) + if max(ysim) > 1e3: + ysol, ysim = ysol/1e3, ysim/1e3 + plt.plot(xsol, ysol, f'{colors[j]}o', fillstyle='none') + plt.plot(xsim, ysim, colors[j]) + plt.xlabel(xname.split(prefix)[1]) + plt.ylabel(yname.split(prefix)[1]) + if j == 0: + plt.grid(visible=True) + i += 1 + plt.show() + + +"""It seems that when the dymos problem is run multiple times within a single +run of this script, the output values are all the same for all timeseries. + +But when the script itself is run again, these values can differ very largely, +optimization takes a very different number of iterations, and the profile looks very +different. Time to climb is also different.""" +if __name__ == '__main__': + if len(sys.argv) > 1 and 'filenum' in sys.argv[1]: + checkDeviation(filenum=sys.argv[1].split('filenum=')[1]) + # multiHeightTest() + + +""" +var names + 'traj.phase0.controls:alpha' + 'traj.phase0.t_initial' + 'traj.phase0.t_duration' + 'traj.phase0.parameters:S' + 'traj.phase0.parameters:Isp' + 'traj.phase0.parameters:throttle' + 'traj.phase0.collocation_constraint.defects:gam' + 'traj.phase0.control_rates:alpha_rate' + 'traj.phase0.control_rates:alpha_rate2' + 'traj.phase0.control_values:alpha' + 'traj.phase0.states:gam' + 'traj.phase0.states:h' + 'traj.phase0.states:m' + 'traj.phase0.states:r' + 'traj.phase0.states:v' + 'traj.phase0.interleave_comp.all_values:CD' + 'traj.phase0.parameter_vals:Isp' + 'traj.phase0.parameter_vals:S' + 'traj.phase0.parameter_vals:throttle' + 'traj.phase0.t_duration_val' + 'traj.phase0.t_initial_val' + 'traj.phase0.rhs_col.aero.CD' + 'traj.phase0.rhs_disc.aero.CL' + 'traj.phase0.rhs_disc.aero.CD0' + 'traj.phase0.rhs_disc.aero.CLa' + 'traj.phase0.rhs_disc.aero.kappa' + 'traj.phase0.rhs_disc.aero.f_drag' + 'traj.phase0.rhs_disc.aero.f_lift' + 'traj.phase0.rhs_disc.aero.mach' + 'traj.phase0.rhs_disc.aero.q' + 'traj.phase0.rhs_disc.atmos.drhos_dh' + 'traj.phase0.rhs_disc.atmos.pres' + 'traj.phase0.rhs_disc.atmos.rho' + 'traj.phase0.rhs_disc.atmos.sos' + 'traj.phase0.rhs_disc.atmos.temp' + 'traj.phase0.rhs_disc.atmos.viscosity' + 'traj.phase0.rhs_disc.flight_dynamics.gam_dot' + 'traj.phase0.rhs_disc.flight_dynamics.h_dot' + 'traj.phase0.rhs_disc.flight_dynamics.r_dot' + 'traj.phase0.rhs_disc.flight_dynamics.v_dot' + 'traj.phase0.rhs_disc.prop.max_thrust' + 'traj.phase0.rhs_disc.prop.m_dot' + 'traj.phase0.rhs_disc.prop.thrust' + 'traj.phase0.state_interp.state_col:gam': array([[ 0.0702449 ], + 'traj.phase0.state_interp.state_col:h' + 'traj.phase0.state_interp.state_col:m' + 'traj.phase0.state_interp.state_col:r' + 'traj.phase0.state_interp.state_col:v' + 'traj.phase0.dt_dstau' + 'traj.phase0.t' + 'traj.phase0.t_phase' + 'traj.phase0.timeseries.CD': array([[0.0195346 ], + 'traj.phase0.timeseries.CD0' + 'traj.phase0.timeseries.CL' + 'traj.phase0.timeseries.CLa' + 'traj.phase0.timeseries.alpha' + 'traj.phase0.timeseries.f_drag' + 'traj.phase0.timeseries.f_lift' + 'traj.phase0.timeseries.gam' + 'traj.phase0.timeseries.h' + 'traj.phase0.timeseries.kappa' + 'traj.phase0.timeseries.m' + 'traj.phase0.timeseries.m_dot' + 'traj.phase0.timeseries.mach' + 'traj.phase0.timeseries.q' + 'traj.phase0.timeseries.r' + 'traj.phase0.timeseries.thrust' + 'traj.phase0.timeseries.time' + 'traj.phase0.timeseries.time_phase' + 'traj.phase0.timeseries.v' + + """ From 6a32d971b4bf38f8578e8f1516e86b2d65067bdc Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 31 Jul 2024 09:12:29 -0400 Subject: [PATCH 017/113] renamed files, added copy model cannonball example --- AvCannonball.html | 14840 ---------------- AvCannonball_noconnect.html | 14840 ---------------- cannonball_copy.py | 297 - checkdiff_0.txt | 226 +- checkdiff_1.txt | 226 +- min_time_climb.py | 5 +- ...onball.py => multI_cannonball_copyparts.py | 4 +- multi_aviary_copymodel.py | 449 + multimission.py => multi_aviary_submodel.py | 0 multi_cannonball_copymodel.py | 407 + multi_mission_importTraj_N2.html | 14840 ---------------- multitraj.py | 181 - 12 files changed, 1087 insertions(+), 45228 deletions(-) delete mode 100644 AvCannonball.html delete mode 100644 AvCannonball_noconnect.html delete mode 100644 cannonball_copy.py rename avcannonball.py => multI_cannonball_copyparts.py (99%) create mode 100644 multi_aviary_copymodel.py rename multimission.py => multi_aviary_submodel.py (100%) create mode 100644 multi_cannonball_copymodel.py delete mode 100644 multi_mission_importTraj_N2.html delete mode 100644 multitraj.py diff --git a/AvCannonball.html b/AvCannonball.html deleted file mode 100644 index e29612ed5..000000000 --- a/AvCannonball.html +++ /dev/null @@ -1,14840 +0,0 @@ - - - -OpenMDAO Model Hierarchy and N2 diagram - - - - - - - - - - - - - - - - - -
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-
- - - - - - - diff --git a/cannonball_copy.py b/cannonball_copy.py deleted file mode 100644 index 9f1d81303..000000000 --- a/cannonball_copy.py +++ /dev/null @@ -1,297 +0,0 @@ -from os import stat -import numpy as np -from scipy.interpolate import interp1d -import matplotlib.pyplot as plt -import openmdao.api as om -import dymos as dm -from dymos.models.atmosphere.atmos_1976 import USatm1976Data - -""" -Currently has linked sizing and motion ODEs, want to add ability to have -multiple trajectories (and associated ODEs) that are linked with the same -sizing class. radii/density etc can be defined as 1xn inputs, with n corresponding -to num of missions. - -Additionally need to incorporate some output into a compound objective that is optimized, -aside from each mission optimizing for max range. Could for example assign $/kg of material. - -Could also add a "fuel" parameter which can then be minimized. -""" - - -class CannonballSizing(om.ExplicitComponent): - def setup(self): - self.add_input(name='radius', val=1.0, units='m') - self.add_input(name='dens', val=7870., units='kg/m**3') - - self.add_output(name='mass', shape=(1,), units='kg') - self.add_output(name='S', shape=(1,), units='m**2') - self.add_output(name='price', shape=(1,), units='USD') - - self.declare_partials(of='mass', wrt='dens') - self.declare_partials(of='mass', wrt='radius') - self.declare_partials(of='S', wrt='radius') - self.declare_partials(of='price', wrt='radius') - self.declare_partials(of='price', wrt='dens') - - def compute(self, inputs, outputs): - radius = inputs['radius'] - dens = inputs['dens'] - outputs['mass'] = (4/3.) * dens * np.pi * radius ** 3 - outputs['S'] = np.pi * radius ** 2 - outputs['price'] = (4/3.) * dens * np.pi * radius ** 3 * 10 # $10 per kg - - def compute_partials(self, inputs, partials): - radius = inputs['radius'] - dens = inputs['dens'] - partials['mass', 'dens'] = (4/3.) * np.pi * radius ** 3 - partials['mass', 'radius'] = 4. * dens * np.pi * radius ** 2 - partials['S', 'radius'] = 2 * np.pi * radius - partials['price', 'dens'] = (4/3.) * np.pi * radius ** 3 * 10 - partials['price', 'radius'] = 4. * dens * np.pi * radius ** 2 * 10 - - -class CannonballODE(om.ExplicitComponent): - def initialize(self): - self.options.declare('num_nodes', types=int) - - def setup(self): - nn = self.options['num_nodes'] - # static params - self.add_input('m', units='kg') - self.add_input('S', units='m**2') - self.add_input('CD', 0.5) - - # time varying inputs - self.add_input('h', units='m', shape=nn) - self.add_input('v', units='m/s', shape=nn) - self.add_input('gam', units='rad', shape=nn) - - # state rates - self.add_output('v_dot', shape=nn, units='m/s**2', - tags=['dymos.state_rate_source:v']) - self.add_output('gam_dot', shape=nn, units='rad/s', - tags=['dymos.state_rate_source:gam']) - self.add_output('h_dot', shape=nn, units='m/s', - tags=['dymos.state_rate_source:h']) - self.add_output('r_dot', shape=nn, units='m/s', - tags=['dymos.state_rate_source:r']) - self.add_output('ke', shape=nn, units='J') - - # Ask OpenMDAO to compute the partial derivatives using complex-step - # with a partial coloring algorithm for improved performance, and use - # a graph coloring algorithm to automatically detect the sparsity pattern. - self.declare_coloring(wrt='*', method='cs') - - alt_data = USatm1976Data.alt * om.unit_conversion('ft', 'm')[0] - rho_data = USatm1976Data.rho * om.unit_conversion('slug/ft**3', 'kg/m**3')[0] - self.rho_interp = interp1d(np.array(alt_data, dtype=complex), - np.array(rho_data, dtype=complex), - kind='linear') - - def compute(self, inputs, outputs): - - gam = inputs['gam'] - v = inputs['v'] - h = inputs['h'] - m = inputs['m'] - S = inputs['S'] - CD = inputs['CD'] - - GRAVITY = 9.80665 # m/s**2 - - # handle complex-step gracefully from the interpolant - if np.iscomplexobj(h): - rho = self.rho_interp(inputs['h']) - else: - rho = self.rho_interp(inputs['h']).real - - q = 0.5*rho*inputs['v']**2 - qS = q * S - D = qS * CD - cgam = np.cos(gam) - sgam = np.sin(gam) - outputs['v_dot'] = - D/m-GRAVITY*sgam - outputs['gam_dot'] = -(GRAVITY/v)*cgam - outputs['h_dot'] = v*sgam - outputs['r_dot'] = v*cgam - outputs['ke'] = 0.5*m*v**2 - - -# ODEs are unique to each traj created -def createTrajectory(ke_max): - traj = dm.Trajectory() - transcription = dm.Radau(num_segments=5, order=3, compressed=True) - ascent = dm.Phase(ode_class=CannonballODE, transcription=transcription) - traj.add_phase('ascent', ascent) - - transcription = dm.GaussLobatto(num_segments=5, order=3, compressed=True) - descent = dm.Phase(ode_class=CannonballODE, transcription=transcription) - traj.add_phase('descent', descent) - - for phase in (ascent, descent): - is_ascent = phase.name == "ascent" - phase.set_time_options(fix_initial=True if is_ascent else False, - duration_bounds=(1, 100), duration_ref=100, units='s') - phase.set_state_options('r', fix_initial=is_ascent, fix_final=False) - phase.set_state_options('h', fix_initial=is_ascent, fix_final=not is_ascent) - phase.set_state_options('gam', fix_initial=False, fix_final=is_ascent) - phase.set_state_options('v', fix_initial=False, fix_final=False) - phase.add_parameter('S', units='m**2', static_target=True, val=0.005) - phase.add_parameter('m', units='kg', static_target=True, val=1.0) - phase.add_parameter('price', units='USD', static_target=True, val=10) - phase.add_parameter('CD', units=None, static_target=True, val=0.5) - - # descent.add_objective('r', loc='final', scaler=-1.0) # negative means to maximize - for param in ('CD', 'm', 'S', 'price'): - traj.add_parameter(param, static_target=True) - - # Link Phases (link time and all state variables) - traj.link_phases(phases=['ascent', 'descent'], vars=['*']) - # have to set muzzle energy here before setup for sim to run properly - ascent.add_boundary_constraint('ke', loc='initial', - upper=ke_max, lower=0, ref=100000) - return traj, ascent, descent - - -p = om.Problem(model=om.Group()) - -p.driver = om.ScipyOptimizeDriver() -p.driver.options['optimizer'] = 'SLSQP' -p.driver.declare_coloring() - -kes = [4e5, 5e5, 6e5] -# 2:1 ratio (or 1:2) causes results that essentially don't optimize the 1 mission, -# 1.01 works, 1.009 doesn't -# 2:1:1 works?! - may be related some normalization/bounds issue -weights = [2.1, 1.5, 1.1] -num_trajs = len(kes) - -p.model.add_subsystem(f"sizing_comp", CannonballSizing(), - promotes_inputs=['radius', 'dens']) - -p.model.set_input_defaults('dens', val=7.87, units='g/cm**3') -p.model.add_design_var('radius', lower=0.01, upper=0.10, - ref0=0.01, ref=0.10, units='m') - -trajs, ascents, descents = [], [], [] -for i, ke in enumerate(kes): - traj, ascent, descent = createTrajectory(ke) - p.model.add_subsystem(f"traj_{i}", traj) - - # Issue Connections - p.model.connect(f"sizing_comp.mass", f"traj_{i}.parameters:m") - p.model.connect(f"sizing_comp.S", f"traj_{i}.parameters:S") - p.model.connect(f"sizing_comp.price", f"traj_{i}.parameters:price") - trajs.append(traj) - ascents.append(ascent) - descents.append(descent) - -ranges = [f"r{i}" for i in range(num_trajs)] -weighted_sum_str = "+".join([f"{weight}*{r}" for r, weight in zip(ranges, weights)]) -p.model.add_subsystem('compoundComp', om.ExecComp("compound_range="+weighted_sum_str), - promotes=['compound_range', *ranges]) - -for i in range(num_trajs): - p.model.connect(f"traj_{i}.descent.states:r", ranges[i], src_indices=-1) - -p.model.add_objective('compound_range', scaler=-1) - - -# A linear solver at the top level can improve performance. -p.model.linear_solver = om.DirectSolver() -p.setup() - -p.set_val('radius', 0.05, units='m') -p.set_val('dens', 7.87, units='g/cm**3') - -for i, (ascent, descent) in enumerate(zip(ascents, descents)): - p.set_val(f"traj_{i}.parameters:CD", 0.5) - - p.set_val(f"traj_{i}.ascent.t_initial", 0.0) - p.set_val(f"traj_{i}.ascent.t_duration", 10.0) - # list is initial and final, based on phase info some are fixed others are not - p.set_val(f"traj_{i}.ascent.states:r", ascent.interp('r', [0, 100])) - p.set_val(f'traj_{i}.ascent.states:h', ascent.interp('h', [0, 100])) - p.set_val(f'traj_{i}.ascent.states:v', ascent.interp('v', [200, 150])) - p.set_val(f'traj_{i}.ascent.states:gam', ascent.interp('gam', [25, 0]), units='deg') - - p.set_val(f'traj_{i}.descent.t_initial', 10.0) - p.set_val(f'traj_{i}.descent.t_duration', 10.0) - - p.set_val(f'traj_{i}.descent.states:r', descent.interp('r', [100, 200])) - p.set_val(f'traj_{i}.descent.states:h', descent.interp('h', [100, 0])) - p.set_val(f'traj_{i}.descent.states:v', descent.interp('v', [150, 200])) - p.set_val(f'traj_{i}.descent.states:gam', - descent.interp('gam', [0, -45]), units='deg') - - -dm.run_problem(p, simulate=True) -sol = om.CaseReader('dymos_solution.db').get_case('final') -sim = om.CaseReader('dymos_simulation.db').get_case('final') - - -def plotstuff(): - print("\n\n=================================================") - print( - f"Optimized {num_trajs} trajectories with weights: {', '.join(map(str,weights))}") - rad = p.get_val('radius', units='cm')[0] - mass = p.get_val('sizing_comp.mass', units='kg')[0] - price = p.get_val('sizing_comp.price', units='USD')[0] - area = p.get_val('sizing_comp.S', units='cm**2')[0] - print("\nOptimal Cannonball Description:") - print( - f"\tRadius: {rad:.2f} cm, Mass: {mass:.2f} kg, Price: ${price:.2f}, Area: {area:.2f} sqcm") - - print("\nOptimal Trajectory Descriptions:") - for i, ke in enumerate(kes): - angle = p.get_val(f'traj_{i}.ascent.timeseries.gam', units='deg')[0, 0] - max_range = p.get_val(f'traj_{i}.descent.timeseries.r')[-1, 0] - - print( - f"\tKE: {ke/1e3:.2f} KJ, Launch Angle: {angle:.2f} deg, Max Range: {max_range:.2f} m") - - # fig, axes = plt.subplots(nrows=1, ncols=1, figsize=(10, 6)) - # time_imp = {'ascent': p.get_val('traj_0.ascent.timeseries.time'), - # 'descent': p.get_val('traj_0.descent.timeseries.time')} - # time_exp = {'ascent': sim.get_val('traj_0.ascent.timeseries.time'), - # 'descent': sim.get_val('traj_0.descent.timeseries.time')} - # r_imp = {'ascent': p.get_val('traj_0.ascent.timeseries.r'), - # 'descent': p.get_val('traj_0.descent.timeseries.r')} - # r_exp = {'ascent': sim.get_val('traj_0.ascent.timeseries.r'), - # 'descent': sim.get_val('traj_0.descent.timeseries.r')} - # h_imp = {'ascent': p.get_val('traj_0.ascent.timeseries.h'), - # 'descent': p.get_val('traj_0.descent.timeseries.h')} - # h_exp = {'ascent': sim.get_val('traj_0.ascent.timeseries.h'), - # 'descent': sim.get_val('traj_0.descent.timeseries.h')} - - # axes.plot(r_imp['ascent'], h_imp['ascent'], 'bo') - # axes.plot(r_imp['descent'], h_imp['descent'], 'ro') - # axes.plot(r_exp['ascent'], h_exp['ascent'], 'b--') - # axes.plot(r_exp['descent'], h_exp['descent'], 'r--') - - # axes.set_xlabel('range (m)') - # axes.set_ylabel('altitude (m)') - # axes.grid(True) - - # fig, axes = plt.subplots(nrows=4, ncols=1, figsize=(10, 6)) - # states = ['r', 'h', 'v', 'gam'] - # for i, state in enumerate(states): - # x_imp = {'ascent': sol.get_val(f'traj_0.ascent.timeseries.{state}'), - # 'descent': sol.get_val(f'traj_0.descent.timeseries.{state}')} - - # x_exp = {'ascent': sim.get_val(f'traj_0.ascent.timeseries.{state}'), - # 'descent': sim.get_val(f'traj_0.descent.timeseries.{state}')} - - # axes[i].set_ylabel(state) - # axes[i].grid(True) - - # axes[i].plot(time_imp['ascent'], x_imp['ascent'], 'bo') - # axes[i].plot(time_imp['descent'], x_imp['descent'], 'ro') - # axes[i].plot(time_exp['ascent'], x_exp['ascent'], 'b--') - # axes[i].plot(time_exp['descent'], x_exp['descent'], 'r--') - - # plt.show() - - -plotstuff() diff --git a/checkdiff_0.txt b/checkdiff_0.txt index 73765b1a6..f83bd9f6c 100644 --- a/checkdiff_0.txt +++ b/checkdiff_0.txt @@ -1,115 +1,115 @@ -time to climb: 255.4723 +time to climb: 217.2520 {'h': [array([[ 100. ], - [ 385.84286893], - [ 2524.05538825], - [ 6330.19786708], - [ 8398.09721022], - [ 8398.09721022], - [ 9496.91321874], - [ 8224.65719818], - [ 7524.51936893], - [ 7967.69790418], - [ 7967.69790418], - [ 7685.19578827], - [ 9594.55531382], - [14749.31150762], - [16000. ]]), array([[ 100. ], - [ 385.84286893], - 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p.driver.declare_coloring() + # p.driver.declare_coloring() if optimizer == 'SNOPT': p.driver.opt_settings['Major iterations limit'] = 1000 @@ -117,7 +117,7 @@ def min_time_climb(height=20e3, def checkDeviation(filenum=0): - heights = [16e3]*2 + heights = [10e3]*2 times_to_climb = [] timeseries_pts = {'h': [], 'r': [], 'thrust': [], 'v': []} prefix = 'traj.phase0.timeseries.' @@ -209,6 +209,7 @@ def multiHeightTest(): optimization takes a very different number of iterations, and the profile looks very different. Time to climb is also different.""" if __name__ == '__main__': + np.random.seed(0) if len(sys.argv) > 1 and 'filenum' in sys.argv[1]: checkDeviation(filenum=sys.argv[1].split('filenum=')[1]) # multiHeightTest() diff --git a/avcannonball.py b/multI_cannonball_copyparts.py similarity index 99% rename from avcannonball.py rename to multI_cannonball_copyparts.py index bb48ec9de..6ae9ea40f 100644 --- a/avcannonball.py +++ b/multI_cannonball_copyparts.py @@ -312,7 +312,7 @@ def runAvCannonball(kes=[4e3], weights=[1], makeN2=False): descent.interp('gam', [0, -45]), units='deg') if makeN2: - om.n2(super_prob, outfile='AvCannonball.html') + om.n2(super_prob, outfile='multi_cannonball_copyparts.html') dm.run_problem(super_prob) return super_prob, prefix, num_trajs, kes, weights @@ -421,7 +421,7 @@ def multiTestCase(makeN2=False): if __name__ == '__main__': - # if run as python avcannonball.py n2, it will create an N2 + # if run as python multi_cannonball_copyparts.py n2, it will create an N2 makeN2 = False singlerun = True if len(sys.argv) > 1: diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py new file mode 100644 index 000000000..3cdbe1e77 --- /dev/null +++ b/multi_aviary_copymodel.py @@ -0,0 +1,449 @@ +""" +Goal: use single aircraft description but optimize it for multiple missions simultaneously, +i.e. all missions are on the range-payload line instead of having excess performance +Aircraft csv: defines plane, but also defines payload (passengers, cargo) which can vary with mission + These will have to be specified in some alternate way such as a list correspond to mission # +Phase info: defines a particular mission, will have multiple phase infos +""" +import sys +import warnings +import aviary.api as av +import openmdao.api as om +import dymos as dm +import numpy as np +from aviary.variable_info.enums import ProblemType +from c5_ferry_phase_info import phase_info as c5_ferry_phase_info +from c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info +from c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info +from aviary.variable_info.variable_meta_data import _MetaData as MetaData +from aviary.variable_info.variables import Mission, Dynamic +from aviary.interface.methods_for_level2 import wrapped_convert_units +from aviary.variable_info.enums import EquationsOfMotion + +TWO_DEGREES_OF_FREEDOM = EquationsOfMotion.TWO_DEGREES_OF_FREEDOM +HEIGHT_ENERGY = EquationsOfMotion.HEIGHT_ENERGY +SOLVED_2DOF = EquationsOfMotion.SOLVED_2DOF + +# "comp?.a can be used to reference multiple comp1.a comp2.a etc" + + +class MultiMissionProblem(om.Problem): + def __init__(self, planes, phase_infos, weights): + super().__init__() + self.num_missions = len(planes) + # phase infos and planes length must match - this maybe unnecessary if + # different planes (payloads) fly same mission (say pax vs cargo) + # or if same payload flies 2 different missions (altitude/mach differences) + if self.num_missions != len(phase_infos): + raise Exception("Length of planes and phase_infos must be the same!") + + # if fewer weights than planes are provided, assign equal weights for all planes + if len(weights) < self.num_missions: + weights = [1]*self.num_missions + # if more weights than planes, raise exception + elif len(weights) > self.num_missions: + raise Exception("Length of weights cannot exceed length of planes!") + self.weights = weights + + self.group_prefix = 'group' + self.probs = [] + # define individual aviary problems + for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): + prob = av.AviaryProblem() + prob.load_inputs(plane, phase_info) + prob.check_and_preprocess_inputs() + prob.add_pre_mission_systems() + prob.add_phases() + prob.add_post_mission_systems() + prob.link_phases() + prob.add_design_variables() # should not work at super prob level + self.probs.append(prob) + + self.model.add_subsystem( + self.group_prefix + f'_{i}', prob.model, + promotes=['mission:design:gross_mass']) + + def add_design_variables(self): + self.model.add_design_var('mission:design:gross_mass', lower=10., upper=900e3) + + def add_driver(self): + self.driver = om.ScipyOptimizeDriver() + self.driver.options['optimizer'] = 'SLSQP' + self.driver.declare_coloring() + self.model.linear_solver = om.DirectSolver() + + def add_objective(self): + weights = self.weights + fuel_burned_vars = [f"fuel_{i}" for i in range(self.num_missions)] + weighted_str = "+".join([f"{fuel}*{weight}" + for fuel, weight in zip(fuel_burned_vars, weights)]) + # weighted_str looks like: fuel_0 * weight[0] + fuel_1 * weight[1] + + # adding compound execComp to super problem + self.model.add_subsystem('compound_fuel_burn_objective', om.ExecComp( + "compound = "+weighted_str), promotes=["compound", *fuel_burned_vars]) + + for i in range(self.num_missions): + # connecting each subcomponent's fuel burn to super problem's unique fuel variables + self.model.connect( + self.group_prefix+f"_{i}.mission:summary:fuel_burned", f"fuel_{i}") + self.model.add_objective('compound') + + def setup_wrapper(self): + """Wrapper for om.Problem setup with warning ignoring and setting options""" + for prob in self.probs: + prob.model.options['aviary_options'] = prob.aviary_inputs + prob.model.options['aviary_metadata'] = prob.meta_data + prob.model.options['phase_info'] = prob.phase_info + + # Aviary's problem setup wrapper uses these ignored warnings to suppress + # some warnings related to variable promotion. Replicating that here with + # setup for the super problem + with warnings.catch_warnings(): + warnings.simplefilter("ignore", om.OpenMDAOWarning) + warnings.simplefilter("ignore", om.PromotionWarning) + self.setup() + + def create_N2(self, outfile='aviary_multi_traj.html'): + om.n2(self, outfile=outfile) + + def initvals(self): + for i, prob in enumerate(self.probs): + self.set_val(self.group_prefix + + f'_{i}.aircraft:design:landing_to_takeoff_mass_ratio', 0.5) + # Grab the trajectory object from the model + traj = prob.model.traj + + # Determine which phases to loop over, fetching them from the trajectory + phase_items = traj._phases.items() + + # Loop over each phase and set initial guesses for the state and control variables + for idx, (phase_name, phase) in enumerate(phase_items): + # If not, fetch the initial guesses specific to the phase + # check if guesses exist for this phase + if "initial_guesses" in prob.phase_info[phase_name]: + guesses = prob.phase_info[phase_name]['initial_guesses'] + else: + guesses = {} + + # ||||||||||||| _add_subsystem_guesses + # Get all subsystems associated with the phase + all_subsystems = prob._get_all_subsystems( + prob.phase_info[phase_name]['external_subsystems']) + + # Loop over each subsystem + for subsystem in all_subsystems: + # Fetch the initial guesses for the subsystem + initial_guesses = subsystem.get_initial_guesses() + + # Loop over each guess + for key, val in initial_guesses.items(): + # Identify the type of the guess (state or control) + type = val.pop('type') + if 'state' in type: + path_string = 'states' + elif 'control' in type: + path_string = 'controls' + + # Process the guess variable (handles array interpolation) + val['val'] = prob._process_guess_var(val['val'], key, phase) + + # Set the initial guess in the problem + self.set_val( + self.group_prefix + + f'_{i}.traj.{phase_name}.{path_string}:{key}', **val) + + # Set initial guesses for states and controls for each phase + + # |||||||||||||||||||||| _add_guesses + # If using the GASP model, set initial guesses for the rotation mass and flight duration + if prob.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): + control_keys = ["mach", "altitude"] + state_keys = ["mass", Dynamic.Mission.DISTANCE] + prob_keys = ["tau_gear", "tau_flaps"] + + # for the simple mission method, use the provided initial and final mach and altitude values from phase_info + if prob.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): + initial_altitude = wrapped_convert_units( + prob.phase_info[phase_name]['user_options'] + ['initial_altitude'], + 'ft') + final_altitude = wrapped_convert_units( + prob.phase_info[phase_name]['user_options']['final_altitude'], 'ft') + initial_mach = prob.phase_info[phase_name]['user_options'][ + 'initial_mach'] + final_mach = prob.phase_info[phase_name]['user_options'][ + 'final_mach'] + + guesses["mach"] = ([initial_mach[0], final_mach[0]], "unitless") + guesses["altitude"] = ([initial_altitude, final_altitude], 'ft') + + if prob.mission_method is HEIGHT_ENERGY: + # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds + if 'time' not in guesses: + initial_bounds = wrapped_convert_units( + prob.phase_info[phase_name]['user_options']['initial_bounds'], 's') + duration_bounds = wrapped_convert_units( + prob.phase_info[phase_name]['user_options']['duration_bounds'], 's') + guesses["time"] = ([np.mean(initial_bounds[0]), np.mean( + duration_bounds[0])], 's') + + # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds + if 'time' not in guesses: + initial_bounds = prob.phase_info[phase_name]['user_options'][ + 'initial_bounds'] + duration_bounds = prob.phase_info[phase_name]['user_options'][ + 'duration_bounds'] + # Add a check for the initial and duration bounds, raise an error if they are not consistent + if initial_bounds[1] != duration_bounds[1]: + raise ValueError( + f"Initial and duration bounds for {phase_name} are not consistent.") + guesses["time"] = ([np.mean(initial_bounds[0]), np.mean( + duration_bounds[0])], initial_bounds[1]) + + for guess_key, guess_data in guesses.items(): + val, units = guess_data + + # Set initial guess for time variables + if 'time' == guess_key and prob.mission_method is not SOLVED_2DOF: + self.set_val( + self.group_prefix + f'_{i}.traj.{phase_name}.t_initial', + val[0], + units=units) + self.set_val( + self.group_prefix + f'_{i}.traj.{phase_name}.t_duration', + val[1], + units=units) + + else: + # Set initial guess for control variables + if guess_key in control_keys: + try: + self.set_val(self.group_prefix + + f'_{i}.traj.{phase_name}.controls:{guess_key}', + prob._process_guess_var( + val, guess_key, phase), + units=units) + except KeyError: + try: + self.set_val( + self.group_prefix + + f'_{i}.traj.{phase_name}.polynomial_controls:{guess_key}', + prob._process_guess_var(val, guess_key, phase), + units=units) + except KeyError: + self.set_val( + self.group_prefix + + f'_{i}.traj.{phase_name}.bspline_controls:{guess_key}', + prob._process_guess_var(val, guess_key, phase), + units=units) + + if guess_key in control_keys: + pass + # Set initial guess for state variables + elif guess_key in state_keys: + self.set_val(self.group_prefix + + f'_{i}.traj.{phase_name}.states:{guess_key}', + prob._process_guess_var( + val, guess_key, phase), + units=units) + elif guess_key in prob_keys: + self.set_val( + self.group_prefix+f'_{i}.'+guess_key, val, units=units) + elif ":" in guess_key: + self.set_val( + self.group_prefix + f'_{i}.traj.{phase_name}.{guess_key}', + prob._process_guess_var(val, guess_key, phase), + units=units) + else: + # raise error if the guess key is not recognized + raise ValueError( + f"Initial guess key {guess_key} in {phase_name} is not recognized.") + + # We need some special logic for these following variables because GASP computes + # initial guesses using some knowledge of the mission duration and other variables + # that are only available after calling `create_vehicle`. Thus these initial guess + # values are not included in the `phase_info` object. + + base_phase = phase_name + if 'mass' not in guesses: + mass_guess = prob.aviary_inputs.get_val( + Mission.Design.GROSS_MASS, units='lbm') + # Set the mass guess as the initial value for the mass state variable + self.set_val(self.group_prefix+f'_{i}.traj.{phase_name}.states:mass', + mass_guess, units='lbm') + + # if 'time' not in guesses: + # # Determine initial time and duration guesses depending on the phase name + # if 'desc1' == base_phase: + # t_initial = flight_duration*.9 + # t_duration = flight_duration*.04 + # elif 'desc2' in base_phase: + # t_initial = flight_duration*.94 + # t_duration = 5000 + # # Set the time guesses as the initial values for the time-related trajectory variables + # self.set_val(f"traj.{phase_name}.t_initial", + # t_initial, units='s') + # self.set_val(f"traj.{phase_name}.t_duration", + # t_duration, units='s') + + def run(self): + dm.run_problem(self) + + # def link_pre_post_traj(self): + # for i, prob in enumerate(self.probs): + # prefix = self.group_prefix+f'_{i}.' + + # self.model.connect(prefix + + # f'traj.{prob.regular_phases[-1]}.timeseries.distance', + # Mission.Summary.RANGE, src_indices=[-1], + # flat_src_indices=True) + + +if __name__ == '__main__': + makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False + planes = ['c5_maxpayload.csv', 'c5_intermediate.csv'] + phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] + weights = [1, 1] + super_prob = MultiMissionProblem(planes, phase_infos, weights) + super_prob.add_driver() + super_prob.add_design_variables() + super_prob.add_objective() + super_prob.setup_wrapper() + super_prob.initvals() + if makeN2: + super_prob.create_N2() + super_prob.run() + + +# ========================================================================= old code + # super_prob = om.Problem() + # num_missions = len(weights) + # probs = [] + # prefix = "problem_" + + # makeN2 = False + # if len(sys.argv) > 1: + # if "n2" in sys.argv: + # makeN2 = True + + # # define individual aviary problems + # for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): + # prob = av.AviaryProblem() + # prob.load_inputs(plane, phase_info) + # prob.check_and_preprocess_inputs() + # prob.add_pre_mission_systems() + # traj = prob.add_phases() # save dymos traj to add to super problem as a subsystem + # prob.add_post_mission_systems() + # prob.link_phases() # this is half working / connect statements from outside of traj to inside are failing + # prob.problem_type = ProblemType.ALTERNATE # adds summary gross mass as design var + # prob.add_design_variables() + # probs.append(prob) + + # group = om.Group() # this group will contain all the promoted aviary vars + # group.add_subsystem("pre", prob.pre_mission) + # group.add_subsystem("traj", traj) + # group.add_subsystem("post", prob.post_mission) + + # # setting defaults for these variables to suppress errors + # longlst = [ + # 'mission:summary:gross_mass', 'aircraft:wing:sweep', + # 'aircraft:wing:thickness_to_chord', 'aircraft:wing:area', + # 'aircraft:wing:taper_ratio', 'mission:design:gross_mass'] + # for var in longlst: + # group.set_input_defaults( + # var, val=MetaData[var]['default_value'], + # units=MetaData[var]['units']) + + # # add group and promote design gross mass (common input amongst multiple missions) + # # in this way it represents the MTOW + # super_prob.model.add_subsystem(prefix+f'{i}', group, promotes=[ + # 'mission:design:gross_mass']) + + # # add design gross mass as a design var + # super_prob.model.add_design_var( + # 'mission:design:gross_mass', lower=100e3, upper=1000e3) + + # for i in range(num_missions): + # # connecting each subcomponent's fuel burn to super problem's unique fuel variables + # super_prob.model.connect( + # prefix+f"{i}.mission:summary:fuel_burned", f"fuel_{i}") + + # # create constraint to force each mission's summary gross mass to not + # # exceed the common mission design gross mass (aka MTOW) + # super_prob.model.add_subsystem(f'MTOW_constraint{i}', om.ExecComp( + # 'mtow_resid = design_gross_mass - summary_gross_mass'), + # promotes=[('summary_gross_mass', prefix+f'{i}.mission:summary:gross_mass'), + # ('design_gross_mass', 'mission:design:gross_mass')]) + + # super_prob.model.add_constraint(f'MTOW_constraint{i}.mtow_resid', lower=0.) + + # # creating variable strings that will represent fuel burn from each mission + # fuel_burned_vars = [f"fuel_{i}" for i in range(num_missions)] + # weighted_str = "+".join([f"{fuel}*{weight}" + # for fuel, weight in zip(fuel_burned_vars, weights)]) + # # weighted_str looks like: fuel_0 * weight[0] + fuel_1 * weight[1] + + # # adding compound execComp to super problem + # super_prob.model.add_subsystem('compound_fuel_burn_objective', om.ExecComp( + # "compound = "+weighted_str), promotes=["compound", *fuel_burned_vars]) + + # super_prob.driver = om.ScipyOptimizeDriver() + # super_prob.driver.options['optimizer'] = 'SLSQP' + # super_prob.model.add_objective('compound') # output from execcomp goes here + + # with warnings.catch_warnings(): + # warnings.simplefilter("ignore", om.OpenMDAOWarning) + # warnings.simplefilter("ignore", om.PromotionWarning) + # super_prob.setup() + + # if makeN2: + # om.n2(super_prob, outfile="multi_mission_importTraj_N2.html") # create N2 diagram + + # # cannot use this b/c initial guesses (i.e. setval func) has to be called on super prob level + # # for prob in probs: + # # # prob.setup() + # # prob.set_initial_guesses() + + # # dm.run_problem(super_prob) + + +""" +Ferry mission phase info: +Times (min): 0, 50, 812, 843 + Alt (ft): 0, 29500, 32000, 0 + Mach: 0.3, 0.77, 0.77, 0.3 +Est. Range: 7001 nmi +Notes: 32k in 30 mins too fast for aviary, climb to low alt then slow rise through cruise + +Intermediate mission phase info: +Times (min): 0, 50, 560, 590 + Alt (ft): 0, 29500, 32000, 0 + Mach: 0.3, 0.77, 0.77, 0.3 +Est. Range: 4839 nmi + +Max Payload mission phase info: +Times (min): 0, 50, 260, 290 + Alt (ft): 0, 29500, 32000, 0 + Mach: 0.3, 0.77, 0.77, 0.3 +Est. Range: 2272 nmi + +Hard to find multiple payload/range values for FwFm (737), so use C-5 instead +Based on: + https://en.wikipedia.org/wiki/Lockheed_C-5_Galaxy#Specifications_(C-5M), + https://www.af.mil/About-Us/Fact-Sheets/Display/Article/1529718/c-5-abc-galaxy-and-c-5m-super-galaxy/ + +MTOW: 840,000 lb +Max Payload: 281,000 lb +Max Fuel: 341,446 lb +Empty Weight: 380,000 lb -> leaves 460,000 lb for fuel+payload (max fuel + max payload = 622,446 lb) + +Payload/range: + 281,000 lb payload -> 2,150 nmi range (AF.mil) [max payload case] + 120,000 lb payload -> 4,800 nmi range (AF.mil) [intermediate case] + 0 lb payload -> 7,000 nmi range (AF.mil) [ferry case] + +Flight characteristics: + Cruise at M0.77 at 33k ft + Max rate of climb: 2100 ft/min +""" diff --git a/multimission.py b/multi_aviary_submodel.py similarity index 100% rename from multimission.py rename to multi_aviary_submodel.py diff --git a/multi_cannonball_copymodel.py b/multi_cannonball_copymodel.py new file mode 100644 index 000000000..64ed68e1f --- /dev/null +++ b/multi_cannonball_copymodel.py @@ -0,0 +1,407 @@ +# Cannonball Multi Mission Example with Aviary-esque setup +# Each mission is defined as a "CannonballProblem", akin to AviaryProblem +from dymos.models.atmosphere.atmos_1976 import USatm1976Data +from scipy.interpolate import interp1d +import matplotlib.pyplot as plt +import openmdao.api as om +import dymos as dm +import numpy as np +import sys + + +class CannonballProblem(om.Problem): + def __init__(self): + super().__init__() + self.model = CannonballGroup() + self.pre_mission = PreMissionGroup() + self.post_mission = PostMissionGroup() + self.traj = None + self.model.add_subsystem('pre_mission', self.pre_mission, + promotes=['*']) + self.model.add_subsystem('post_mission', self.post_mission) + + def add_trajectory(self, ke_max=1e2): + traj = dm.Trajectory() + transcription = dm.Radau(num_segments=5, order=3, compressed=True) + ascent = dm.Phase(ode_class=CannonballODE, transcription=transcription) + traj.add_phase('ascent', ascent) + + transcription = dm.GaussLobatto(num_segments=5, order=3, compressed=True) + descent = dm.Phase(ode_class=CannonballODE, transcription=transcription) + traj.add_phase('descent', descent) + + for phase in (ascent, descent): + is_ascent = phase.name == "ascent" + phase.set_time_options(fix_initial=True if is_ascent else False, + duration_bounds=(1, 100), duration_ref=100, units='s') + phase.set_state_options('r', fix_initial=is_ascent, fix_final=False) + phase.set_state_options('h', fix_initial=is_ascent, fix_final=not is_ascent) + phase.set_state_options('gam', fix_initial=False, fix_final=is_ascent) + phase.set_state_options('v', fix_initial=False, fix_final=False) + phase.add_parameter('S', units='m**2', static_target=True, val=0.005) + phase.add_parameter('m', units='kg', static_target=True, val=1.0) + phase.add_parameter('price', units='USD', static_target=True, val=10) + phase.add_parameter('CD', units=None, static_target=True, val=0.5) + + # descent.add_objective('r', loc='final', scaler=-1.0) # negative means to maximize + for param in ('CD', 'm', 'S', 'price'): + traj.add_parameter(param, static_target=True) + + # Link Phases (link time and all state variables) + traj.link_phases(phases=['ascent', 'descent'], vars=['*']) + # have to set muzzle energy here before setup for sim to run properly + ascent.add_boundary_constraint('ke', loc='initial', + upper=ke_max, lower=0, ref=100000) + self.traj = traj + self.model.add_subsystem('traj', traj) + self.phases = [ascent, descent] + + def setDefaults(self): + self.model.set_input_defaults('density', val=7.87, units='g/cm**3') + + def addDesVar(self): + self.model.add_design_var('radius', lower=0.01, upper=0.10, + ref0=0.01, ref=0.10, units='m') + + def connectPreTraj(self): + self.model.connect('mass', 'traj.parameters:m') + self.model.connect('S', 'traj.parameters:S') + self.model.connect('price', 'traj.parameters:price') + + def setInitialVals(self, super_problem=None, prefix=""): + ref = self + if super_problem is not None and prefix != "": + ref = super_problem + + ref.set_val(prefix+'radius', 0.05, units='m') + ref.set_val(prefix+'density', 7.87, units='g/cm**3') + + ref.set_val(prefix+"traj.parameters:CD", 0.5) + ref.set_val(prefix+"traj.ascent.t_initial", 0.0) + ref.set_val(prefix+"traj.ascent.t_duration", 10.0) + + # list is initial and final, based on phase info some are fixed others are not + ascent, descent = self.phases + ref.set_val(prefix+"traj.ascent.states:r", ascent.interp('r', [0, 100])) + ref.set_val(prefix+'traj.ascent.states:h', ascent.interp('h', [0, 100])) + ref.set_val(prefix+'traj.ascent.states:v', ascent.interp('v', [200, 150])) + ref.set_val(prefix+'traj.ascent.states:gam', + ascent.interp('gam', [25, 0]), units='deg') + + ref.set_val(prefix+'traj.descent.t_initial', 10.0) + ref.set_val(prefix+'traj.descent.t_duration', 10.0) + ref.set_val(prefix+'traj.descent.states:r', descent.interp('r', [100, 200])) + ref.set_val(prefix+'traj.descent.states:h', descent.interp('h', [100, 0])) + ref.set_val(prefix+'traj.descent.states:v', descent.interp('v', [150, 200])) + ref.set_val(prefix+'traj.descent.states:gam', + descent.interp('gam', [0, -45]), units='deg') + + +class CannonballGroup(om.Group): + def __init__(self): + super().__init__() + + +class PreMissionGroup(om.Group): + def __init__(self): + super().__init__() + self.sizingcomp = CannonballSizing() + self.add_subsystem('sizing_comp', self.sizingcomp, + promotes=['*']) + + +class PostMissionGroup(om.Group): + pass + + +class CannonballODE(om.ExplicitComponent): + def initialize(self): + self.options.declare('num_nodes', types=int) + + def setup(self): + nn = self.options['num_nodes'] + # static params + self.add_input('m', units='kg') + self.add_input('S', units='m**2') + self.add_input('CD', 0.5) + + # time varying inputs + self.add_input('h', units='m', shape=nn) + self.add_input('v', units='m/s', shape=nn) + self.add_input('gam', units='rad', shape=nn) + + # state rates + self.add_output('v_dot', shape=nn, units='m/s**2', + tags=['dymos.state_rate_source:v']) + self.add_output('gam_dot', shape=nn, units='rad/s', + tags=['dymos.state_rate_source:gam']) + self.add_output('h_dot', shape=nn, units='m/s', + tags=['dymos.state_rate_source:h']) + self.add_output('r_dot', shape=nn, units='m/s', + tags=['dymos.state_rate_source:r']) + self.add_output('ke', shape=nn, units='J') + + # Ask OpenMDAO to compute the partial derivatives using complex-step + # with a partial coloring algorithm for improved performance, and use + # a graph coloring algorithm to automatically detect the sparsity pattern. + self.declare_coloring(wrt='*', method='cs') + + alt_data = USatm1976Data.alt * om.unit_conversion('ft', 'm')[0] + rho_data = USatm1976Data.rho * om.unit_conversion('slug/ft**3', 'kg/m**3')[0] + self.rho_interp = interp1d(np.array(alt_data, dtype=complex), + np.array(rho_data, dtype=complex), + kind='linear') + + def compute(self, inputs, outputs): + + gam = inputs['gam'] + v = inputs['v'] + h = inputs['h'] + m = inputs['m'] + S = inputs['S'] + CD = inputs['CD'] + + GRAVITY = 9.80665 # m/s**2 + + # handle complex-step gracefully from the interpolant + if np.iscomplexobj(h): + rho = self.rho_interp(inputs['h']) + else: + rho = self.rho_interp(inputs['h']).real + + q = 0.5*rho*inputs['v']**2 + qS = q * S + D = qS * CD + cgam = np.cos(gam) + sgam = np.sin(gam) + outputs['v_dot'] = - D/m-GRAVITY*sgam + outputs['gam_dot'] = -(GRAVITY/v)*cgam + outputs['h_dot'] = v*sgam + outputs['r_dot'] = v*cgam + outputs['ke'] = 0.5*m*v**2 + + +class CannonballSizing(om.ExplicitComponent): + def setup(self): + self.add_input(name='radius', val=1.0, units='m') + self.add_input(name='density', val=7870., units='kg/m**3') + + self.add_output(name='mass', shape=(1,), units='kg') + self.add_output(name='S', shape=(1,), units='m**2') + self.add_output(name='price', shape=(1,), units='USD') + + self.declare_partials(of='mass', wrt='density') + self.declare_partials(of='mass', wrt='radius') + self.declare_partials(of='S', wrt='radius') + self.declare_partials(of='price', wrt='radius') + self.declare_partials(of='price', wrt='density') + + def compute(self, inputs, outputs): + radius = inputs['radius'] + density = inputs['density'] + outputs['mass'] = (4/3.) * density * np.pi * radius ** 3 + outputs['S'] = np.pi * radius ** 2 + outputs['price'] = (4/3.) * density * np.pi * radius ** 3 * 10 # $10 per kg + + def compute_partials(self, inputs, partials): + radius = inputs['radius'] + density = inputs['density'] + partials['mass', 'density'] = (4/3.) * np.pi * radius ** 3 + partials['mass', 'radius'] = 4. * density * np.pi * radius ** 2 + partials['S', 'radius'] = 2 * np.pi * radius + partials['price', 'density'] = (4/3.) * np.pi * radius ** 3 * 10 + partials['price', 'radius'] = 4. * density * np.pi * radius ** 2 * 10 + + +def runAvCannonball(kes=[4e3], weights=[1], makeN2=False): + # handling of multiple KEs + # if fewer weights present than KEs, use same weight + if len(kes) > len(weights): + weights = [1]*len(kes) + elif len(kes) < len(weights): + raise Exception("Cannot have more weights than cannons!") + num_trajs = len(kes) + + probs = [] + super_prob = om.Problem() + + # create sub problems and add them to super in a group + # group prevents spillage of promoted vars into super + prefix = "group" # prefix for each om.Group + for i, ke in enumerate(kes): + prob = CannonballProblem() + prob.add_trajectory(ke_max=ke) + prob.setDefaults() + prob.addDesVar() # doesn't seem to do anything + prob.connectPreTraj() + + super_prob.model.add_subsystem(prefix+f'_{i}', prob.model, + promotes_inputs=['radius', 'density']) + probs.append(prob) + + # create an execComp with a compound range function to maximize range + # for all cannons with a weighted function + ranges = [f"r{i}" for i in range(num_trajs)] # looks like: [r0, r1, ...] + # weighted_sum_str looks like: 1*r0+1*r1+... + weighted_sum_str = "+".join([f"{weight}*{r}" for r, weight in zip(ranges, weights)]) + super_prob.model.add_subsystem('compoundComp', om.ExecComp( + "compound_range=" + weighted_sum_str), + promotes=['compound_range', *ranges]) + + # controlling radius to affect mass/ballistic coeff + super_prob.model.add_design_var('radius', lower=0.01, upper=0.10, + ref0=0.01, ref=0.10, units='m') + + for i in range(num_trajs): + # connect end of trajectory range to compound range input + super_prob.model.connect( + prefix+f'_{i}.traj.descent.states:r', ranges[i], + src_indices=-1) + + super_prob.model.add_objective('compound_range', scaler=-1) # maximize range + + super_prob.driver = om.ScipyOptimizeDriver() + super_prob.driver.options['optimizer'] = 'SLSQP' + super_prob.driver.declare_coloring() + super_prob.model.linear_solver = om.DirectSolver() + super_prob.setup() + + for i, prob in enumerate(probs): + subprefix = prefix+f"_{i}." + prob.setInitialVals(super_prob, subprefix) + + if makeN2: + om.n2(super_prob, outfile='multi_cannonball_modelcopy.html') + + dm.run_problem(super_prob) + return super_prob, prefix, num_trajs, kes, weights + + +def printOutput(super_prob, prefix, num_trajs, kes, weights): + # formatted output + print("\n\n=================================================") + print( + f"Optimized {num_trajs} trajectories with weights: {', '.join(map(str,weights))}") + rad = super_prob.get_val('radius', units='cm')[0] + + mass0 = super_prob.get_val(prefix+'_0.mass', units='kg')[0] + price0 = super_prob.get_val(prefix+'_0.price', units='USD')[0] + area0 = super_prob.get_val(prefix+'_0.S', units='cm**2')[0] + + # mass, price, S are outputs from sizing. These should be common amongst all + # trajectories, however since they're outputs they cannot be promoted upto + # super problem without unique names. This loop checks their values with + # value of the first trajectory to ensure they are the same. + if num_trajs > 1: + for i in range(num_trajs-1): + mass = super_prob.get_val(prefix+f'_{i+1}.mass', units='kg')[0] + price = super_prob.get_val(prefix+f'_{i+1}.price', units='USD')[0] + area = super_prob.get_val(prefix+f'_{i+1}.S', units='cm**2')[0] + if mass != mass0 or price != price0 or area != area0: + raise Exception( + "Masses, Prices, and/or Areas are not equivalent between trajectories.") + + print("\nOptimal Cannonball Description:") + print( + f"\tRadius: {rad:.2f} cm, Mass: {mass0:.2f} kg, Price: ${price0:.2f}, Area: {area0:.2f} sqcm") + + print("\nOptimal Trajectory Descriptions:") + ranges = 0 + for i, ke in enumerate(kes): + angle = super_prob.get_val( + prefix+f'_{i}.traj.ascent.timeseries.gam', units='deg')[0, 0] + max_range = super_prob.get_val( + prefix+f'_{i}.traj.descent.timeseries.r')[-1, 0] + + print( + f"\tKE: {ke/1e3:.2f} KJ, Launch Angle: {angle:.2f} deg, Max Range: {max_range:.2f} m") + ranges += weights[i]*max_range + print(f"System range: {ranges}") + + +def plotOutput(super_prob, prefix, num_trajs, kes, weights, show=True): + if show: + _, ax = plt.subplots() + timevals = [] + hvals = [] + rvals = [] + for i in range(num_trajs): + tv = [] + hv = [] + rv = [] + for phase in ('ascent', 'descent'): + tv.append(super_prob.get_val( + prefix+f'_{i}.traj.{phase}.timeseries.time')) + hv.append(super_prob.get_val( + prefix+f'_{i}.traj.{phase}.timeseries.h')) + rv.append(super_prob.get_val( + prefix+f'_{i}.traj.{phase}.timeseries.r')) + + timevals.append(np.vstack(tv)) + hvals.append(np.vstack(hv)) + rvals.append(np.vstack(rv)) + if show: + ax.plot(rvals[-1], hvals[-1]) + + if show: + plt.grid() + plt.legend([f"Weights = {weight}" for weight in weights]) + plt.title(f"Cannonballs With KEs: {kes} J") + plt.show() + return timevals, rvals, hvals + + +def multiTestCase(makeN2=False): + testing_weights = [[2, 1.2], [1.2, 2], [1, 1]] + kes = [1e5, 6e5] + legendlst = [] + rs, hs = [], [] + for weighting in testing_weights: + super_prob, prefix, num_trajs, kes, weights = runAvCannonball( + kes=kes, weights=weighting, makeN2=makeN2) + printOutput(super_prob, prefix, num_trajs, kes, weights) + tvals, rvals, hvals = plotOutput( + super_prob, prefix, num_trajs, kes, weights, show=False) + + for r, h, weight, ke in zip(rvals, hvals, weighting, kes): + rs.append(r) + hs.append(h) + legendlst.append(f"KE: {ke/1e3} kJ, Weight: {weight} of {weighting}") + + _, ax = plt.subplots() + colors = ['r--', 'r-', 'b--', 'b-', 'g--', 'g-'] # same color for each cannonball + for r, h, col in zip(rs, hs, colors): + ax.plot(r, h, col) + plt.grid() + plt.legend(legendlst, loc='upper left') + titlestr = ", ".join([str(ke/1e3) for ke in kes]) + plt.title(f"Cannonballs With KEs: {titlestr} kJ") + plt.show() + + +if __name__ == '__main__': + # if run as python avcannonball.py n2, it will create an N2 + makeN2 = False + singlerun = True + if len(sys.argv) > 1: + if "n2" in sys.argv: + makeN2 = True + if "multi" in sys.argv: + # runs multiple weightings to see what impact system optimization makes + multiTestCase(makeN2) + singlerun = False + + if singlerun: + # singular weighting run + super_prob, prefix, num_trajs, kes, weights = runAvCannonball( + kes=[4e5, 6e5], weights=[2, 1.5], makeN2=makeN2) + printOutput(super_prob, prefix, num_trajs, kes, weights) + plotOutput(super_prob, prefix, num_trajs, kes, weights) + + +""" +Findings: +- importing prob.model solves the issue of connecting traj to pre/post mission (at least in cannonball) +- initial values can be set with the internal function as long as set_val gets called on the super problem instance + and as such the variable name passed in contains the unique reference + """ diff --git a/multi_mission_importTraj_N2.html b/multi_mission_importTraj_N2.html deleted file mode 100644 index c1b62f22d..000000000 --- a/multi_mission_importTraj_N2.html +++ /dev/null @@ -1,14840 +0,0 @@ - - - -OpenMDAO Model Hierarchy and N2 diagram - - - - - - - - - - - - - - - - - -
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- - - - - - - diff --git a/multitraj.py b/multitraj.py deleted file mode 100644 index a143aa24d..000000000 --- a/multitraj.py +++ /dev/null @@ -1,181 +0,0 @@ -""" -Goal: use single aircraft description but optimize it for multiple missions simultaneously, -i.e. all missions are on the range-payload line instead of having excess performance -Aircraft csv: defines plane, but also defines payload (passengers, cargo) which can vary with mission - These will have to be specified in some alternate way such as a list correspond to mission # -Phase info: defines a particular mission, will have multiple phase infos -""" -import sys -import warnings -import aviary.api as av -import openmdao.api as om -import dymos as dm -from aviary.variable_info.enums import ProblemType -from c5_ferry_phase_info import phase_info as c5_ferry_phase_info -from c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info -from c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info -from aviary.variable_info.variable_meta_data import _MetaData as MetaData - -planes = ['c5_maxpayload.csv', 'c5_intermediate.csv'] -phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] -weights = [1, 1] -num_missions = len(weights) - -# "comp?.a can be used to reference multiple comp1.a comp2.a etc" - - -class MultiMissionProblem(om.Problem): - def __init__(self): - super().__init__() - self.model.add_subsystem() - - def add_design_variable(): - pass - - def link_pre_post_traj(): - pass - - def set_initial_values(): - pass - - -def add_design_var(): - pass - - -def setupprob(super_prob): - # Aviary's problem setup wrapper uses these ignored warnings to suppress - # some warnings related to variable promotion. Replicating that here with - # setup for the super problem - with warnings.catch_warnings(): - warnings.simplefilter("ignore", om.OpenMDAOWarning) - warnings.simplefilter("ignore", om.PromotionWarning) - super_prob.setup() - - -if __name__ == '__main__': - super_prob = om.Problem() - probs = [] - prefix = "problem_" - - makeN2 = False - if len(sys.argv) > 1: - if "n2" in sys.argv: - makeN2 = True - - # define individual aviary problems - for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): - prob = av.AviaryProblem() - prob.load_inputs(plane, phase_info) - prob.check_and_preprocess_inputs() - prob.add_pre_mission_systems() - traj = prob.add_phases() # save dymos traj to add to super problem as a subsystem - prob.add_post_mission_systems() - prob.link_phases() # this is half working / connect statements from outside of traj to inside are failing - prob.problem_type = ProblemType.ALTERNATE # adds summary gross mass as design var - prob.add_design_variables() - probs.append(prob) - - group = om.Group() # this group will contain all the promoted aviary vars - group.add_subsystem("pre", prob.pre_mission) - group.add_subsystem("traj", traj) - group.add_subsystem("post", prob.post_mission) - - # setting defaults for these variables to suppress errors - longlst = [ - 'mission:summary:gross_mass', 'aircraft:wing:sweep', - 'aircraft:wing:thickness_to_chord', 'aircraft:wing:area', - 'aircraft:wing:taper_ratio', 'mission:design:gross_mass'] - for var in longlst: - group.set_input_defaults( - var, val=MetaData[var]['default_value'], - units=MetaData[var]['units']) - - # add group and promote design gross mass (common input amongst multiple missions) - # in this way it represents the MTOW - super_prob.model.add_subsystem(prefix+f'{i}', group, promotes=[ - 'mission:design:gross_mass']) - - # add design gross mass as a design var - super_prob.model.add_design_var( - 'mission:design:gross_mass', lower=100e3, upper=1000e3) - - for i in range(num_missions): - # connecting each subcomponent's fuel burn to super problem's unique fuel variables - super_prob.model.connect( - prefix+f"{i}.mission:summary:fuel_burned", f"fuel_{i}") - - # create constraint to force each mission's summary gross mass to not - # exceed the common mission design gross mass (aka MTOW) - super_prob.model.add_subsystem(f'MTOW_constraint{i}', om.ExecComp( - 'mtow_resid = design_gross_mass - summary_gross_mass'), - promotes=[('summary_gross_mass', prefix+f'{i}.mission:summary:gross_mass'), - ('design_gross_mass', 'mission:design:gross_mass')]) - - super_prob.model.add_constraint(f'MTOW_constraint{i}.mtow_resid', lower=0.) - - # creating variable strings that will represent fuel burn from each mission - fuel_burned_vars = [f"fuel_{i}" for i in range(num_missions)] - weighted_str = "+".join([f"{fuel}*{weight}" - for fuel, weight in zip(fuel_burned_vars, weights)]) - # weighted_str looks like: fuel_0 * weight[0] + fuel_1 * weight[1] - - # adding compound execComp to super problem - super_prob.model.add_subsystem('compound_fuel_burn_objective', om.ExecComp( - "compound = "+weighted_str), promotes=["compound", *fuel_burned_vars]) - - super_prob.driver = om.ScipyOptimizeDriver() - super_prob.driver.options['optimizer'] = 'SLSQP' - super_prob.model.add_objective('compound') # output from execcomp goes here - - setupprob(super_prob) - if makeN2: - om.n2(super_prob, outfile="multi_mission_importTraj_N2.html") # create N2 diagram - - # cannot use this b/c initial guesses (i.e. setval func) has to be called on super prob level - # for prob in probs: - # # prob.setup() - # prob.set_initial_guesses() - - # dm.run_problem(super_prob) - - -""" -Ferry mission phase info: -Times (min): 0, 50, 812, 843 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 7001 nmi -Notes: 32k in 30 mins too fast for aviary, climb to low alt then slow rise through cruise - -Intermediate mission phase info: -Times (min): 0, 50, 560, 590 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 4839 nmi - -Max Payload mission phase info: -Times (min): 0, 50, 260, 290 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 2272 nmi - -Hard to find multiple payload/range values for FwFm (737), so use C-5 instead -Based on: - https://en.wikipedia.org/wiki/Lockheed_C-5_Galaxy#Specifications_(C-5M), - https://www.af.mil/About-Us/Fact-Sheets/Display/Article/1529718/c-5-abc-galaxy-and-c-5m-super-galaxy/ - -MTOW: 840,000 lb -Max Payload: 281,000 lb -Max Fuel: 341,446 lb -Empty Weight: 380,000 lb -> leaves 460,000 lb for fuel+payload (max fuel + max payload = 622,446 lb) - -Payload/range: - 281,000 lb payload -> 2,150 nmi range (AF.mil) [max payload case] - 120,000 lb payload -> 4,800 nmi range (AF.mil) [intermediate case] - 0 lb payload -> 7,000 nmi range (AF.mil) [ferry case] - -Flight characteristics: - Cruise at M0.77 at 33k ft - Max rate of climb: 2100 ft/min -""" From 8c11e98db712655e7b67d4f781026dd5d2fb6a14 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 31 Jul 2024 09:14:21 -0400 Subject: [PATCH 018/113] renamed single mission file --- singlemission.py => single_aviary.py | 0 1 file changed, 0 insertions(+), 0 deletions(-) rename singlemission.py => single_aviary.py (100%) diff --git a/singlemission.py b/single_aviary.py similarity index 100% rename from singlemission.py rename to single_aviary.py From c2065d5e104f1599270a679b67d65eeaa59f06b1 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 31 Jul 2024 09:22:59 -0400 Subject: [PATCH 019/113] added N2s for all examples --- multi_aviary_copymodel.html | 14840 ++++++++++++++++++++++++++++++ multi_aviary_copymodel.py | 4 +- multi_aviary_submodel.html | 14840 ++++++++++++++++++++++++++++++ multi_aviary_submodel.py | 7 +- multi_cannonball_copymodel.html | 14840 ++++++++++++++++++++++++++++++ multi_cannonball_copymodel.py | 2 +- multi_cannonball_copyparts.html | 14840 ++++++++++++++++++++++++++++++ 7 files changed, 59369 insertions(+), 4 deletions(-) create mode 100644 multi_aviary_copymodel.html create mode 100644 multi_aviary_submodel.html create mode 100644 multi_cannonball_copymodel.html create mode 100644 multi_cannonball_copyparts.html diff --git a/multi_aviary_copymodel.html b/multi_aviary_copymodel.html new file mode 100644 index 000000000..b44798028 --- /dev/null +++ b/multi_aviary_copymodel.html @@ -0,0 +1,14840 @@ + + + +OpenMDAO Model Hierarchy and N2 diagram + + + + + + + + + + + + + + + + + +
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+ + + + + + + From abcf2bfeb0add8f7cc11b2103a84afd540f2670a Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 31 Jul 2024 11:21:39 -0400 Subject: [PATCH 020/113] fixed randomness issues with min time climb, increasing num of segments --- min_time_climb.py | 20 +++++++++++--------- multi_aviary_copymodel.py | 1 + 2 files changed, 12 insertions(+), 9 deletions(-) diff --git a/min_time_climb.py b/min_time_climb.py index 8c0d42cf8..c711b4b08 100644 --- a/min_time_climb.py +++ b/min_time_climb.py @@ -7,15 +7,15 @@ def min_time_climb(height=20e3, - optimizer='SLSQP', num_seg=3, transcription='gauss-lobatto', - transcription_order=5, force_alloc_complex=False, add_rate=False, + optimizer='SLSQP', num_seg=9, transcription='gauss-lobatto', + transcription_order=3, force_alloc_complex=False, add_rate=False, time_name='time'): p = om.Problem(model=om.Group()) p.driver = om.ScipyOptimizeDriver() p.driver.options['optimizer'] = optimizer - # p.driver.declare_coloring() + p.driver.declare_coloring() if optimizer == 'SNOPT': p.driver.opt_settings['Major iterations limit'] = 1000 @@ -50,7 +50,7 @@ def min_time_climb(height=20e3, ref=1.0E3, defect_ref=1.0E3, units='m', rate_source='flight_dynamics.r_dot') - phase.add_state('h', fix_initial=True, lower=1, upper=height, + phase.add_state('h', fix_initial=True, lower=0, upper=height, ref=height, defect_ref=height, units='m', rate_source='flight_dynamics.h_dot', targets=['h']) @@ -74,7 +74,7 @@ def min_time_climb(height=20e3, phase.add_parameter('Isp', val=1600.0, units='s', opt=False, targets=['Isp']) phase.add_parameter('throttle', val=1.0, opt=False, targets=['throttle']) - phase.add_boundary_constraint('h', loc='final', equals=height, scaler=1.0E-3) + phase.add_boundary_constraint('h', loc='final', equals=height) # , scaler=1.0E-3) phase.add_boundary_constraint('aero.mach', loc='final', equals=1.0) phase.add_boundary_constraint('gam', loc='final', equals=0.0) @@ -105,7 +105,7 @@ def min_time_climb(height=20e3, p['traj.phase0.t_duration'] = 350.0 p['traj.phase0.states:r'] = phase.interp('r', [0.0, 111319.54]) - p['traj.phase0.states:h'] = phase.interp('h', [100.0, 20000.0]) + p['traj.phase0.states:h'] = phase.interp('h', [100.0, height]) p['traj.phase0.states:v'] = phase.interp('v', [135.964, 283.159]) p['traj.phase0.states:gam'] = phase.interp('gam', [0.0, 0.0]) p['traj.phase0.states:m'] = phase.interp('m', [19030.468, 16841.431]) @@ -117,6 +117,8 @@ def min_time_climb(height=20e3, def checkDeviation(filenum=0): + """Function to run min time climb problem multiple times for the same height and report any deviation in results. + Made to check for random results in outputs, fixed 7/31, seems to be caused by transcription order being 5 not 3""" heights = [10e3]*2 times_to_climb = [] timeseries_pts = {'h': [], 'r': [], 'thrust': [], 'v': []} @@ -150,7 +152,7 @@ def checkDeviation(filenum=0): def multiHeightTest(): - heights = [8e3, 10e3] + heights = [6e3, 10e3] prefix = 'traj.phase0.timeseries.' plotvars = {'r': ['h'], 'time': ['v', 'thrust', 'm_dot', 'alpha']} varnames = {prefix+x: [prefix+y for y in ylst] for x, ylst in plotvars.items()} @@ -209,10 +211,10 @@ def multiHeightTest(): optimization takes a very different number of iterations, and the profile looks very different. Time to climb is also different.""" if __name__ == '__main__': - np.random.seed(0) if len(sys.argv) > 1 and 'filenum' in sys.argv[1]: checkDeviation(filenum=sys.argv[1].split('filenum=')[1]) - # multiHeightTest() + else: + multiHeightTest() """ diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index 469b876bb..9d410e245 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -108,6 +108,7 @@ def create_N2(self, outfile='multi_aviary_copymodel.html'): om.n2(self, outfile=outfile) def initvals(self): + """attempting to copy over aviary code for setting initial values and changing references""" for i, prob in enumerate(self.probs): self.set_val(self.group_prefix + f'_{i}.aircraft:design:landing_to_takeoff_mass_ratio', 0.5) From 23221845bc1ecf103925c289e1bbcb86f35e770e Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 31 Jul 2024 13:46:11 -0400 Subject: [PATCH 021/113] updated methods for level 2 with initial vals able to use set val on passed in problem --- aviary/interface/methods_for_level2.py | 180 +- multi_aviary_copymodel.html | 2 +- multi_aviary_copymodel.py | 389 +- single_aviary.html | 14840 +++++++++++++++++++++++ single_aviary.py | 5 + 5 files changed, 15097 insertions(+), 319 deletions(-) create mode 100644 single_aviary.html diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index 66d59a9df..9c72f4f3f 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -1970,29 +1970,18 @@ def setup(self, **kwargs): warnings.simplefilter("ignore", om.PromotionWarning) super().setup(**kwargs) - def set_initial_guesses(self): - """ - Call `set_val` on the trajectory for states and controls to seed - the problem with reasonable initial guesses. This is especially - important for collocation methods. - - This method first identifies all phases in the trajectory then - loops over each phase. Specific initial guesses - are added depending on the phase and mission method. Cruise is treated - as a special phase for GASP-based missions because it is an AnalyticPhase - in Dymos. For this phase, we handle the initial guesses first separately - and continue to the next phase after that. For other phases, we set the initial - guesses for states and controls according to the information available - in the 'initial_guesses' attribute of the phase. - """ + def set_initial_guesses(self, parent_prob=None, parent_prefix=""): + setvalprob = self + if parent_prob is not None and parent_prefix != "": + setvalprob = parent_prob # Grab the trajectory object from the model if self.analysis_scheme is AnalysisScheme.SHOOTING: if self.problem_type is ProblemType.SIZING: - self.set_val(Mission.Summary.GROSS_MASS, - self.get_val(Mission.Design.GROSS_MASS)) + setvalprob.set_val(parent_prefix+Mission.Summary.GROSS_MASS, + self.get_val(Mission.Design.GROSS_MASS)) - self.set_val("traj.SGMClimb_"+Dynamic.Mission.ALTITUDE + - "_trigger", val=self.cruise_alt, units="ft") + setvalprob.set_val(parent_prefix+"traj.SGMClimb_"+Dynamic.Mission.ALTITUDE + + "_trigger", val=self.cruise_alt, units="ft") return @@ -2023,52 +2012,26 @@ def set_initial_guesses(self): if 'mass' == guess_key: # Set initial and duration mass for the analytic cruise phase. # Note we are integrating over mass, not time for this phase. - self.set_val(f'traj.{phase_name}.t_initial', - val[0], units=units) - self.set_val(f'traj.{phase_name}.t_duration', - val[1], units=units) + setvalprob.set_val(parent_prefix+f'traj.{phase_name}.t_initial', + val[0], units=units) + setvalprob.set_val(parent_prefix+f'traj.{phase_name}.t_duration', + val[1], units=units) else: # Otherwise, set the value of the parameter in the trajectory phase - self.set_val(f'traj.{phase_name}.parameters:{guess_key}', - val, units=units) + setvalprob.set_val( + parent_prefix + f'traj.{phase_name}.parameters:{guess_key}', + val, units=units) continue # If not cruise and GASP, add subsystem guesses - self._add_subsystem_guesses(phase_name, phase) + self._add_subsystem_guesses(phase_name, phase, setvalprob, parent_prefix) # Set initial guesses for states and controls for each phase - self._add_guesses(phase_name, phase, guesses) + self._add_guesses(phase_name, phase, guesses, setvalprob, parent_prefix) def _process_guess_var(self, val, key, phase): - """ - Process the guess variable, which can either be a float or an array of floats. - - This method is responsible for interpolating initial guesses when the user - provides a list or array of values rather than a single float. It interpolates - the guess values across the phase's domain for a given variable, be it a control - or a state variable. The interpolation is performed between -1 and 1 (representing - the normalized phase time domain), using the numpy linspace function. - - The result of this method is a single value or an array of interpolated values - that can be used to seed the optimization problem with initial guesses. - - Parameters - ---------- - val : float or list/array of floats - The initial guess value(s) for a particular variable. - key : str - The key identifying the variable for which the initial guess is provided. - phase : Phase - The phase for which the variable is being set. - - Returns - ------- - val : float or array of floats - The processed guess value(s) to be used in the optimization problem. - """ - # Check if val is not a single float if not isinstance(val, float): # If val is an array of values @@ -2094,24 +2057,7 @@ def _process_guess_var(self, val, key, phase): # Return the processed guess value(s) return val - def _add_subsystem_guesses(self, phase_name, phase): - """ - Adds the initial guesses for each subsystem of a given phase to the problem. - - This method first fetches all subsystems associated with the given phase. - It then loops over each subsystem and fetches its initial guesses. For each - guess, it identifies whether the guess corresponds to a state or a control - variable and then processes the guess variable. After this, the initial - guess is set in the problem using the `set_val` method. - - Parameters - ---------- - phase_name : str - The name of the phase for which the subsystem guesses are being added. - phase : Phase - The phase object for which the subsystem guesses are being added. - """ - + def _add_subsystem_guesses(self, phase_name, phase, setvalprob, parent_prefix): # Get all subsystems associated with the phase all_subsystems = self._get_all_subsystems( self.phase_info[phase_name]['external_subsystems']) @@ -2134,28 +2080,10 @@ def _add_subsystem_guesses(self, phase_name, phase): val['val'] = self._process_guess_var(val['val'], key, phase) # Set the initial guess in the problem - self.set_val(f'traj.{phase_name}.{path_string}:{key}', **val) - - def _add_guesses(self, phase_name, phase, guesses): - """ - Adds the initial guesses for each variable of a given phase to the problem. - - This method sets the initial guesses for time, control, state, and problem-specific - variables for a given phase. If using the GASP model, it also handles some special - cases that are not covered in the `phase_info` object. These include initial guesses - for mass, time, and distance, which are determined based on the phase name and other - mission-related variables. - - Parameters - ---------- - phase_name : str - The name of the phase for which the guesses are being added. - phase : Phase - The phase object for which the guesses are being added. - guesses : dict - A dictionary containing the initial guesses for the phase. - """ + setvalprob.set_val( + parent_prefix+f'traj.{phase_name}.{path_string}:{key}', **val) + def _add_guesses(self, phase_name, phase, guesses, setvalprob, parent_prefix): # If using the GASP model, set initial guesses for the rotation mass and flight duration if self.mission_method is TWO_DEGREES_OF_FREEDOM: rotation_mass = self.initial_guesses['rotation_mass'] @@ -2214,30 +2142,32 @@ def _add_guesses(self, phase_name, phase, guesses): # Set initial guess for time variables if 'time' == guess_key and self.mission_method is not SOLVED_2DOF: - self.set_val(f'traj.{phase_name}.t_initial', - val[0], units=units) - self.set_val(f'traj.{phase_name}.t_duration', - val[1], units=units) + setvalprob.set_val(parent_prefix+f'traj.{phase_name}.t_initial', + val[0], units=units) + setvalprob.set_val(parent_prefix+f'traj.{phase_name}.t_duration', + val[1], units=units) else: # Set initial guess for control variables if guess_key in control_keys: try: - self.set_val(f'traj.{phase_name}.controls:{guess_key}', self._process_guess_var( - val, guess_key, phase), units=units) + setvalprob.set_val( + parent_prefix + f'traj.{phase_name}.controls:{guess_key}', + self._process_guess_var(val, guess_key, phase), + units=units) except KeyError: try: - self.set_val( + setvalprob.set_val( + parent_prefix + f'traj.{phase_name}.polynomial_controls:{guess_key}', - self._process_guess_var( - val, guess_key, phase), + self._process_guess_var(val, guess_key, phase), units=units) except KeyError: - self.set_val( - f'traj.{phase_name}.bspline_controls:{guess_key}', - self._process_guess_var( - val, guess_key, phase), - units=units) + setvalprob.set_val(parent_prefix + + f'traj.{phase_name}.bspline_controls:{guess_key}', + self._process_guess_var( + val, guess_key, phase), + units=units) if self.mission_method is SOLVED_2DOF: continue @@ -2246,15 +2176,17 @@ def _add_guesses(self, phase_name, phase, guesses): pass # Set initial guess for state variables elif guess_key in state_keys: - self.set_val(f'traj.{phase_name}.states:{guess_key}', self._process_guess_var( - val, guess_key, phase), units=units) + setvalprob.set_val(parent_prefix + + f'traj.{phase_name}.states:{guess_key}', self. + _process_guess_var(val, guess_key, phase), + units=units) elif guess_key in prob_keys: - self.set_val(guess_key, val, units=units) + setvalprob.set_val(parent_prefix+guess_key, val, units=units) elif ":" in guess_key: - self.set_val( - f'traj.{phase_name}.{guess_key}', self._process_guess_var( - val, guess_key, phase), - units=units) + setvalprob.set_val(parent_prefix + + f'traj.{phase_name}.{guess_key}', self._process_guess_var( + val, guess_key, phase), + units=units) else: # raise error if the guess key is not recognized raise ValueError( @@ -2284,8 +2216,8 @@ def _add_guesses(self, phase_name, phase, guesses): mass_guess = self.aviary_inputs.get_val( Mission.Design.GROSS_MASS, units='lbm') # Set the mass guess as the initial value for the mass state variable - self.set_val(f'traj.{phase_name}.states:mass', - mass_guess, units='lbm') + setvalprob.set_val(parent_prefix+f'traj.{phase_name}.states:mass', + mass_guess, units='lbm') if 'time' not in guesses: # Determine initial time and duration guesses depending on the phase name @@ -2296,10 +2228,10 @@ def _add_guesses(self, phase_name, phase, guesses): t_initial = flight_duration*.94 t_duration = 5000 # Set the time guesses as the initial values for the time-related trajectory variables - self.set_val(f"traj.{phase_name}.t_initial", - t_initial, units='s') - self.set_val(f"traj.{phase_name}.t_duration", - t_duration, units='s') + setvalprob.set_val(parent_prefix+f"traj.{phase_name}.t_initial", + t_initial, units='s') + setvalprob.set_val(parent_prefix+f"traj.{phase_name}.t_duration", + t_duration, units='s') if self.mission_method is TWO_DEGREES_OF_FREEDOM: if 'distance' not in guesses: @@ -2309,10 +2241,10 @@ def _add_guesses(self, phase_name, phase, guesses): elif 'desc2' in base_phase: ys = [self.target_range*.99, self.target_range] # Set the distance guesses as the initial values for the distance state variable - self.set_val( - f"traj.{phase_name}.states:distance", phase.interp( - Dynamic.Mission.DISTANCE, ys=ys) - ) + setvalprob.set_val(parent_prefix + + f"traj.{phase_name}.states:distance", phase.interp( + Dynamic.Mission.DISTANCE, ys=ys) + ) def run_aviary_problem(self, record_filename="problem_history.db", optimization_history_filename=None, restart_filename=None, diff --git a/multi_aviary_copymodel.html b/multi_aviary_copymodel.html index b44798028..5e3f7127c 100644 --- a/multi_aviary_copymodel.html +++ b/multi_aviary_copymodel.html @@ -3255,7 +3255,7 @@

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diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index 9d410e245..11e61451b 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -11,7 +11,7 @@ import openmdao.api as om import dymos as dm import numpy as np -from aviary.variable_info.enums import ProblemType +from aviary.variable_info.enums import ProblemType, AnalysisScheme from c5_ferry_phase_info import phase_info as c5_ferry_phase_info from c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info from c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info @@ -69,7 +69,7 @@ def add_design_variables(self): def add_driver(self): self.driver = om.ScipyOptimizeDriver() self.driver.options['optimizer'] = 'SLSQP' - self.driver.declare_coloring() + # self.driver.declare_coloring() self.model.linear_solver = om.DirectSolver() def add_objective(self): @@ -107,198 +107,10 @@ def setup_wrapper(self): def create_N2(self, outfile='multi_aviary_copymodel.html'): om.n2(self, outfile=outfile) - def initvals(self): - """attempting to copy over aviary code for setting initial values and changing references""" - for i, prob in enumerate(self.probs): - self.set_val(self.group_prefix + - f'_{i}.aircraft:design:landing_to_takeoff_mass_ratio', 0.5) - # Grab the trajectory object from the model - traj = prob.model.traj - - # Determine which phases to loop over, fetching them from the trajectory - phase_items = traj._phases.items() - - # Loop over each phase and set initial guesses for the state and control variables - for idx, (phase_name, phase) in enumerate(phase_items): - # If not, fetch the initial guesses specific to the phase - # check if guesses exist for this phase - if "initial_guesses" in prob.phase_info[phase_name]: - guesses = prob.phase_info[phase_name]['initial_guesses'] - else: - guesses = {} - - # ||||||||||||| _add_subsystem_guesses - # Get all subsystems associated with the phase - all_subsystems = prob._get_all_subsystems( - prob.phase_info[phase_name]['external_subsystems']) - - # Loop over each subsystem - for subsystem in all_subsystems: - # Fetch the initial guesses for the subsystem - initial_guesses = subsystem.get_initial_guesses() - - # Loop over each guess - for key, val in initial_guesses.items(): - # Identify the type of the guess (state or control) - type = val.pop('type') - if 'state' in type: - path_string = 'states' - elif 'control' in type: - path_string = 'controls' - - # Process the guess variable (handles array interpolation) - val['val'] = prob._process_guess_var(val['val'], key, phase) - - # Set the initial guess in the problem - self.set_val( - self.group_prefix + - f'_{i}.traj.{phase_name}.{path_string}:{key}', **val) - - # Set initial guesses for states and controls for each phase - - # |||||||||||||||||||||| _add_guesses - # If using the GASP model, set initial guesses for the rotation mass and flight duration - if prob.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): - control_keys = ["mach", "altitude"] - state_keys = ["mass", Dynamic.Mission.DISTANCE] - prob_keys = ["tau_gear", "tau_flaps"] - - # for the simple mission method, use the provided initial and final mach and altitude values from phase_info - if prob.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): - initial_altitude = wrapped_convert_units( - prob.phase_info[phase_name]['user_options'] - ['initial_altitude'], - 'ft') - final_altitude = wrapped_convert_units( - prob.phase_info[phase_name]['user_options']['final_altitude'], 'ft') - initial_mach = prob.phase_info[phase_name]['user_options'][ - 'initial_mach'] - final_mach = prob.phase_info[phase_name]['user_options'][ - 'final_mach'] - - guesses["mach"] = ([initial_mach[0], final_mach[0]], "unitless") - guesses["altitude"] = ([initial_altitude, final_altitude], 'ft') - - if prob.mission_method is HEIGHT_ENERGY: - # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds - if 'time' not in guesses: - initial_bounds = wrapped_convert_units( - prob.phase_info[phase_name]['user_options']['initial_bounds'], 's') - duration_bounds = wrapped_convert_units( - prob.phase_info[phase_name]['user_options']['duration_bounds'], 's') - guesses["time"] = ([np.mean(initial_bounds[0]), np.mean( - duration_bounds[0])], 's') - - # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds - if 'time' not in guesses: - initial_bounds = prob.phase_info[phase_name]['user_options'][ - 'initial_bounds'] - duration_bounds = prob.phase_info[phase_name]['user_options'][ - 'duration_bounds'] - # Add a check for the initial and duration bounds, raise an error if they are not consistent - if initial_bounds[1] != duration_bounds[1]: - raise ValueError( - f"Initial and duration bounds for {phase_name} are not consistent.") - guesses["time"] = ([np.mean(initial_bounds[0]), np.mean( - duration_bounds[0])], initial_bounds[1]) - - for guess_key, guess_data in guesses.items(): - val, units = guess_data - - # Set initial guess for time variables - if 'time' == guess_key and prob.mission_method is not SOLVED_2DOF: - self.set_val( - self.group_prefix + f'_{i}.traj.{phase_name}.t_initial', - val[0], - units=units) - self.set_val( - self.group_prefix + f'_{i}.traj.{phase_name}.t_duration', - val[1], - units=units) - - else: - # Set initial guess for control variables - if guess_key in control_keys: - try: - self.set_val(self.group_prefix + - f'_{i}.traj.{phase_name}.controls:{guess_key}', - prob._process_guess_var( - val, guess_key, phase), - units=units) - except KeyError: - try: - self.set_val( - self.group_prefix + - f'_{i}.traj.{phase_name}.polynomial_controls:{guess_key}', - prob._process_guess_var(val, guess_key, phase), - units=units) - except KeyError: - self.set_val( - self.group_prefix + - f'_{i}.traj.{phase_name}.bspline_controls:{guess_key}', - prob._process_guess_var(val, guess_key, phase), - units=units) - - if guess_key in control_keys: - pass - # Set initial guess for state variables - elif guess_key in state_keys: - self.set_val(self.group_prefix + - f'_{i}.traj.{phase_name}.states:{guess_key}', - prob._process_guess_var( - val, guess_key, phase), - units=units) - elif guess_key in prob_keys: - self.set_val( - self.group_prefix+f'_{i}.'+guess_key, val, units=units) - elif ":" in guess_key: - self.set_val( - self.group_prefix + f'_{i}.traj.{phase_name}.{guess_key}', - prob._process_guess_var(val, guess_key, phase), - units=units) - else: - # raise error if the guess key is not recognized - raise ValueError( - f"Initial guess key {guess_key} in {phase_name} is not recognized.") - - # We need some special logic for these following variables because GASP computes - # initial guesses using some knowledge of the mission duration and other variables - # that are only available after calling `create_vehicle`. Thus these initial guess - # values are not included in the `phase_info` object. - - base_phase = phase_name - if 'mass' not in guesses: - mass_guess = prob.aviary_inputs.get_val( - Mission.Design.GROSS_MASS, units='lbm') - # Set the mass guess as the initial value for the mass state variable - self.set_val(self.group_prefix+f'_{i}.traj.{phase_name}.states:mass', - mass_guess, units='lbm') - - # if 'time' not in guesses: - # # Determine initial time and duration guesses depending on the phase name - # if 'desc1' == base_phase: - # t_initial = flight_duration*.9 - # t_duration = flight_duration*.04 - # elif 'desc2' in base_phase: - # t_initial = flight_duration*.94 - # t_duration = 5000 - # # Set the time guesses as the initial values for the time-related trajectory variables - # self.set_val(f"traj.{phase_name}.t_initial", - # t_initial, units='s') - # self.set_val(f"traj.{phase_name}.t_duration", - # t_duration, units='s') - def run(self): - dm.run_problem(self) - - # def link_pre_post_traj(self): - # for i, prob in enumerate(self.probs): - # prefix = self.group_prefix+f'_{i}.' - - # self.model.connect(prefix + - # f'traj.{prob.regular_phases[-1]}.timeseries.distance', - # Mission.Summary.RANGE, src_indices=[-1], - # flat_src_indices=True) + self.run_model() + self.check_totals(method='fd') + # dm.run_problem(self) if __name__ == '__main__': @@ -311,11 +123,200 @@ def run(self): super_prob.add_design_variables() super_prob.add_objective() super_prob.setup_wrapper() - # super_prob.initvals() + for i, prob in enumerate(super_prob.probs): + super_prob.set_val( + super_prob.group_prefix + + f"_{i}.aircraft:design:landing_to_takeoff_mass_ratio", 0.5) + prob.set_initial_guesses(super_prob, super_prob.group_prefix+f"_{i}.") + print(super_prob.get_val(super_prob.group_prefix + + f"_{i}.aircraft:design:landing_to_takeoff_mass_ratio")) + print(super_prob.get_val(super_prob.group_prefix + + f"_{i}.mission:summary:range")) if makeN2: super_prob.create_N2() super_prob.run() + # def initvals(self): + # """attempting to copy over aviary code for setting initial values and changing references""" + # for i, prob in enumerate(self.probs): + # setvalprob.set_val(parent_prefix+self.group_prefix + + # f'_{i}.aircraft:design:landing_to_takeoff_mass_ratio', 0.5) + # # Grab the trajectory object from the model + # traj = prob.model.traj + + # # Determine which phases to loop over, fetching them from the trajectory + # phase_items = traj._phases.items() + + # # Loop over each phase and set initial guesses for the state and control variables + # for idx, (phase_name, phase) in enumerate(phase_items): + # # If not, fetch the initial guesses specific to the phase + # # check if guesses exist for this phase + # if "initial_guesses" in prob.phase_info[phase_name]: + # guesses = prob.phase_info[phase_name]['initial_guesses'] + # else: + # guesses = {} + + # # ||||||||||||| _add_subsystem_guesses + # # Get all subsystems associated with the phase + # all_subsystems = prob._get_all_subsystems( + # prob.phase_info[phase_name]['external_subsystems']) + + # # Loop over each subsystem + # for subsystem in all_subsystems: + # # Fetch the initial guesses for the subsystem + # initial_guesses = subsystem.get_initial_guesses() + + # # Loop over each guess + # for key, val in initial_guesses.items(): + # # Identify the type of the guess (state or control) + # type = val.pop('type') + # if 'state' in type: + # path_string = 'states' + # elif 'control' in type: + # path_string = 'controls' + + # # Process the guess variable (handles array interpolation) + # val['val'] = prob._process_guess_var(val['val'], key, phase) + + # # Set the initial guess in the problem + # setvalprob.set_val(parent_prefix+ + # self.group_prefix + + # f'_{i}.traj.{phase_name}.{path_string}:{key}', **val) + + # # Set initial guesses for states and controls for each phase + + # # |||||||||||||||||||||| _add_guesses + # # If using the GASP model, set initial guesses for the rotation mass and flight duration + # if prob.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): + # control_keys = ["mach", "altitude"] + # state_keys = ["mass", Dynamic.Mission.DISTANCE] + # prob_keys = ["tau_gear", "tau_flaps"] + + # # for the simple mission method, use the provided initial and final mach and altitude values from phase_info + # if prob.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): + # initial_altitude = wrapped_convert_units( + # prob.phase_info[phase_name]['user_options'] + # ['initial_altitude'], + # 'ft') + # final_altitude = wrapped_convert_units( + # prob.phase_info[phase_name]['user_options']['final_altitude'], 'ft') + # initial_mach = prob.phase_info[phase_name]['user_options'][ + # 'initial_mach'] + # final_mach = prob.phase_info[phase_name]['user_options'][ + # 'final_mach'] + + # guesses["mach"] = ([initial_mach[0], final_mach[0]], "unitless") + # guesses["altitude"] = ([initial_altitude, final_altitude], 'ft') + + # if prob.mission_method is HEIGHT_ENERGY: + # # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds + # if 'time' not in guesses: + # initial_bounds = wrapped_convert_units( + # prob.phase_info[phase_name]['user_options']['initial_bounds'], 's') + # duration_bounds = wrapped_convert_units( + # prob.phase_info[phase_name]['user_options']['duration_bounds'], 's') + # guesses["time"] = ([np.mean(initial_bounds[0]), np.mean( + # duration_bounds[0])], 's') + + # # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds + # if 'time' not in guesses: + # initial_bounds = prob.phase_info[phase_name]['user_options'][ + # 'initial_bounds'] + # duration_bounds = prob.phase_info[phase_name]['user_options'][ + # 'duration_bounds'] + # # Add a check for the initial and duration bounds, raise an error if they are not consistent + # if initial_bounds[1] != duration_bounds[1]: + # raise ValueError( + # f"Initial and duration bounds for {phase_name} are not consistent.") + # guesses["time"] = ([np.mean(initial_bounds[0]), np.mean( + # duration_bounds[0])], initial_bounds[1]) + + # for guess_key, guess_data in guesses.items(): + # val, units = guess_data + + # # Set initial guess for time variables + # if 'time' == guess_key and prob.mission_method is not SOLVED_2DOF: + # setvalprob.set_val(parent_prefix+ + # self.group_prefix + f'_{i}.traj.{phase_name}.t_initial', + # val[0], + # units=units) + # setvalprob.set_val(parent_prefix+ + # self.group_prefix + f'_{i}.traj.{phase_name}.t_duration', + # val[1], + # units=units) + + # else: + # # Set initial guess for control variables + # if guess_key in control_keys: + # try: + # setvalprob.set_val(parent_prefix+self.group_prefix + + # f'_{i}.traj.{phase_name}.controls:{guess_key}', + # prob._process_guess_var( + # val, guess_key, phase), + # units=units) + # except KeyError: + # try: + # setvalprob.set_val(parent_prefix+ + # self.group_prefix + + # f'_{i}.traj.{phase_name}.polynomial_controls:{guess_key}', + # prob._process_guess_var(val, guess_key, phase), + # units=units) + # except KeyError: + # setvalprob.set_val(parent_prefix+ + # self.group_prefix + + # f'_{i}.traj.{phase_name}.bspline_controls:{guess_key}', + # prob._process_guess_var(val, guess_key, phase), + # units=units) + + # if guess_key in control_keys: + # pass + # # Set initial guess for state variables + # elif guess_key in state_keys: + # setvalprob.set_val(parent_prefix+self.group_prefix + + # f'_{i}.traj.{phase_name}.states:{guess_key}', + # prob._process_guess_var( + # val, guess_key, phase), + # units=units) + # elif guess_key in prob_keys: + # setvalprob.set_val(parent_prefix+ + # self.group_prefix+f'_{i}.'+guess_key, val, units=units) + # elif ":" in guess_key: + # setvalprob.set_val(parent_prefix+ + # self.group_prefix + f'_{i}.traj.{phase_name}.{guess_key}', + # prob._process_guess_var(val, guess_key, phase), + # units=units) + # else: + # # raise error if the guess key is not recognized + # raise ValueError( + # f"Initial guess key {guess_key} in {phase_name} is not recognized.") + + # # We need some special logic for these following variables because GASP computes + # # initial guesses using some knowledge of the mission duration and other variables + # # that are only available after calling `create_vehicle`. Thus these initial guess + # # values are not included in the `phase_info` object. + + # base_phase = phase_name + # if 'mass' not in guesses: + # mass_guess = prob.aviary_inputs.get_val( + # Mission.Design.GROSS_MASS, units='lbm') + # # Set the mass guess as the initial value for the mass state variable + # setvalprob.set_val(parent_prefix+self.group_prefix+f'_{i}.traj.{phase_name}.states:mass', + # mass_guess, units='lbm') + + # # if 'time' not in guesses: + # # # Determine initial time and duration guesses depending on the phase name + # # if 'desc1' == base_phase: + # # t_initial = flight_duration*.9 + # # t_duration = flight_duration*.04 + # # elif 'desc2' in base_phase: + # # t_initial = flight_duration*.94 + # # t_duration = 5000 + # # # Set the time guesses as the initial values for the time-related trajectory variables + # # setvalprob.set_val(parent_prefix+f"traj.{phase_name}.t_initial", + # # t_initial, units='s') + # # setvalprob.set_val(parent_prefix+f"traj.{phase_name}.t_duration", + # # t_duration, units='s') + # ========================================================================= old code # super_prob = om.Problem() diff --git a/single_aviary.html b/single_aviary.html new file mode 100644 index 000000000..5cb7b0313 --- /dev/null +++ b/single_aviary.html @@ -0,0 +1,14840 @@ + + + +OpenMDAO Model Hierarchy and N2 diagram + + + + + + + + + + + + + + + + + +
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+ + + + + + + diff --git a/single_aviary.py b/single_aviary.py index bf5cd91b6..35acbcb4f 100644 --- a/single_aviary.py +++ b/single_aviary.py @@ -1,4 +1,5 @@ import aviary.api as av +import openmdao.api as om import sys from c5_ferry_phase_info import phase_info as c5_ferry_phase_info from c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info @@ -37,6 +38,7 @@ def modify_plane(orig_filename, payloads, ranges): if __name__ == '__main__': + makeN2 = True if len(sys.argv) > 2 and "n2" in sys.argv else False prob = av.AviaryProblem() plane_file = 'c5.csv' payloads = {"ferry": 0, "intermediate": 120e3, "maxpayload": 281e3} @@ -74,6 +76,9 @@ def modify_plane(orig_filename, payloads, ranges): prob.setup() + if makeN2: + om.n2(prob, outfile='single_aviary.html') + prob.set_initial_guesses() # remove all plots and extras From d3588434f26561c1f2dc9a7aeb6329cd1a21a575 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 31 Jul 2024 14:14:32 -0400 Subject: [PATCH 022/113] cehckpt --- min_time_climb.py | 35 ++++++++++++++++++++--------------- 1 file changed, 20 insertions(+), 15 deletions(-) diff --git a/min_time_climb.py b/min_time_climb.py index c711b4b08..c51ea006f 100644 --- a/min_time_climb.py +++ b/min_time_climb.py @@ -70,7 +70,7 @@ def min_time_climb(height=20e3, rate_continuity=True, rate_continuity_scaler=100.0, rate2_continuity=False, targets=['alpha']) - phase.add_parameter('S', val=49.2386, units='m**2', opt=False, targets=['S']) + phase.add_parameter('S', val=49.2386, units='m**2', opt=True, targets=['S']) phase.add_parameter('Isp', val=1600.0, units='s', opt=False, targets=['Isp']) phase.add_parameter('throttle', val=1.0, opt=False, targets=['throttle']) @@ -152,9 +152,10 @@ def checkDeviation(filenum=0): def multiHeightTest(): - heights = [6e3, 10e3] + heights = [12e3, 20e3] prefix = 'traj.phase0.timeseries.' plotvars = {'r': ['h'], 'time': ['v', 'thrust', 'm_dot', 'alpha']} + plotunits = {'r': ['km', 'km'], 'time': ['s', 'm/s', 'kN', 'kg/s', 'deg']} varnames = {prefix+x: [prefix+y for y in ylst] for x, ylst in plotvars.items()} numplots = sum([len(item) for item in plotvars.values()]) data = {f'h{i}': {} for i in range(len(heights))} @@ -170,37 +171,41 @@ def multiHeightTest(): f"{p.get_val('traj.phase0.timeseries.time',units='s')[-1][0]:.2f}" + f" s with wing area: {wing_area} sqm") - for xname in varnames.keys(): - xsol = sol.get_val(xname) - xsim = sim.get_val(xname) + for xname, unitkey in zip(varnames.keys(), plotunits.keys()): + xsol = sol.get_val(xname, units=plotunits[unitkey][0]) + xsim = sim.get_val(xname, units=plotunits[unitkey][0]) if not xname in data.keys(): data[f'h{j}'][xname] = {'x': (xsol, xsim), 'y': []} - for yname in varnames[xname]: + for i, yname in enumerate(varnames[xname]): if not 'yname' in data[f'h{j}'][xname].keys(): data[f'h{j}'][xname]['yname'] = [yname] else: data[f'h{j}'][xname]['yname'].append(yname) - ysol = sol.get_val(yname) - ysim = sim.get_val(yname) + ysol = sol.get_val(yname, units=plotunits[unitkey][i+1]) + ysim = sim.get_val(yname, units=plotunits[unitkey][i+1]) data[f'h{j}'][xname]['y'].append((ysol, ysim)) colors = ['r', 'b'] + legendlst = [] for j in range(len(heights)): datadict = data[f'h{j}'] i = 1 - for xname in datadict.keys(): + for xname, unitkey in zip(datadict.keys(), plotunits.keys()): xsol, xsim = datadict[xname]['x'] - for (ysol, ysim), yname in zip(datadict[xname]['y'], datadict[xname]['yname']): - ax = plt.subplot(int(numplots/2), numplots-int(numplots/2), i) - if max(ysim) > 1e3: - ysol, ysim = ysol/1e3, ysim/1e3 + for (ysol, ysim), yname, yunit in zip(datadict[xname]['y'], datadict[xname]['yname'], plotunits[unitkey][1:]): + plt.subplot(int(numplots/2), numplots-int(numplots/2), i) + # if max(ysim) > 1e3: + # ysol, ysim = ysol/1e3, ysim/1e3 plt.plot(xsol, ysol, f'{colors[j]}o', fillstyle='none') plt.plot(xsim, ysim, colors[j]) - plt.xlabel(xname.split(prefix)[1]) - plt.ylabel(yname.split(prefix)[1]) + plt.xlabel(f"{xname.split(prefix)[1]} ({plotunits[unitkey][0]})") + plt.ylabel(f"{yname.split(prefix)[1]} ({yunit})") if j == 0: plt.grid(visible=True) i += 1 + for datatype in ('Solution', 'Simulation'): + legendlst.append(f"{datatype} @ h = {heights[j]/1e3} km") + plt.figlegend(legendlst) plt.show() From c3c3004d3c7f85c0026072ed37714b956bc33474 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Thu, 1 Aug 2024 09:46:24 -0400 Subject: [PATCH 023/113] restructured files --- .../n2_multi_aviary_copymodel.html | 2 +- .../n2_multi_aviary_submodel.html | 0 .../n2_multi_cannonball_copymodel.html | 0 .../n2_multi_cannonball_copyparts.html | 0 .../n2_multi_min_time_to_climb.html | 2 +- c5.csv => c5_models/c5.csv | 0 c5_ferry.csv => c5_models/c5_ferry.csv | 0 .../c5_ferry_phase_info.py | 0 .../c5_intermediate.csv | 0 .../c5_intermediate_phase_info.py | 0 .../c5_maxpayload.csv | 0 .../c5_maxpayload_phase_info.py | 0 .../cannonball.py | 0 .../multi_cannonball_copymodel.py | 4 +- .../multi_cannonball_copyparts.py | 4 +- checkdiff_0.txt | 115 ----------- checkdiff_1.txt | 115 ----------- createN2.py | 8 + .../min_time_climb.py | 62 +++--- .../multi_min_time_to_climb.py | 178 ++++++++++++++++++ multi_aviary_copymodel.py | 16 +- multi_aviary_submodel.py | 11 +- outputted_phase_info.py | 8 - single_aviary.py | 6 +- 24 files changed, 246 insertions(+), 285 deletions(-) rename multi_aviary_copymodel.html => N2s/n2_multi_aviary_copymodel.html (99%) rename multi_aviary_submodel.html => N2s/n2_multi_aviary_submodel.html (100%) rename multi_cannonball_copymodel.html => N2s/n2_multi_cannonball_copymodel.html (100%) rename multi_cannonball_copyparts.html => N2s/n2_multi_cannonball_copyparts.html (100%) rename single_aviary.html => N2s/n2_multi_min_time_to_climb.html (85%) rename c5.csv => c5_models/c5.csv (100%) rename c5_ferry.csv => c5_models/c5_ferry.csv (100%) rename c5_ferry_phase_info.py => c5_models/c5_ferry_phase_info.py (100%) rename c5_intermediate.csv => c5_models/c5_intermediate.csv (100%) rename c5_intermediate_phase_info.py => c5_models/c5_intermediate_phase_info.py (100%) rename c5_maxpayload.csv => c5_models/c5_maxpayload.csv (100%) rename c5_maxpayload_phase_info.py => c5_models/c5_maxpayload_phase_info.py (100%) rename cannonball.py => cannonball_models/cannonball.py (100%) rename multi_cannonball_copymodel.py => cannonball_models/multi_cannonball_copymodel.py (99%) rename multI_cannonball_copyparts.py => cannonball_models/multi_cannonball_copyparts.py (99%) delete mode 100644 checkdiff_0.txt delete mode 100644 checkdiff_1.txt create mode 100644 createN2.py rename min_time_climb.py => min_time_climb_models/min_time_climb.py (86%) create mode 100644 min_time_climb_models/multi_min_time_to_climb.py delete mode 100644 outputted_phase_info.py diff --git a/multi_aviary_copymodel.html b/N2s/n2_multi_aviary_copymodel.html similarity index 99% rename from multi_aviary_copymodel.html rename to N2s/n2_multi_aviary_copymodel.html index 5e3f7127c..e1f80b09c 100644 --- a/multi_aviary_copymodel.html +++ b/N2s/n2_multi_aviary_copymodel.html @@ -3255,7 +3255,7 @@

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diff --git a/multi_aviary_submodel.html b/N2s/n2_multi_aviary_submodel.html similarity index 100% rename from multi_aviary_submodel.html rename to N2s/n2_multi_aviary_submodel.html diff --git a/multi_cannonball_copymodel.html b/N2s/n2_multi_cannonball_copymodel.html similarity index 100% rename from multi_cannonball_copymodel.html rename to N2s/n2_multi_cannonball_copymodel.html diff --git a/multi_cannonball_copyparts.html b/N2s/n2_multi_cannonball_copyparts.html similarity index 100% rename from multi_cannonball_copyparts.html rename to N2s/n2_multi_cannonball_copyparts.html diff --git a/single_aviary.html b/N2s/n2_multi_min_time_to_climb.html similarity index 85% rename from single_aviary.html rename to N2s/n2_multi_min_time_to_climb.html index 5cb7b0313..7b4a51ce7 100644 --- a/single_aviary.html +++ b/N2s/n2_multi_min_time_to_climb.html @@ -3255,7 +3255,7 @@

Toolbar Help

diff --git a/c5.csv b/c5_models/c5.csv similarity index 100% rename from c5.csv rename to c5_models/c5.csv diff --git a/c5_ferry.csv b/c5_models/c5_ferry.csv similarity index 100% rename from c5_ferry.csv rename to c5_models/c5_ferry.csv diff --git a/c5_ferry_phase_info.py b/c5_models/c5_ferry_phase_info.py similarity index 100% rename from c5_ferry_phase_info.py rename to c5_models/c5_ferry_phase_info.py diff --git a/c5_intermediate.csv b/c5_models/c5_intermediate.csv similarity index 100% rename from c5_intermediate.csv rename to c5_models/c5_intermediate.csv diff --git a/c5_intermediate_phase_info.py b/c5_models/c5_intermediate_phase_info.py similarity index 100% rename from c5_intermediate_phase_info.py rename to c5_models/c5_intermediate_phase_info.py diff --git a/c5_maxpayload.csv b/c5_models/c5_maxpayload.csv similarity index 100% rename from c5_maxpayload.csv rename to c5_models/c5_maxpayload.csv diff --git a/c5_maxpayload_phase_info.py b/c5_models/c5_maxpayload_phase_info.py similarity index 100% rename from c5_maxpayload_phase_info.py rename to c5_models/c5_maxpayload_phase_info.py diff --git a/cannonball.py b/cannonball_models/cannonball.py similarity index 100% rename from cannonball.py rename to cannonball_models/cannonball.py diff --git a/multi_cannonball_copymodel.py b/cannonball_models/multi_cannonball_copymodel.py similarity index 99% rename from multi_cannonball_copymodel.py rename to cannonball_models/multi_cannonball_copymodel.py index 86eba920b..06effc571 100644 --- a/multi_cannonball_copymodel.py +++ b/cannonball_models/multi_cannonball_copymodel.py @@ -271,7 +271,9 @@ def runAvCannonball(kes=[4e3], weights=[1], makeN2=False): prob.setInitialVals(super_prob, subprefix) if makeN2: - om.n2(super_prob, outfile='multi_cannonball_copymodel.html') + sys.path.append('../') + from createN2 import createN2 + createN2(__file__, super_prob) dm.run_problem(super_prob) return super_prob, prefix, num_trajs, kes, weights diff --git a/multI_cannonball_copyparts.py b/cannonball_models/multi_cannonball_copyparts.py similarity index 99% rename from multI_cannonball_copyparts.py rename to cannonball_models/multi_cannonball_copyparts.py index 6ae9ea40f..327b983d2 100644 --- a/multI_cannonball_copyparts.py +++ b/cannonball_models/multi_cannonball_copyparts.py @@ -312,7 +312,9 @@ def runAvCannonball(kes=[4e3], weights=[1], makeN2=False): descent.interp('gam', [0, -45]), units='deg') if makeN2: - om.n2(super_prob, outfile='multi_cannonball_copyparts.html') + sys.path.append('../') + from createN2 import createN2 + createN2(__file__, super_prob) dm.run_problem(super_prob) return super_prob, prefix, num_trajs, kes, weights diff --git a/checkdiff_0.txt b/checkdiff_0.txt deleted file mode 100644 index f83bd9f6c..000000000 --- a/checkdiff_0.txt +++ /dev/null @@ -1,115 +0,0 @@ -time to climb: 217.2520 - -{'h': [array([[ 100. ], - [ 103.80775766], - [ 930.71769738], - [ 2018.93438639], - [ 1079.40343002], - [ 1079.40343002], - [ 100.50805119], - [ 1438.27501212], - [ 1602.57149682], - [ 1904.86259749], - [ 1904.86259749], - [ 3712.98528547], - [ 7915.33675389], - [ 9999.15426009], - [10000. ]]), array([[ 100. ], - [ 103.80775766], - [ 930.71769738], - [ 2018.93438639], - [ 1079.40343002], - [ 1079.40343002], - [ 100.50805119], - [ 1438.27501212], - [ 1602.57149682], - [ 1904.86259749], - [ 1904.86259749], - [ 3712.98528547], - [ 7915.33675389], - [ 9999.15426009], - [10000. ]])], 'r': [array([[ 0. ], - [ 2164.77845444], - [ 8473.61758302], - [16609.52293651], - [21085.59321018], - [21085.59321018], - [25851.44200422], - [34547.78294612], - [42985.06162566], - [47584.61382911], - [47584.61382911], - [51585.06694611], - [57432.22219674], - [63136.01715066], - [66759.00094891]]), array([[ 0. ], - [ 2164.77845444], - [ 8473.61758302], - [16609.52293651], - [21085.59321018], - [21085.59321018], - [25851.44200422], - [34547.78294612], - [42985.06162566], - [47584.61382911], - [47584.61382911], - [51585.06694611], - [57432.22219674], - [63136.01715066], - [66759.00094891]])], 'thrust': [array([[28040.14632377], - [31556.75143551], - [34632.8452248 ], - [34460.21958075], - [36675.29708332], - [36675.29708332], - [37236.1319661 ], - [34983.71270878], - [35728.22081081], - [34948.49191097], - [34948.49191097], - [29809.33906985], - [17293.91714046], - [13796.64728958], - [14828.82136199]]), array([[28040.14632377], - [31556.75143551], - [34632.8452248 ], - [34460.21958075], - [36675.29708332], - [36675.29708332], - [37236.1319661 ], - [34983.71270878], - [35728.22081081], - [34948.49191097], - [34948.49191097], - [29809.33906985], - [17293.91714046], - [13796.64728958], - [14828.82136199]])], 'v': [array([[135.964 ], - [208.97354876], - [320.68563986], - [359.68260029], - [388.15357668], - [388.15357668], - [390.55430662], - [351.23126062], - [374.4217715 ], - [366.01620721], - [366.01620721], - [335.87183483], - [271.12367442], - [274.0747837 ], - [299.52547901]]), array([[135.964 ], - [208.97354876], - [320.68563986], - [359.68260029], - [388.15357668], - [388.15357668], - [390.55430662], - [351.23126062], - [374.4217715 ], - [366.01620721], - [366.01620721], - [335.87183483], - [271.12367442], - [274.0747837 ], - [299.52547901]])]} \ No newline at end of file diff --git a/checkdiff_1.txt b/checkdiff_1.txt deleted file mode 100644 index ed7e9d1b6..000000000 --- a/checkdiff_1.txt +++ /dev/null @@ -1,115 +0,0 @@ -time to climb: 157.8796 - -{'h': [array([[ 100. ], - [ 515.07613051], - [ 1381.81693255], - [ 101.0458639 ], - [ 172.85115116], - [ 172.85115116], - [ 816.09835065], - [ 979.82075129], - [ 3756.26728314], - [ 5485.0832487 ], - [ 5485.0832487 ], - [ 6275.04817479], - [ 8240.0346346 ], - [ 9882.93735171], - [10000. ]]), array([[ 100. ], - [ 515.07613051], - [ 1381.81693255], - [ 101.0458639 ], - [ 172.85115116], - [ 172.85115116], - [ 816.09835065], - [ 979.82075129], - [ 3756.26728314], - [ 5485.0832487 ], - [ 5485.0832487 ], - [ 6275.04817479], - [ 8240.0346346 ], - [ 9882.93735171], - [10000. ]])], 'r': [array([[ 0. ], - [ 1206.82136366], - [ 3914.17528984], - [ 8451.44496816], - [11399.92146116], - [11399.92146116], - [14365.84009676], - [20639.75294521], - [25288.31640182], - [27271.04173952], - [27271.04173952], - [29881.11674619], - [34591.83602889], - [39138.45065608], - [41792.19739333]]), array([[ 0. ], - [ 1206.82136366], - [ 3914.17528984], - [ 8451.44496816], - [11399.92146116], - [11399.92146116], - [14365.84009676], - [20639.75294521], - [25288.31640182], - [27271.04173952], - [27271.04173952], - [29881.11674619], - [34591.83602889], - [39138.45065608], - [41792.19739333]])], 'thrust': [array([[28040.14632377], - [27840.96435929], - [27801.17232139], - [36538.29991158], - [36783.4253821 ], - [36783.4253821 ], - [35767.31775612], - [35695.44888759], - [27672.82594699], - [23340.56296487], - [23340.56296487], - [22190.71836546], - [17569.77743693], - [14367.81307749], - [14828.82136199]]), array([[28040.14632377], - [27840.96435929], - [27801.17232139], - [36538.29991158], - [36783.4253821 ], - [36783.4253821 ], - [35767.31775612], - [35695.44888759], - [27672.82594699], - [23340.56296487], - [23340.56296487], - [22190.71836546], - [17569.77743693], - [14367.81307749], - [14828.82136199]])], 'v': [array([[135.964 ], - [152.24096545], - [200.85748578], - [328.70862359], - [346.73855457], - [346.73855457], - [346.4022868 ], - [351.79430504], - [304.2851606 ], - [294.30253244], - [294.30253244], - [302.5443161 ], - [289.57065259], - [283.7594102 ], - [299.52547901]]), array([[135.964 ], - [152.24096545], - [200.85748578], - [328.70862359], - [346.73855457], - [346.73855457], - [346.4022868 ], - [351.79430504], - [304.2851606 ], - [294.30253244], - [294.30253244], - [302.5443161 ], - [289.57065259], - [283.7594102 ], - [299.52547901]])]} \ No newline at end of file diff --git a/createN2.py b/createN2.py new file mode 100644 index 000000000..a41f99de6 --- /dev/null +++ b/createN2.py @@ -0,0 +1,8 @@ +from openmdao.api import n2 +from os.path import basename, dirname, join, abspath + + +def createN2(fileref, prob): + n2folder = join(dirname(abspath(__file__)), "N2s") + n2(prob, outfile=join(n2folder, + f"n2_{basename(fileref).split('.')[0]}.html")) diff --git a/min_time_climb.py b/min_time_climb_models/min_time_climb.py similarity index 86% rename from min_time_climb.py rename to min_time_climb_models/min_time_climb.py index c51ea006f..1f6e77b11 100644 --- a/min_time_climb.py +++ b/min_time_climb_models/min_time_climb.py @@ -4,6 +4,7 @@ import matplotlib.pyplot as plt import numpy as np import sys +from createN2 import createN2 def min_time_climb(height=20e3, @@ -104,11 +105,11 @@ def min_time_climb(height=20e3, p['traj.phase0.t_initial'] = 0.0 p['traj.phase0.t_duration'] = 350.0 - p['traj.phase0.states:r'] = phase.interp('r', [0.0, 111319.54]) + p['traj.phase0.states:r'] = phase.interp('r', [0.0, 100e3]) p['traj.phase0.states:h'] = phase.interp('h', [100.0, height]) p['traj.phase0.states:v'] = phase.interp('v', [135.964, 283.159]) p['traj.phase0.states:gam'] = phase.interp('gam', [0.0, 0.0]) - p['traj.phase0.states:m'] = phase.interp('m', [19030.468, 16841.431]) + p['traj.phase0.states:m'] = phase.interp('m', [30e3, 16e3]) p['traj.phase0.controls:alpha'] = phase.interp('alpha', [0.0, 0.0]) dm.run_problem(p, simulate=True) @@ -152,28 +153,34 @@ def checkDeviation(filenum=0): def multiHeightTest(): - heights = [12e3, 20e3] + heights = [6e3, 18e3] prefix = 'traj.phase0.timeseries.' - plotvars = {'r': ['h'], 'time': ['v', 'thrust', 'm_dot', 'alpha']} - plotunits = {'r': ['km', 'km'], 'time': ['s', 'm/s', 'kN', 'kg/s', 'deg']} + # these dictionaries are defined with the x-variable and its units as the key, + # with corresponding y-variables and units in a list as the key's value + # allows for multiple y vars to be plotted against same x var + plotvars = {'r': ['h'], 'time': ['h', 'v', 'thrust', 'm_dot', 'alpha']} + plotunits = {'km': ['km'], 's': ['km', 'm/s', 'kN', 'kg/s', 'deg']} varnames = {prefix+x: [prefix+y for y in ylst] for x, ylst in plotvars.items()} - numplots = sum([len(item) for item in plotvars.values()]) + numplots = sum([len(yvars) for yvars in plotvars.values()]) data = {f'h{i}': {} for i in range(len(heights))} + times = [] for j, height in enumerate(heights): p = min_time_climb(height=height) wing_area = p.get_val('traj.phase0.parameters:S', units='m**2')[0] sol = om.CaseReader('dymos_solution.db').get_case('final') sim = om.CaseReader('dymos_simulation.db').get_case('final') + timetoclimb = p.get_val('traj.phase0.timeseries.time', units='s')[-1][0] + times.append(timetoclimb) print("\n\n=======================================") print(f"Time to climb {height/1e3} km: " + - f"{p.get_val('traj.phase0.timeseries.time',units='s')[-1][0]:.2f}" + + f"{timetoclimb:.2f}" + f" s with wing area: {wing_area} sqm") - for xname, unitkey in zip(varnames.keys(), plotunits.keys()): - xsol = sol.get_val(xname, units=plotunits[unitkey][0]) - xsim = sim.get_val(xname, units=plotunits[unitkey][0]) + for xname, xunit in zip(varnames.keys(), plotunits.keys()): + xsol = sol.get_val(xname, units=xunit) + xsim = sim.get_val(xname, units=xunit) if not xname in data.keys(): data[f'h{j}'][xname] = {'x': (xsol, xsim), 'y': []} for i, yname in enumerate(varnames[xname]): @@ -181,31 +188,34 @@ def multiHeightTest(): data[f'h{j}'][xname]['yname'] = [yname] else: data[f'h{j}'][xname]['yname'].append(yname) - ysol = sol.get_val(yname, units=plotunits[unitkey][i+1]) - ysim = sim.get_val(yname, units=plotunits[unitkey][i+1]) + ysol = sol.get_val(yname, units=plotunits[xunit][i]) + ysim = sim.get_val(yname, units=plotunits[xunit][i]) data[f'h{j}'][xname]['y'].append((ysol, ysim)) - colors = ['r', 'b'] + colors = ['r', 'b', 'g', 'm', 'k'] legendlst = [] for j in range(len(heights)): datadict = data[f'h{j}'] - i = 1 - for xname, unitkey in zip(datadict.keys(), plotunits.keys()): + plot_idx = 1 + for xname, xunit in zip(datadict.keys(), plotunits.keys()): xsol, xsim = datadict[xname]['x'] - for (ysol, ysim), yname, yunit in zip(datadict[xname]['y'], datadict[xname]['yname'], plotunits[unitkey][1:]): - plt.subplot(int(numplots/2), numplots-int(numplots/2), i) - # if max(ysim) > 1e3: - # ysol, ysim = ysol/1e3, ysim/1e3 + for (ysol, ysim), yname, yunit in zip(datadict[xname]['y'], datadict[xname]['yname'], plotunits[xunit]): + plt.subplot(2, int(numplots/2), plot_idx) plt.plot(xsol, ysol, f'{colors[j]}o', fillstyle='none') plt.plot(xsim, ysim, colors[j]) - plt.xlabel(f"{xname.split(prefix)[1]} ({plotunits[unitkey][0]})") + plt.xlabel(f"{xname.split(prefix)[1]} ({xunit})") plt.ylabel(f"{yname.split(prefix)[1]} ({yunit})") - if j == 0: - plt.grid(visible=True) - i += 1 + plt.grid(visible=True) + plot_idx += 1 + for datatype in ('Solution', 'Simulation'): - legendlst.append(f"{datatype} @ h = {heights[j]/1e3} km") - plt.figlegend(legendlst) + legendlst.append(f"h = {heights[j]/1e3} km, {datatype} ") + plt.figlegend(legendlst, ncols=2, loc='lower center') + plt.tight_layout(pad=2) + titlestr = ", ".join( + [f"{time:.1f} s to h = {height/1e3:.1f} km" for time, height + in zip(times, heights)]) + plt.suptitle(f"Minimum Time to Climb: "+titlestr) plt.show() @@ -216,7 +226,7 @@ def multiHeightTest(): optimization takes a very different number of iterations, and the profile looks very different. Time to climb is also different.""" if __name__ == '__main__': - if len(sys.argv) > 1 and 'filenum' in sys.argv[1]: + if 'filenum' in sys.argv[1]: checkDeviation(filenum=sys.argv[1].split('filenum=')[1]) else: multiHeightTest() diff --git a/min_time_climb_models/multi_min_time_to_climb.py b/min_time_climb_models/multi_min_time_to_climb.py new file mode 100644 index 000000000..0a710dc61 --- /dev/null +++ b/min_time_climb_models/multi_min_time_to_climb.py @@ -0,0 +1,178 @@ +import openmdao.api as om +import dymos as dm +from dymos.examples.min_time_climb.min_time_climb_ode import MinTimeClimbODE +import matplotlib.pyplot as plt +import numpy as np +import sys + + +class MinTimeClimbProblem(om.Problem): + def __init__(self, target_height=20e3, initial_mass=20e3): + super().__init__() + self.model = om.Group() + self.target_height = target_height + self.initial_mass = initial_mass + + def setOptimizer(self, driver='scipy', optimizer='SLSQP'): + self.driver = om.pyOptSparseDriver() if driver == "pyoptsparse" else om.ScipyOptimizeDriver() + self.driver.options['optimizer'] = optimizer + self.driver.declare_coloring() + if optimizer == 'SNOPT': + self.driver.opt_settings['Major iterations limit'] = 1000 + self.driver.opt_settings['iSumm'] = 6 + self.driver.opt_settings['Major feasibility tolerance'] = 1.0E-6 + self.driver.opt_settings['Major optimality tolerance'] = 1.0E-6 + self.driver.opt_settings['Function precision'] = 1.0E-12 + self.driver.opt_settings['Linesearch tolerance'] = 0.1 + self.driver.opt_settings['Major step limit'] = 0.5 + elif optimizer == 'IPOPT': + self.driver.opt_settings['tol'] = 1.0E-5 + self.driver.opt_settings['print_level'] = 0 + self.driver.opt_settings['mu_strategy'] = 'monotone' + self.driver.opt_settings['bound_mult_init_method'] = 'mu-based' + self.driver.opt_settings['mu_init'] = 0.01 + + self.model.linear_solver = om.DirectSolver() + + def addTrajectory(self, num_seg=9, transcription='gauss-lobatto', + transcription_order=3): + t = {'gauss-lobatto': dm.GaussLobatto( + num_segments=num_seg, order=transcription_order), + 'radau-ps': dm.Radau(num_segments=num_seg, order=transcription_order)} + + traj = dm.Trajectory() + phase = dm.Phase(ode_class=MinTimeClimbODE, transcription=t[transcription]) + traj.add_phase('phase0', phase) + + height = self.target_height + time_name = 'time' + add_rate = False + phase.set_time_options(fix_initial=True, duration_bounds=(50, 600), + duration_ref=100.0, name=time_name) + + phase.add_state('r', fix_initial=True, lower=0, upper=1.0E6, + ref=1.0E3, defect_ref=1.0E3, units='m', + rate_source='flight_dynamics.r_dot') + + phase.add_state('h', fix_initial=True, lower=0, upper=height, + ref=height, defect_ref=height, units='m', + rate_source='flight_dynamics.h_dot', targets=['h']) + + phase.add_state('v', fix_initial=True, lower=10.0, + ref=1.0E2, defect_ref=1.0E2, units='m/s', + rate_source='flight_dynamics.v_dot', targets=['v']) + + phase.add_state('gam', fix_initial=True, lower=-1.5, upper=1.5, + ref=1.0, defect_ref=1.0, units='rad', + rate_source='flight_dynamics.gam_dot', targets=['gam']) + + phase.add_state('m', fix_initial=True, lower=10.0, upper=1.0E5, + ref=10_000, defect_ref=10_000, units='kg', + rate_source='prop.m_dot', targets=['m']) + + phase.add_control('alpha', units='deg', lower=-8.0, upper=8.0, scaler=1.0, + rate_continuity=True, rate_continuity_scaler=100.0, + rate2_continuity=False, targets=['alpha']) + + phase.add_parameter('S', val=49.2386, units='m**2', opt=True, targets=['S']) + phase.add_parameter('Isp', val=1600.0, units='s', opt=False, targets=['Isp']) + phase.add_parameter('throttle', val=1.0, opt=False, targets=['throttle']) + + phase.add_boundary_constraint( + 'h', loc='final', equals=height) # , scaler=1.0E-3) + phase.add_boundary_constraint('aero.mach', loc='final', equals=1.0) + phase.add_boundary_constraint('gam', loc='final', equals=0.0) + + phase.add_path_constraint(name='h', lower=100.0, upper=height, ref=height) + phase.add_path_constraint(name='aero.mach', lower=0.1, upper=1.8) + + # Unnecessary but included to test capability + phase.add_path_constraint(name='alpha', lower=-8, upper=8) + phase.add_path_constraint(name=f'{time_name}', lower=0, upper=400) + phase.add_path_constraint(name=f'{time_name}_phase', lower=0, upper=400) + + # Minimize time at the end of the phase + # phase.add_objective(time_name, loc='final', ref=1.0) + + # test mixing wildcard ODE variable expansion and unit overrides + phase.add_timeseries_output(['aero.*', 'prop.thrust', 'prop.m_dot'], + units={'aero.f_lift': 'lbf', 'prop.thrust': 'lbf'}) + + # test adding rate as timeseries output + if add_rate: + phase.add_timeseries_rate_output('aero.mach') + + self.phase = phase + self.model.add_subsystem('traj', traj, promotes=['*']) + + def setInitialConditions(self, super_prob=None, prefix=""): + ref = self + if super_prob is not None and prefix != "": + ref = super_prob + ref[prefix+'traj.phase0.t_initial'] = 0.0 + ref[prefix+'traj.phase0.t_duration'] = 350.0 + ref[prefix+'traj.phase0.states:r'] = self.phase.interp('r', [0.0, 100e3]) + ref[prefix+'traj.phase0.states:h'] = self.phase.interp( + 'h', [100.0, self.target_height]) + ref[prefix+'traj.phase0.states:v'] = self.phase.interp('v', [135.964, 283.159]) + ref[prefix+'traj.phase0.states:gam'] = self.phase.interp('gam', [0.0, 0.0]) + ref[prefix+'traj.phase0.states:m'] = self.phase.interp( + 'm', [self.initial_mass, 10e3]) + ref[prefix+'traj.phase0.controls:alpha'] = self.phase.interp('alpha', [0.0, 0.0]) + + +if __name__ == '__main__': + makeN2 = True if "n2" in sys.argv else False + heights = [6e3, 18e3] + weights = [1, 1] + num_missions = len(heights) + super_prob = om.Problem() + probs = [] + for i, height in enumerate(heights): + prob = MinTimeClimbProblem(height, 30e3) + # prob.setOptimizer() + prob.addTrajectory() + super_prob.model.add_subsystem( + f"group_{i}", prob.model, promotes=[('phase0.parameters:S', 'S')]) + probs.append(prob) + + super_prob.model.add_design_var('S', lower=1, upper=100, units='m**2') + + times = [f"time_{i}" for i in range(num_missions)] + weighted_sum_str = "+".join([f"{time}*{weight}" for time, + weight in zip(times, weights)]) + super_prob.model.add_subsystem('compoundComp', om.ExecComp( + "compound_time=" + weighted_sum_str), + promotes=['compound_time', *times]) + + for i in range(num_missions): + super_prob.model.connect(f"group_{i}.phase0.t", times[i], src_indices=-1) + super_prob.model.add_objective('compound_time') + + super_prob.driver = om.ScipyOptimizeDriver() + super_prob.driver.options['optimizer'] = 'SLSQP' + super_prob.driver.declare_coloring() + super_prob.model.linear_solver = om.DirectSolver() + + super_prob.setup() + if makeN2: + sys.path.append('../') + from createN2 import createN2 + createN2(__file__, super_prob) + for i, prob in enumerate(probs): + prob.setInitialConditions(super_prob, f"group_{i}.") + + dm.run_problem(super_prob) + wing_area = super_prob.get_val('S', units='m**2')[0] + # sol = om.CaseReader('dymos_solution.db').get_case('final') + # sim = om.CaseReader('dymos_simulation.db').get_case('final') + print("\n\n=====================================") + for i in range(num_missions): + timetoclimb = super_prob.get_val(f'group_{i}.phase0.t', units='s')[-1] + print(f"TtoC: {timetoclimb}, S: {wing_area}") + xsol = super_prob.get_val(f"group_{i}.phase0.timeseries.r") + ysol = super_prob.get_val(f"group_{i}.phase0.timeseries.h") + plt.plot(xsol, ysol) + + plt.grid() + plt.show() diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index 11e61451b..e0a0cb23f 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -12,9 +12,9 @@ import dymos as dm import numpy as np from aviary.variable_info.enums import ProblemType, AnalysisScheme -from c5_ferry_phase_info import phase_info as c5_ferry_phase_info -from c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info -from c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info +from c5_models.c5_ferry_phase_info import phase_info as c5_ferry_phase_info +from c5_models.c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info +from c5_models.c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info from aviary.variable_info.variable_meta_data import _MetaData as MetaData from aviary.variable_info.variables import Mission, Dynamic from aviary.interface.methods_for_level2 import wrapped_convert_units @@ -102,10 +102,7 @@ def setup_wrapper(self): with warnings.catch_warnings(): warnings.simplefilter("ignore", om.OpenMDAOWarning) warnings.simplefilter("ignore", om.PromotionWarning) - self.setup() - - def create_N2(self, outfile='multi_aviary_copymodel.html'): - om.n2(self, outfile=outfile) + self.setup(check='all') def run(self): self.run_model() @@ -115,7 +112,7 @@ def run(self): if __name__ == '__main__': makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False - planes = ['c5_maxpayload.csv', 'c5_intermediate.csv'] + planes = ['c5_models/c5_maxpayload.csv', 'c5_models/c5_intermediate.csv'] phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] weights = [1, 1] super_prob = MultiMissionProblem(planes, phase_infos, weights) @@ -133,7 +130,8 @@ def run(self): print(super_prob.get_val(super_prob.group_prefix + f"_{i}.mission:summary:range")) if makeN2: - super_prob.create_N2() + from createN2 import createN2 + createN2(__file__, super_prob) super_prob.run() # def initvals(self): diff --git a/multi_aviary_submodel.py b/multi_aviary_submodel.py index 7435aebd6..c1a640c72 100644 --- a/multi_aviary_submodel.py +++ b/multi_aviary_submodel.py @@ -9,11 +9,11 @@ import aviary.api as av import openmdao.api as om import dymos as dm -from c5_ferry_phase_info import phase_info as c5_ferry_phase_info -from c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info -from c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info +from c5_models.c5_ferry_phase_info import phase_info as c5_ferry_phase_info +from c5_models.c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info +from c5_models.c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info -planes = ['c5_maxpayload.csv', 'c5_intermediate.csv'] +planes = ['c5_models/c5_maxpayload.csv', 'c5_models/c5_intermediate.csv'] phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] weights = [1, 1] num_missions = len(weights) @@ -77,7 +77,8 @@ prob.set_initial_guesses() if makeN2: - om.n2(super_prob, outfile='multi_aviary_submodel.html') + from createN2 import createN2 + createN2(__file__, super_prob) dm.run_problem(super_prob) print(super_prob.check_partials()) diff --git a/outputted_phase_info.py b/outputted_phase_info.py deleted file mode 100644 index 9e9fd754f..000000000 --- a/outputted_phase_info.py +++ /dev/null @@ -1,8 +0,0 @@ -phase_info = { - "pre_mission": {"include_takeoff": False, "optimize_mass": True}, - "post_mission": { - "include_landing": False, - "constrain_range": True, - "target_range": (0.0, "nmi"), - }, -} diff --git a/single_aviary.py b/single_aviary.py index 35acbcb4f..5966b37d6 100644 --- a/single_aviary.py +++ b/single_aviary.py @@ -1,9 +1,9 @@ +from c5_models.c5_ferry_phase_info import phase_info as c5_ferry_phase_info +from c5_models.c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info +from c5_models.c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info import aviary.api as av import openmdao.api as om import sys -from c5_ferry_phase_info import phase_info as c5_ferry_phase_info -from c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info -from c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info def modify_plane(orig_filename, payloads, ranges): From cf1fcfdbf288d336c78fc825fd35862781bc5aed Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Thu, 1 Aug 2024 09:50:21 -0400 Subject: [PATCH 024/113] checkpt --- min_time_climb_models/min_time_climb.py | 1 - 1 file changed, 1 deletion(-) diff --git a/min_time_climb_models/min_time_climb.py b/min_time_climb_models/min_time_climb.py index 1f6e77b11..44b07395a 100644 --- a/min_time_climb_models/min_time_climb.py +++ b/min_time_climb_models/min_time_climb.py @@ -4,7 +4,6 @@ import matplotlib.pyplot as plt import numpy as np import sys -from createN2 import createN2 def min_time_climb(height=20e3, From 9053df3d47b6d653c1dd70c5474c9a6de63b2a88 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Thu, 1 Aug 2024 15:16:04 -0400 Subject: [PATCH 025/113] reasonable multi mission for min time to climb, plot helper for min time funcs --- min_time_climb_models/min_time_climb.py | 129 ++++++------------ .../multi_min_time_to_climb.py | 53 +++---- min_time_climb_models/plot_helper.py | 88 ++++++++++++ 3 files changed, 163 insertions(+), 107 deletions(-) create mode 100644 min_time_climb_models/plot_helper.py diff --git a/min_time_climb_models/min_time_climb.py b/min_time_climb_models/min_time_climb.py index 44b07395a..a49c956f9 100644 --- a/min_time_climb_models/min_time_climb.py +++ b/min_time_climb_models/min_time_climb.py @@ -1,19 +1,21 @@ import openmdao.api as om import dymos as dm from dymos.examples.min_time_climb.min_time_climb_ode import MinTimeClimbODE +from plot_helper import make_min_time_climb_plot import matplotlib.pyplot as plt import numpy as np import sys -def min_time_climb(height=20e3, - optimizer='SLSQP', num_seg=9, transcription='gauss-lobatto', - transcription_order=3, force_alloc_complex=False, add_rate=False, - time_name='time'): +def min_time_climb( + height=20e3, driver='scipy', optimizer='SLSQP', num_seg=15, + transcription='gauss-lobatto', transcription_order=3, force_alloc_complex=False, + add_rate=False, time_name='time', simfile='dymos_simulatin.db', + solfile='dymos_solution.db'): p = om.Problem(model=om.Group()) - p.driver = om.ScipyOptimizeDriver() + p.driver = om.ScipyOptimizeDriver() if driver == 'scipy' else om.pyOptSparseDriver() p.driver.options['optimizer'] = optimizer p.driver.declare_coloring() @@ -41,8 +43,6 @@ def min_time_climb(height=20e3, phase = dm.Phase(ode_class=MinTimeClimbODE, transcription=t[transcription]) traj.add_phase('phase0', phase) - p.model.add_subsystem('traj', traj) - phase.set_time_options(fix_initial=True, duration_bounds=(50, 400), duration_ref=100.0, name=time_name) @@ -70,7 +70,8 @@ def min_time_climb(height=20e3, rate_continuity=True, rate_continuity_scaler=100.0, rate2_continuity=False, targets=['alpha']) - phase.add_parameter('S', val=49.2386, units='m**2', opt=True, targets=['S']) + phase.add_parameter('S', val=42.554663555518836, + units='m**2', opt=True, targets=['S']) phase.add_parameter('Isp', val=1600.0, units='s', opt=False, targets=['Isp']) phase.add_parameter('throttle', val=1.0, opt=False, targets=['throttle']) @@ -80,6 +81,7 @@ def min_time_climb(height=20e3, phase.add_path_constraint(name='h', lower=100.0, upper=height, ref=height) phase.add_path_constraint(name='aero.mach', lower=0.1, upper=1.8) + # phase.add_path_constraint(name='gam', lower=-23, upper=23, units='deg') # Unnecessary but included to test capability phase.add_path_constraint(name='alpha', lower=-8, upper=8) @@ -97,21 +99,24 @@ def min_time_climb(height=20e3, if add_rate: phase.add_timeseries_rate_output('aero.mach') + p.model.add_subsystem('traj', traj, promotes=['*']) + p.model.linear_solver = om.DirectSolver() p.setup(check=True, force_alloc_complex=force_alloc_complex) - p['traj.phase0.t_initial'] = 0.0 - p['traj.phase0.t_duration'] = 350.0 + p.set_val('phase0.t_initial', 0.0) + p.set_val('phase0.t_duration', 350.0) - p['traj.phase0.states:r'] = phase.interp('r', [0.0, 100e3]) - p['traj.phase0.states:h'] = phase.interp('h', [100.0, height]) - p['traj.phase0.states:v'] = phase.interp('v', [135.964, 283.159]) - p['traj.phase0.states:gam'] = phase.interp('gam', [0.0, 0.0]) - p['traj.phase0.states:m'] = phase.interp('m', [30e3, 16e3]) - p['traj.phase0.controls:alpha'] = phase.interp('alpha', [0.0, 0.0]) + p.set_val('phase0.states:r', phase.interp('r', [0.0, 100e3])) + p.set_val('phase0.states:h', phase.interp('h', [100.0, height])) + p.set_val('phase0.states:v', phase.interp('v', [135.964, 283.159])) + p.set_val('phase0.states:gam', phase.interp('gam', [0.0, 0.0])) + p.set_val('phase0.states:m', phase.interp('m', [30e3, 16e3])) + p.set_val('phase0.controls:alpha', phase.interp('alpha', [0.0, 0.0])) - dm.run_problem(p, simulate=True) + dm.run_problem(p, simulate=True, simulation_record_file=simfile, + solution_record_file=solfile) return p @@ -153,79 +158,35 @@ def checkDeviation(filenum=0): def multiHeightTest(): heights = [6e3, 18e3] - prefix = 'traj.phase0.timeseries.' - # these dictionaries are defined with the x-variable and its units as the key, - # with corresponding y-variables and units in a list as the key's value - # allows for multiple y vars to be plotted against same x var - plotvars = {'r': ['h'], 'time': ['h', 'v', 'thrust', 'm_dot', 'alpha']} - plotunits = {'km': ['km'], 's': ['km', 'm/s', 'kN', 'kg/s', 'deg']} - varnames = {prefix+x: [prefix+y for y in ylst] for x, ylst in plotvars.items()} - numplots = sum([len(yvars) for yvars in plotvars.values()]) - data = {f'h{i}': {} for i in range(len(heights))} times = [] + areas = [] + outfiles = {'sol': [], 'sim': []} for j, height in enumerate(heights): - p = min_time_climb(height=height) - wing_area = p.get_val('traj.phase0.parameters:S', units='m**2')[0] - sol = om.CaseReader('dymos_solution.db').get_case('final') - sim = om.CaseReader('dymos_simulation.db').get_case('final') - timetoclimb = p.get_val('traj.phase0.timeseries.time', units='s')[-1][0] - times.append(timetoclimb) + solfile = f'single_solution_{j}.db' + simfile = f'single_simulation_{j}.db' + outfiles['sim'].append(simfile) + outfiles['sol'].append(solfile) + p = min_time_climb( + height=height, simfile=simfile, + solfile=solfile) + areas.append(p.get_val('phase0.parameters:S', units='m**2')[0]) + times.append(p.get_val('phase0.timeseries.time', units='s')[-1][0]) - print("\n\n=======================================") + print("\n\n=======================================") + # print(p.get_val('phase.flight_dynamics.gam_dot')) + for time, area, height in zip(times, areas, heights): print(f"Time to climb {height/1e3} km: " + - f"{timetoclimb:.2f}" + - f" s with wing area: {wing_area} sqm") - - for xname, xunit in zip(varnames.keys(), plotunits.keys()): - xsol = sol.get_val(xname, units=xunit) - xsim = sim.get_val(xname, units=xunit) - if not xname in data.keys(): - data[f'h{j}'][xname] = {'x': (xsol, xsim), 'y': []} - for i, yname in enumerate(varnames[xname]): - if not 'yname' in data[f'h{j}'][xname].keys(): - data[f'h{j}'][xname]['yname'] = [yname] - else: - data[f'h{j}'][xname]['yname'].append(yname) - ysol = sol.get_val(yname, units=plotunits[xunit][i]) - ysim = sim.get_val(yname, units=plotunits[xunit][i]) - data[f'h{j}'][xname]['y'].append((ysol, ysim)) - - colors = ['r', 'b', 'g', 'm', 'k'] - legendlst = [] - for j in range(len(heights)): - datadict = data[f'h{j}'] - plot_idx = 1 - for xname, xunit in zip(datadict.keys(), plotunits.keys()): - xsol, xsim = datadict[xname]['x'] - for (ysol, ysim), yname, yunit in zip(datadict[xname]['y'], datadict[xname]['yname'], plotunits[xunit]): - plt.subplot(2, int(numplots/2), plot_idx) - plt.plot(xsol, ysol, f'{colors[j]}o', fillstyle='none') - plt.plot(xsim, ysim, colors[j]) - plt.xlabel(f"{xname.split(prefix)[1]} ({xunit})") - plt.ylabel(f"{yname.split(prefix)[1]} ({yunit})") - plt.grid(visible=True) - plot_idx += 1 - - for datatype in ('Solution', 'Simulation'): - legendlst.append(f"h = {heights[j]/1e3} km, {datatype} ") - plt.figlegend(legendlst, ncols=2, loc='lower center') - plt.tight_layout(pad=2) - titlestr = ", ".join( - [f"{time:.1f} s to h = {height/1e3:.1f} km" for time, height - in zip(times, heights)]) - plt.suptitle(f"Minimum Time to Climb: "+titlestr) - plt.show() - - -"""It seems that when the dymos problem is run multiple times within a single -run of this script, the output values are all the same for all timeseries. - -But when the script itself is run again, these values can differ very largely, -optimization takes a very different number of iterations, and the profile looks very -different. Time to climb is also different.""" + f"{time:.2f}" + + f" s with wing area: {area} sqm") + make_min_time_climb_plot( + solfile=outfiles['sol'], + simfile=outfiles['sim'], + omitpromote='traj') + + if __name__ == '__main__': - if 'filenum' in sys.argv[1]: + if 'filenum' in sys.argv: checkDeviation(filenum=sys.argv[1].split('filenum=')[1]) else: multiHeightTest() diff --git a/min_time_climb_models/multi_min_time_to_climb.py b/min_time_climb_models/multi_min_time_to_climb.py index 0a710dc61..b378526ef 100644 --- a/min_time_climb_models/multi_min_time_to_climb.py +++ b/min_time_climb_models/multi_min_time_to_climb.py @@ -1,6 +1,7 @@ import openmdao.api as om import dymos as dm from dymos.examples.min_time_climb.min_time_climb_ode import MinTimeClimbODE +from plot_helper import make_min_time_climb_plot import matplotlib.pyplot as plt import numpy as np import sys @@ -34,7 +35,7 @@ def setOptimizer(self, driver='scipy', optimizer='SLSQP'): self.model.linear_solver = om.DirectSolver() - def addTrajectory(self, num_seg=9, transcription='gauss-lobatto', + def addTrajectory(self, num_seg=15, transcription='gauss-lobatto', transcription_order=3): t = {'gauss-lobatto': dm.GaussLobatto( num_segments=num_seg, order=transcription_order), @@ -85,6 +86,7 @@ def addTrajectory(self, num_seg=9, transcription='gauss-lobatto', phase.add_path_constraint(name='h', lower=100.0, upper=height, ref=height) phase.add_path_constraint(name='aero.mach', lower=0.1, upper=1.8) + # phase.add_path_constraint(name='gam', lower=-23, upper=23, units='deg') # Unnecessary but included to test capability phase.add_path_constraint(name='alpha', lower=-8, upper=8) @@ -109,16 +111,19 @@ def setInitialConditions(self, super_prob=None, prefix=""): ref = self if super_prob is not None and prefix != "": ref = super_prob - ref[prefix+'traj.phase0.t_initial'] = 0.0 - ref[prefix+'traj.phase0.t_duration'] = 350.0 - ref[prefix+'traj.phase0.states:r'] = self.phase.interp('r', [0.0, 100e3]) - ref[prefix+'traj.phase0.states:h'] = self.phase.interp( - 'h', [100.0, self.target_height]) - ref[prefix+'traj.phase0.states:v'] = self.phase.interp('v', [135.964, 283.159]) - ref[prefix+'traj.phase0.states:gam'] = self.phase.interp('gam', [0.0, 0.0]) - ref[prefix+'traj.phase0.states:m'] = self.phase.interp( - 'm', [self.initial_mass, 10e3]) - ref[prefix+'traj.phase0.controls:alpha'] = self.phase.interp('alpha', [0.0, 0.0]) + phase = self.phase + ref.set_val(prefix+'traj.phase0.t_initial', 0.0) + ref.set_val(prefix+'traj.phase0.t_duration', 350.0) + + ref.set_val(prefix+'traj.phase0.states:r', phase.interp('r', [0.0, 100e3])) + ref.set_val(prefix+'traj.phase0.states:h', phase.interp( + 'h', [100.0, self.target_height])) + ref.set_val(prefix+'traj.phase0.states:v', phase.interp('v', [135.964, 283.159])) + ref.set_val(prefix+'traj.phase0.states:gam', phase.interp('gam', [0.0, 0.0])) + ref.set_val(prefix+'traj.phase0.states:m', + phase.interp('m', [self.initial_mass, 16e3])) + ref.set_val(prefix+'traj.phase0.controls:alpha', + phase.interp('alpha', [0.0, 0.0])) if __name__ == '__main__': @@ -126,11 +131,11 @@ def setInitialConditions(self, super_prob=None, prefix=""): heights = [6e3, 18e3] weights = [1, 1] num_missions = len(heights) + super_prob = om.Problem() probs = [] for i, height in enumerate(heights): prob = MinTimeClimbProblem(height, 30e3) - # prob.setOptimizer() prob.addTrajectory() super_prob.model.add_subsystem( f"group_{i}", prob.model, promotes=[('phase0.parameters:S', 'S')]) @@ -146,11 +151,14 @@ def setInitialConditions(self, super_prob=None, prefix=""): promotes=['compound_time', *times]) for i in range(num_missions): - super_prob.model.connect(f"group_{i}.phase0.t", times[i], src_indices=-1) + super_prob.model.connect( + f"group_{i}.phase0.t", times[i], + src_indices=-1) super_prob.model.add_objective('compound_time') - super_prob.driver = om.ScipyOptimizeDriver() - super_prob.driver.options['optimizer'] = 'SLSQP' + # super_prob.driver = om.ScipyOptimizeDriver() + super_prob.driver = om.pyOptSparseDriver() + super_prob.driver.options['optimizer'] = 'SLSQP' # 'IPOPT' super_prob.driver.declare_coloring() super_prob.model.linear_solver = om.DirectSolver() @@ -159,20 +167,19 @@ def setInitialConditions(self, super_prob=None, prefix=""): sys.path.append('../') from createN2 import createN2 createN2(__file__, super_prob) + for i, prob in enumerate(probs): prob.setInitialConditions(super_prob, f"group_{i}.") - dm.run_problem(super_prob) + dm.run_problem(super_prob, simulate=True) + wing_area = super_prob.get_val('S', units='m**2')[0] - # sol = om.CaseReader('dymos_solution.db').get_case('final') - # sim = om.CaseReader('dymos_simulation.db').get_case('final') print("\n\n=====================================") for i in range(num_missions): timetoclimb = super_prob.get_val(f'group_{i}.phase0.t', units='s')[-1] print(f"TtoC: {timetoclimb}, S: {wing_area}") - xsol = super_prob.get_val(f"group_{i}.phase0.timeseries.r") - ysol = super_prob.get_val(f"group_{i}.phase0.timeseries.h") - plt.plot(xsol, ysol) - plt.grid() - plt.show() + make_min_time_climb_plot( + solfile='dymos_solution.db', + simfile=['dymos_simulation.db', 'dymos_simulation_1.db'], + solprefix='group', omitpromote='traj') diff --git a/min_time_climb_models/plot_helper.py b/min_time_climb_models/plot_helper.py new file mode 100644 index 000000000..cb3d3db68 --- /dev/null +++ b/min_time_climb_models/plot_helper.py @@ -0,0 +1,88 @@ +import matplotlib.pyplot as plt +from openmdao.api import CaseReader + + +def make_min_time_climb_plot( + solfile='dymos_solution.db', simfile='dymos_simulation.db', solprefix='', + omitpromote=None): + + singleprob, multiprob, multitraj = True, False, False + if isinstance(solfile, list) and isinstance(simfile, list): + multiprob, singleprob = True, False + if len(solfile) != len(simfile): + raise Exception( + "Must provide same number of solution and simulation files with separate problems") + + elif isinstance(simfile, list) and isinstance(solfile, str): + multitraj, singleprob = True, False + solfile = [solfile]*len(simfile) + if solprefix == '': + raise Exception( + "When plotting multiple trajectories, must provide prefix to access solutions!") + + if singleprob: + solfile, simfile = [solfile], [simfile] + + plotvars = [('r', 'h'), + ('time', 'h'), + ('time', 'v'), + ('time', 'thrust'), + ('time', 'gam'), + ('time', 'alpha')] + plotunits = [ + ('km', 'km'), + ('s', 'km'), + ('s', 'm/s'), + ('s', 'kN'), + ('s', 'deg'), + ('s', 'deg')] + + numplots = len(plotvars) + tsprefix = 'traj.phase0.timeseries.' + + sols = [CaseReader(file).get_case('final') for file in solfile] + sims = [CaseReader(file).get_case('final') for file in simfile] + colors = ['r', 'b', 'g', 'm'] + legend = [] + areas = [] + heights = [None]*len(simfile) + + for i, (solf, simf) in enumerate(zip(sols, sims)): + for j, ((xvar, yvar), (xunit, yunit)) in enumerate(zip(plotvars, plotunits)): + plt.subplot(2, int(numplots/2), j+1) + xname, yname = addPrefix(tsprefix, (xvar, yvar)) + xsim = simf.get_val(xname, units=xunit) + ysim = simf.get_val(yname, units=yunit) + if omitpromote is not None: + xname = xname.replace(omitpromote+".", "") + yname = yname.replace(omitpromote+".", "") + if multitraj: + xname, yname = addPrefix(f"{solprefix}_{i}.", (xname, yname)) + xsol = solf.get_val(xname, units=xunit) + ysol = solf.get_val(yname, units=yunit) + if yvar == "h" and not heights[i]: + heights[i] = ysol[-1][0] + plt.plot(xsol, ysol, f"{colors[i]}o", fillstyle='none') + plt.plot(xsim, ysim, colors[i]) + plt.xlabel(f"{xvar} ({xunit})") + plt.ylabel(f"{yvar} ({yunit})") + plt.grid(visible=True) + legend.append(f"{heights[i]} {plotunits[0][1]} solution") + legend.append(f"{heights[i]} {plotunits[0][1]} simulation") + try: + areas.append(round(solf.get_val('S')[0], 2)) + except KeyError: + areas.append(round(solf.get_val('phase0.parameters:S')[0], 2)) + plt.figlegend(legend, ncols=len(simfile)) + plt.suptitle(f"Min Time to Climb, wing areas: {areas}") + plt.tight_layout(pad=1) + plt.show() + + +def addPrefix(prefix, iterable): + return [prefix+item for item in iterable] + + +if __name__ == '__main__': + make_min_time_climb_plot(solfile=['dymos_solution_0.db', 'dymos_solution_1.db'], + simfile=['dymos_simulation_0.db', 'dymos_simulation_1.db']) From 531c41f3b6684bb97b418cf1a6b1953a182a2d7d Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Fri, 2 Aug 2024 12:15:10 -0400 Subject: [PATCH 026/113] added comparison func to multi min time climb to compare with singular optimization --- min_time_climb_models/min_time_climb.py | 279 ++++++++++-------- .../multi_min_time_to_climb.py | 259 +++++++--------- min_time_climb_models/plot_helper.py | 32 +- multi_aviary_copymodel.py | 15 +- 4 files changed, 288 insertions(+), 297 deletions(-) diff --git a/min_time_climb_models/min_time_climb.py b/min_time_climb_models/min_time_climb.py index a49c956f9..b4b9dcd67 100644 --- a/min_time_climb_models/min_time_climb.py +++ b/min_time_climb_models/min_time_climb.py @@ -7,118 +7,136 @@ import sys -def min_time_climb( - height=20e3, driver='scipy', optimizer='SLSQP', num_seg=15, - transcription='gauss-lobatto', transcription_order=3, force_alloc_complex=False, - add_rate=False, time_name='time', simfile='dymos_simulatin.db', - solfile='dymos_solution.db'): - - p = om.Problem(model=om.Group()) - - p.driver = om.ScipyOptimizeDriver() if driver == 'scipy' else om.pyOptSparseDriver() - p.driver.options['optimizer'] = optimizer - p.driver.declare_coloring() - - if optimizer == 'SNOPT': - p.driver.opt_settings['Major iterations limit'] = 1000 - p.driver.opt_settings['iSumm'] = 6 - p.driver.opt_settings['Major feasibility tolerance'] = 1.0E-6 - p.driver.opt_settings['Major optimality tolerance'] = 1.0E-6 - p.driver.opt_settings['Function precision'] = 1.0E-12 - p.driver.opt_settings['Linesearch tolerance'] = 0.1 - p.driver.opt_settings['Major step limit'] = 0.5 - elif optimizer == 'IPOPT': - p.driver.opt_settings['tol'] = 1.0E-5 - p.driver.opt_settings['print_level'] = 0 - p.driver.opt_settings['mu_strategy'] = 'monotone' - p.driver.opt_settings['bound_mult_init_method'] = 'mu-based' - p.driver.opt_settings['mu_init'] = 0.01 - - t = {'gauss-lobatto': dm.GaussLobatto( - num_segments=num_seg, order=transcription_order), - 'radau-ps': dm.Radau(num_segments=num_seg, order=transcription_order)} - - traj = dm.Trajectory() - - phase = dm.Phase(ode_class=MinTimeClimbODE, transcription=t[transcription]) - traj.add_phase('phase0', phase) - - phase.set_time_options(fix_initial=True, duration_bounds=(50, 400), - duration_ref=100.0, name=time_name) - - phase.add_state('r', fix_initial=True, lower=0, upper=1.0E6, - ref=1.0E3, defect_ref=1.0E3, units='m', - rate_source='flight_dynamics.r_dot') - - phase.add_state('h', fix_initial=True, lower=0, upper=height, - ref=height, defect_ref=height, units='m', - rate_source='flight_dynamics.h_dot', targets=['h']) - - phase.add_state('v', fix_initial=True, lower=10.0, - ref=1.0E2, defect_ref=1.0E2, units='m/s', - rate_source='flight_dynamics.v_dot', targets=['v']) - - phase.add_state('gam', fix_initial=True, lower=-1.5, upper=1.5, - ref=1.0, defect_ref=1.0, units='rad', - rate_source='flight_dynamics.gam_dot', targets=['gam']) - - phase.add_state('m', fix_initial=True, lower=10.0, upper=1.0E5, - ref=10_000, defect_ref=10_000, units='kg', - rate_source='prop.m_dot', targets=['m']) - - phase.add_control('alpha', units='deg', lower=-8.0, upper=8.0, scaler=1.0, - rate_continuity=True, rate_continuity_scaler=100.0, - rate2_continuity=False, targets=['alpha']) - - phase.add_parameter('S', val=42.554663555518836, - units='m**2', opt=True, targets=['S']) - phase.add_parameter('Isp', val=1600.0, units='s', opt=False, targets=['Isp']) - phase.add_parameter('throttle', val=1.0, opt=False, targets=['throttle']) - - phase.add_boundary_constraint('h', loc='final', equals=height) # , scaler=1.0E-3) - phase.add_boundary_constraint('aero.mach', loc='final', equals=1.0) - phase.add_boundary_constraint('gam', loc='final', equals=0.0) - - phase.add_path_constraint(name='h', lower=100.0, upper=height, ref=height) - phase.add_path_constraint(name='aero.mach', lower=0.1, upper=1.8) - # phase.add_path_constraint(name='gam', lower=-23, upper=23, units='deg') - - # Unnecessary but included to test capability - phase.add_path_constraint(name='alpha', lower=-8, upper=8) - phase.add_path_constraint(name=f'{time_name}', lower=0, upper=400) - phase.add_path_constraint(name=f'{time_name}_phase', lower=0, upper=400) - - # Minimize time at the end of the phase - phase.add_objective(time_name, loc='final', ref=1.0) - - # test mixing wildcard ODE variable expansion and unit overrides - phase.add_timeseries_output(['aero.*', 'prop.thrust', 'prop.m_dot'], - units={'aero.f_lift': 'lbf', 'prop.thrust': 'lbf'}) - - # test adding rate as timeseries output - if add_rate: - phase.add_timeseries_rate_output('aero.mach') - - p.model.add_subsystem('traj', traj, promotes=['*']) - - p.model.linear_solver = om.DirectSolver() - - p.setup(check=True, force_alloc_complex=force_alloc_complex) - - p.set_val('phase0.t_initial', 0.0) - p.set_val('phase0.t_duration', 350.0) - - p.set_val('phase0.states:r', phase.interp('r', [0.0, 100e3])) - p.set_val('phase0.states:h', phase.interp('h', [100.0, height])) - p.set_val('phase0.states:v', phase.interp('v', [135.964, 283.159])) - p.set_val('phase0.states:gam', phase.interp('gam', [0.0, 0.0])) - p.set_val('phase0.states:m', phase.interp('m', [30e3, 16e3])) - p.set_val('phase0.controls:alpha', phase.interp('alpha', [0.0, 0.0])) - - dm.run_problem(p, simulate=True, simulation_record_file=simfile, - solution_record_file=solfile) - - return p +class MinTimeClimbProblem(om.Problem): + def __init__( + self, target_height=20e3, + modelinfo={'m_initial': 16e3, 'S': 49.24, 'v_initial': 150, 'h_initial': 10, + 'mach_final': 1.0}): + super().__init__() + defaults = {'m_initial': 16e3, 'S': 49.24, 'v_initial': 150, 'h_initial': 10, + 'mach_final': 1.0} + for key in defaults.keys(): + if key not in modelinfo.keys(): + modelinfo[key] = defaults[key] + + self.model = om.Group() + self.target_height = target_height + self.modelinfo = modelinfo + + def setOptimizer(self, driver='scipy', optimizer='SLSQP'): + self.driver = om.pyOptSparseDriver() if driver == "pyoptsparse" else om.ScipyOptimizeDriver() + self.driver.options['optimizer'] = optimizer + self.driver.declare_coloring() + if optimizer == 'SNOPT': + self.driver.opt_settings['Major iterations limit'] = 1000 + self.driver.opt_settings['iSumm'] = 6 + self.driver.opt_settings['Major feasibility tolerance'] = 1.0E-6 + self.driver.opt_settings['Major optimality tolerance'] = 1.0E-6 + self.driver.opt_settings['Function precision'] = 1.0E-12 + self.driver.opt_settings['Linesearch tolerance'] = 0.1 + self.driver.opt_settings['Major step limit'] = 0.5 + elif optimizer == 'IPOPT': + self.driver.opt_settings['tol'] = 1.0E-5 + self.driver.opt_settings['print_level'] = 0 + self.driver.opt_settings['mu_strategy'] = 'monotone' + self.driver.opt_settings['bound_mult_init_method'] = 'mu-based' + self.driver.opt_settings['mu_init'] = 0.01 + + self.model.linear_solver = om.DirectSolver() + + def addTrajectory(self, num_seg=15, transcription='gauss-lobatto', + transcription_order=3, optWing=False): + t = {'gauss-lobatto': dm.GaussLobatto( + num_segments=num_seg, order=transcription_order), + 'radau-ps': dm.Radau(num_segments=num_seg, order=transcription_order)} + + traj = dm.Trajectory() + phase = dm.Phase(ode_class=MinTimeClimbODE, transcription=t[transcription]) + traj.add_phase('phase0', phase) + + height = self.target_height + time_name = 'time' + add_rate = False + phase.set_time_options(fix_initial=True, duration_bounds=(50, 600), + duration_ref=100.0, name=time_name) + + phase.add_state('r', fix_initial=True, lower=0, upper=1.0E6, + ref=1.0E3, defect_ref=1.0E3, units='m', + rate_source='flight_dynamics.r_dot') + + phase.add_state('h', fix_initial=True, lower=0, upper=height, + ref=height, defect_ref=height, units='m', + rate_source='flight_dynamics.h_dot', targets=['h']) + + phase.add_state('v', fix_initial=True, lower=10.0, + ref=1.0E2, defect_ref=1.0E2, units='m/s', + rate_source='flight_dynamics.v_dot', targets=['v']) + + phase.add_state('gam', fix_initial=True, lower=-1.5, upper=1.5, + ref=1.0, defect_ref=1.0, units='rad', + rate_source='flight_dynamics.gam_dot', targets=['gam']) + + phase.add_state('m', fix_initial=True, lower=10.0, upper=1.0E5, + ref=10_000, defect_ref=10_000, units='kg', + rate_source='prop.m_dot', targets=['m']) + + phase.add_control('alpha', units='deg', lower=-8.0, upper=8.0, scaler=1.0, + rate_continuity=True, rate_continuity_scaler=100.0, + rate2_continuity=False, targets=['alpha']) + + phase.add_parameter('S', val=self.modelinfo['S'], units='m**2', + opt=optWing, targets=['S']) + phase.add_parameter('Isp', val=1600.0, units='s', opt=False, targets=['Isp']) + phase.add_parameter('throttle', val=1.0, opt=False, targets=['throttle']) + + phase.add_boundary_constraint( + 'h', loc='final', equals=height) # , scaler=1.0E-3) + phase.add_boundary_constraint( + 'aero.mach', loc='final', equals=self.modelinfo['mach_final']) + phase.add_boundary_constraint('gam', loc='final', equals=0.0) + + phase.add_path_constraint(name='h', lower=100.0, upper=height, ref=height) + phase.add_path_constraint(name='aero.mach', lower=0.1, upper=1.8) + # phase.add_path_constraint(name='gam', lower=-23, upper=23, units='deg') + + # Unnecessary but included to test capability + phase.add_path_constraint(name='alpha', lower=-8, upper=8) + phase.add_path_constraint(name=f'{time_name}', lower=0, upper=600) + phase.add_path_constraint(name=f'{time_name}_phase', lower=0, upper=600) + + # test mixing wildcard ODE variable expansion and unit overrides + phase.add_timeseries_output(['aero.*', 'prop.thrust', 'prop.m_dot'], + units={'aero.f_lift': 'lbf', 'prop.thrust': 'lbf'}) + + # test adding rate as timeseries output + if add_rate: + phase.add_timeseries_rate_output('aero.mach') + + self.phase = phase + self.model.add_subsystem('traj', traj, promotes=['*']) + + def setInitialConditions(self, super_prob=None, prefix=""): + ref = self + if super_prob is not None and prefix != "": + ref = super_prob + phase = self.phase + ref.set_val(prefix+'traj.phase0.t_initial', 0.0) + ref.set_val(prefix+'traj.phase0.t_duration', 350.0) + + ref.set_val(prefix+'traj.phase0.states:r', phase.interp('r', [0.0, 100e3])) + ref.set_val(prefix+'traj.phase0.states:h', phase.interp( + 'h', [self.modelinfo['h_initial'], self.target_height])) + ref.set_val(prefix+'traj.phase0.states:v', + phase.interp('v', [self.modelinfo['v_initial'], 280])) + ref.set_val(prefix+'traj.phase0.states:gam', phase.interp('gam', [0.0, 0.0])) + ref.set_val(prefix+'traj.phase0.states:m', + phase.interp('m', [self.modelinfo['m_initial'], 16e3])) + ref.set_val(prefix+'traj.phase0.controls:alpha', + phase.interp('alpha', [0.0, 0.0])) + + def addObjective(self): + # Minimize time at the end of the phase + self.phase.add_objective('time', loc='final', ref=1.0) def checkDeviation(filenum=0): @@ -130,7 +148,13 @@ def checkDeviation(filenum=0): prefix = 'traj.phase0.timeseries.' for height in heights: - p = min_time_climb(height=height) + p = MinTimeClimbProblem(target_height=height) + p.addTrajectory() + p.addObjective() + p.setOptimizer(driver='pyoptsparse') + p.setup() + p.setInitialConditions() + dm.run_problem(p, simulate=True) sol = om.CaseReader('dymos_solution.db').get_case('final') sim = om.CaseReader('dymos_simulation.db').get_case('final') times_to_climb.append(p.get_val('traj.phase0.timeseries.time', @@ -156,7 +180,7 @@ def checkDeviation(filenum=0): f" {np.std(timeseries_pts[key]):.2f}") -def multiHeightTest(): +def multiHeightTest(printResults=True): heights = [6e3, 18e3] times = [] areas = [] @@ -167,23 +191,32 @@ def multiHeightTest(): simfile = f'single_simulation_{j}.db' outfiles['sim'].append(simfile) outfiles['sol'].append(solfile) - p = min_time_climb( - height=height, simfile=simfile, - solfile=solfile) + p = MinTimeClimbProblem(target_height=height) + p.addTrajectory(optWing=True) + p.addObjective() + p.setOptimizer(driver='pyoptsparse') + p.setup() + p.setInitialConditions() + dm.run_problem( + p, simulate=True, solution_record_file=solfile, + simulation_record_file=simfile) areas.append(p.get_val('phase0.parameters:S', units='m**2')[0]) times.append(p.get_val('phase0.timeseries.time', units='s')[-1][0]) - print("\n\n=======================================") - # print(p.get_val('phase.flight_dynamics.gam_dot')) - for time, area, height in zip(times, areas, heights): - print(f"Time to climb {height/1e3} km: " + - f"{time:.2f}" + - f" s with wing area: {area} sqm") + if printResults: + print("\n\n=======================================") + for time, area, height in zip(times, areas, heights): + print(f"Time to climb {height/1e3} km: " + + f"{time:.2f}" + + f" s with wing area: {area} sqm") + make_min_time_climb_plot( solfile=outfiles['sol'], simfile=outfiles['sim'], omitpromote='traj') + return outfiles + if __name__ == '__main__': if 'filenum' in sys.argv: diff --git a/min_time_climb_models/multi_min_time_to_climb.py b/min_time_climb_models/multi_min_time_to_climb.py index b378526ef..7fecae749 100644 --- a/min_time_climb_models/multi_min_time_to_climb.py +++ b/min_time_climb_models/multi_min_time_to_climb.py @@ -1,181 +1,80 @@ import openmdao.api as om import dymos as dm -from dymos.examples.min_time_climb.min_time_climb_ode import MinTimeClimbODE from plot_helper import make_min_time_climb_plot +from min_time_climb import MinTimeClimbProblem import matplotlib.pyplot as plt -import numpy as np import sys -class MinTimeClimbProblem(om.Problem): - def __init__(self, target_height=20e3, initial_mass=20e3): +class MultiMinTime(om.Problem): + def __init__( + self, heights, weights, optWing=False, modelinfo={}): super().__init__() - self.model = om.Group() - self.target_height = target_height - self.initial_mass = initial_mass - - def setOptimizer(self, driver='scipy', optimizer='SLSQP'): - self.driver = om.pyOptSparseDriver() if driver == "pyoptsparse" else om.ScipyOptimizeDriver() - self.driver.options['optimizer'] = optimizer + if len(weights) > len(heights): + raise Exception("Can't have more weights than heights!") + elif len(weights) < len(heights): + weights = [1]*len(heights) + + self.weights = weights + self.num_missions = len(heights) + self.probs = [] + + for i, height in enumerate(heights): + prob = MinTimeClimbProblem( + target_height=height, modelinfo=modelinfo) + prob.addTrajectory(optWing=optWing) + self.model.add_subsystem( + f"group_{i}", prob.model, promotes=[('phase0.parameters:S', 'S')]) + self.probs.append(prob) + if optWing: + self.model.add_design_var('S', lower=1, upper=100, units='m**2') + + def addCompoundObj(self): + num_missions = self.num_missions + weights = self.weights + times = [f"time_{i}" for i in range(num_missions)] + weighted_sum_str = "+".join([f"{time}*{weight}" for time, + weight in zip(times, weights)]) + self.model.add_subsystem('compoundComp', om.ExecComp( + "compound_time=" + weighted_sum_str), + promotes=['compound_time', *times]) + + for i in range(num_missions): + self.model.connect( + f"group_{i}.phase0.t", times[i], + src_indices=-1) + self.model.add_objective('compound_time') + + def addDriver(self, driver='pyoptsparse', optimizer='SLSQP'): + self.driver = om.pyOptSparseDriver() \ + if driver == 'pyoptsparse' else \ + om.ScipyOptimizeDriver() + self.driver.options['optimizer'] = optimizer # 'IPOPT' self.driver.declare_coloring() - if optimizer == 'SNOPT': - self.driver.opt_settings['Major iterations limit'] = 1000 - self.driver.opt_settings['iSumm'] = 6 - self.driver.opt_settings['Major feasibility tolerance'] = 1.0E-6 - self.driver.opt_settings['Major optimality tolerance'] = 1.0E-6 - self.driver.opt_settings['Function precision'] = 1.0E-12 - self.driver.opt_settings['Linesearch tolerance'] = 0.1 - self.driver.opt_settings['Major step limit'] = 0.5 - elif optimizer == 'IPOPT': - self.driver.opt_settings['tol'] = 1.0E-5 - self.driver.opt_settings['print_level'] = 0 - self.driver.opt_settings['mu_strategy'] = 'monotone' - self.driver.opt_settings['bound_mult_init_method'] = 'mu-based' - self.driver.opt_settings['mu_init'] = 0.01 - self.model.linear_solver = om.DirectSolver() - def addTrajectory(self, num_seg=15, transcription='gauss-lobatto', - transcription_order=3): - t = {'gauss-lobatto': dm.GaussLobatto( - num_segments=num_seg, order=transcription_order), - 'radau-ps': dm.Radau(num_segments=num_seg, order=transcription_order)} - - traj = dm.Trajectory() - phase = dm.Phase(ode_class=MinTimeClimbODE, transcription=t[transcription]) - traj.add_phase('phase0', phase) - - height = self.target_height - time_name = 'time' - add_rate = False - phase.set_time_options(fix_initial=True, duration_bounds=(50, 600), - duration_ref=100.0, name=time_name) - - phase.add_state('r', fix_initial=True, lower=0, upper=1.0E6, - ref=1.0E3, defect_ref=1.0E3, units='m', - rate_source='flight_dynamics.r_dot') - - phase.add_state('h', fix_initial=True, lower=0, upper=height, - ref=height, defect_ref=height, units='m', - rate_source='flight_dynamics.h_dot', targets=['h']) - - phase.add_state('v', fix_initial=True, lower=10.0, - ref=1.0E2, defect_ref=1.0E2, units='m/s', - rate_source='flight_dynamics.v_dot', targets=['v']) - - phase.add_state('gam', fix_initial=True, lower=-1.5, upper=1.5, - ref=1.0, defect_ref=1.0, units='rad', - rate_source='flight_dynamics.gam_dot', targets=['gam']) - - phase.add_state('m', fix_initial=True, lower=10.0, upper=1.0E5, - ref=10_000, defect_ref=10_000, units='kg', - rate_source='prop.m_dot', targets=['m']) - - phase.add_control('alpha', units='deg', lower=-8.0, upper=8.0, scaler=1.0, - rate_continuity=True, rate_continuity_scaler=100.0, - rate2_continuity=False, targets=['alpha']) - - phase.add_parameter('S', val=49.2386, units='m**2', opt=True, targets=['S']) - phase.add_parameter('Isp', val=1600.0, units='s', opt=False, targets=['Isp']) - phase.add_parameter('throttle', val=1.0, opt=False, targets=['throttle']) - - phase.add_boundary_constraint( - 'h', loc='final', equals=height) # , scaler=1.0E-3) - phase.add_boundary_constraint('aero.mach', loc='final', equals=1.0) - phase.add_boundary_constraint('gam', loc='final', equals=0.0) - - phase.add_path_constraint(name='h', lower=100.0, upper=height, ref=height) - phase.add_path_constraint(name='aero.mach', lower=0.1, upper=1.8) - # phase.add_path_constraint(name='gam', lower=-23, upper=23, units='deg') - - # Unnecessary but included to test capability - phase.add_path_constraint(name='alpha', lower=-8, upper=8) - phase.add_path_constraint(name=f'{time_name}', lower=0, upper=400) - phase.add_path_constraint(name=f'{time_name}_phase', lower=0, upper=400) - - # Minimize time at the end of the phase - # phase.add_objective(time_name, loc='final', ref=1.0) - - # test mixing wildcard ODE variable expansion and unit overrides - phase.add_timeseries_output(['aero.*', 'prop.thrust', 'prop.m_dot'], - units={'aero.f_lift': 'lbf', 'prop.thrust': 'lbf'}) - - # test adding rate as timeseries output - if add_rate: - phase.add_timeseries_rate_output('aero.mach') - - self.phase = phase - self.model.add_subsystem('traj', traj, promotes=['*']) - - def setInitialConditions(self, super_prob=None, prefix=""): - ref = self - if super_prob is not None and prefix != "": - ref = super_prob - phase = self.phase - ref.set_val(prefix+'traj.phase0.t_initial', 0.0) - ref.set_val(prefix+'traj.phase0.t_duration', 350.0) - - ref.set_val(prefix+'traj.phase0.states:r', phase.interp('r', [0.0, 100e3])) - ref.set_val(prefix+'traj.phase0.states:h', phase.interp( - 'h', [100.0, self.target_height])) - ref.set_val(prefix+'traj.phase0.states:v', phase.interp('v', [135.964, 283.159])) - ref.set_val(prefix+'traj.phase0.states:gam', phase.interp('gam', [0.0, 0.0])) - ref.set_val(prefix+'traj.phase0.states:m', - phase.interp('m', [self.initial_mass, 16e3])) - ref.set_val(prefix+'traj.phase0.controls:alpha', - phase.interp('alpha', [0.0, 0.0])) + def setICs(self): + for i, prob in enumerate(self.probs): + prob.setInitialConditions(self, f"group_{i}.") -if __name__ == '__main__': +def multiExample(): makeN2 = True if "n2" in sys.argv else False - heights = [6e3, 18e3] - weights = [1, 1] - num_missions = len(heights) - - super_prob = om.Problem() - probs = [] - for i, height in enumerate(heights): - prob = MinTimeClimbProblem(height, 30e3) - prob.addTrajectory() - super_prob.model.add_subsystem( - f"group_{i}", prob.model, promotes=[('phase0.parameters:S', 'S')]) - probs.append(prob) - - super_prob.model.add_design_var('S', lower=1, upper=100, units='m**2') - - times = [f"time_{i}" for i in range(num_missions)] - weighted_sum_str = "+".join([f"{time}*{weight}" for time, - weight in zip(times, weights)]) - super_prob.model.add_subsystem('compoundComp', om.ExecComp( - "compound_time=" + weighted_sum_str), - promotes=['compound_time', *times]) - - for i in range(num_missions): - super_prob.model.connect( - f"group_{i}.phase0.t", times[i], - src_indices=-1) - super_prob.model.add_objective('compound_time') - - # super_prob.driver = om.ScipyOptimizeDriver() - super_prob.driver = om.pyOptSparseDriver() - super_prob.driver.options['optimizer'] = 'SLSQP' # 'IPOPT' - super_prob.driver.declare_coloring() - super_prob.model.linear_solver = om.DirectSolver() - + super_prob = MultiMinTime(heights=[6e3, 18e3], weights=[1, 1], + optWing=True, modelinfo={'m_initial': 20e3}) + super_prob.addCompoundObj() + super_prob.addDriver() super_prob.setup() + super_prob.setICs() if makeN2: sys.path.append('../') from createN2 import createN2 createN2(__file__, super_prob) - - for i, prob in enumerate(probs): - prob.setInitialConditions(super_prob, f"group_{i}.") - dm.run_problem(super_prob, simulate=True) wing_area = super_prob.get_val('S', units='m**2')[0] print("\n\n=====================================") - for i in range(num_missions): + for i in range(super_prob.num_missions): timetoclimb = super_prob.get_val(f'group_{i}.phase0.t', units='s')[-1] print(f"TtoC: {timetoclimb}, S: {wing_area}") @@ -183,3 +82,53 @@ def setInitialConditions(self, super_prob=None, prefix=""): solfile='dymos_solution.db', simfile=['dymos_simulation.db', 'dymos_simulation_1.db'], solprefix='group', omitpromote='traj') + + +def comparison(): + heights = [10e3, 15e3] + weights = [1, 1] + optimize_wing = True + m_0 = 23e3 + modelinfo = {'m_initial': m_0, 'S': 49.24, 'v_initial': 104, 'h_initial': 100, + 'mach_final': 1.0} + + solfiles, simfiles = [], [] + for i, height in enumerate(heights): + p = MinTimeClimbProblem(target_height=height, modelinfo=modelinfo) + p.addTrajectory(optWing=optimize_wing) + p.addObjective() + p.setOptimizer(driver='pyoptsparse') + p.setup() + p.setInitialConditions() + solfile, simfile = f'Sol_Comp_{i}.db', f'Sim_Comp_{i}.db' + solfiles.append(solfile) + simfiles.append(simfile) + dm.run_problem( + p, simulate=True, solution_record_file=solfile, + simulation_record_file=simfile) + + super_prob = MultiMinTime(heights=heights, weights=weights, + optWing=optimize_wing, modelinfo=modelinfo) + super_prob.addCompoundObj() + super_prob.addDriver() + super_prob.setup() + super_prob.setICs() + dm.run_problem(super_prob, simulate=True) + + fig1, fig2 = plt.figure(1), plt.figure(2) + make_min_time_climb_plot( + solfile=solfiles, simfile=simfiles, omitpromote='traj', show=False, fig=fig1, + extratitle=f"{m_0} kg") + make_min_time_climb_plot( + solfile='dymos_solution.db', + simfile=['dymos_simulation.db', 'dymos_simulation_1.db'], + solprefix='group', omitpromote='traj', show=False, fig=fig2, + extratitle=f"{m_0} kg") + plt.show() + + +if __name__ == '__main__': + if "comparison" in sys.argv: + comparison() + else: + multiExample() diff --git a/min_time_climb_models/plot_helper.py b/min_time_climb_models/plot_helper.py index cb3d3db68..695991d0f 100644 --- a/min_time_climb_models/plot_helper.py +++ b/min_time_climb_models/plot_helper.py @@ -4,7 +4,7 @@ def make_min_time_climb_plot( solfile='dymos_solution.db', simfile='dymos_simulation.db', solprefix='', - omitpromote=None): + omitpromote=None, show=True, fig=None, extratitle=''): singleprob, multiprob, multitraj = True, False, False if isinstance(solfile, list) and isinstance(simfile, list): @@ -38,6 +38,7 @@ def make_min_time_climb_plot( ('s', 'deg')] numplots = len(plotvars) + axes = [None]*numplots tsprefix = 'traj.phase0.timeseries.' sols = [CaseReader(file).get_case('final') for file in solfile] @@ -47,9 +48,17 @@ def make_min_time_climb_plot( areas = [] heights = [None]*len(simfile) + if fig is None: + fig = plt.figure() for i, (solf, simf) in enumerate(zip(sols, sims)): for j, ((xvar, yvar), (xunit, yunit)) in enumerate(zip(plotvars, plotunits)): - plt.subplot(2, int(numplots/2), j+1) + if axes[j] is None: + ax = fig.add_subplot(2, int(numplots/2), j+1, + xlabel=f"{xvar} ({xunit})", + ylabel=f"{yvar} ({yunit})") + axes[j] = ax + else: + ax = axes[j] xname, yname = addPrefix(tsprefix, (xvar, yvar)) xsim = simf.get_val(xname, units=xunit) ysim = simf.get_val(yname, units=yunit) @@ -61,22 +70,21 @@ def make_min_time_climb_plot( xsol = solf.get_val(xname, units=xunit) ysol = solf.get_val(yname, units=yunit) if yvar == "h" and not heights[i]: - heights[i] = ysol[-1][0] - plt.plot(xsol, ysol, f"{colors[i]}o", fillstyle='none') - plt.plot(xsim, ysim, colors[i]) - plt.xlabel(f"{xvar} ({xunit})") - plt.ylabel(f"{yvar} ({yunit})") - plt.grid(visible=True) + heights[i] = round(ysol[-1][0]) + ax.plot(xsol, ysol, f"{colors[i]}o", fillstyle='none') + ax.plot(xsim, ysim, colors[i]) + ax.grid(visible=True) legend.append(f"{heights[i]} {plotunits[0][1]} solution") legend.append(f"{heights[i]} {plotunits[0][1]} simulation") try: areas.append(round(solf.get_val('S')[0], 2)) except KeyError: areas.append(round(solf.get_val('phase0.parameters:S')[0], 2)) - plt.figlegend(legend, ncols=len(simfile)) - plt.suptitle(f"Min Time to Climb, wing areas: {areas}") - plt.tight_layout(pad=1) - plt.show() + fig.legend(legend, ncols=len(simfile), loc='lower center') + fig.suptitle(f"Min Time to Climb, wing areas: {areas}, {extratitle}") + fig.tight_layout(pad=1) + if show: + plt.show() def addPrefix(prefix, iterable): diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index e0a0cb23f..c7bc8daf3 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -67,10 +67,10 @@ def add_design_variables(self): self.model.add_design_var('mission:design:gross_mass', lower=10., upper=900e3) def add_driver(self): - self.driver = om.ScipyOptimizeDriver() - self.driver.options['optimizer'] = 'SLSQP' - # self.driver.declare_coloring() - self.model.linear_solver = om.DirectSolver() + self.driver = om.pyOptSparseDriver() + self.driver.options['optimizer'] = 'IPOPT' + self.driver.declare_coloring() + # self.model.linear_solver = om.DirectSolver() def add_objective(self): weights = self.weights @@ -105,9 +105,10 @@ def setup_wrapper(self): self.setup(check='all') def run(self): - self.run_model() - self.check_totals(method='fd') - # dm.run_problem(self) + # self.run_model() + # self.check_totals(method='fd', compact_print=True) + self.model.set_solver_print(0) + dm.run_problem(self, make_plots=True) if __name__ == '__main__': From cff9d90f588a4a92e4f184cab5e88f8addc25fbe Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Fri, 2 Aug 2024 14:58:19 -0400 Subject: [PATCH 027/113] added weight comparison to min time to climb example --- .../multi_min_time_to_climb.py | 41 ++++++++++++++++++- min_time_climb_models/plot_helper.py | 12 +++--- multi_aviary_copymodel.py | 6 +-- 3 files changed, 50 insertions(+), 9 deletions(-) diff --git a/min_time_climb_models/multi_min_time_to_climb.py b/min_time_climb_models/multi_min_time_to_climb.py index 7fecae749..bb6431f67 100644 --- a/min_time_climb_models/multi_min_time_to_climb.py +++ b/min_time_climb_models/multi_min_time_to_climb.py @@ -31,7 +31,7 @@ def __init__( def addCompoundObj(self): num_missions = self.num_missions - weights = self.weights + weights = [float(weight/sum(self.weights)) for weight in self.weights] times = [f"time_{i}" for i in range(num_missions)] weighted_sum_str = "+".join([f"{time}*{weight}" for time, weight in zip(times, weights)]) @@ -59,6 +59,7 @@ def setICs(self): def multiExample(): + """Example of multi mission min time to climb problem.""" makeN2 = True if "n2" in sys.argv else False super_prob = MultiMinTime(heights=[6e3, 18e3], weights=[1, 1], optWing=True, modelinfo={'m_initial': 20e3}) @@ -84,7 +85,43 @@ def multiExample(): solprefix='group', omitpromote='traj') +def weightCompare(): + """Runs the multi mission min time to climb problem for different weights. Shows + impact of changing weights on 1 figure.""" + heights = [10e3, 15e3] + weights_to_test = [[1, 3], [3, 1]] + modelinfo = {'m_initial': 18e3, 'S': 49.24, 'v_initial': 104, 'h_initial': 100, + 'mach_final': 1.0} + solfiles, simfiles = [], [] + for i, weights in enumerate(weights_to_test): + super_prob = MultiMinTime(heights=heights, weights=weights, + optWing=True, modelinfo=modelinfo) + super_prob.addCompoundObj() + super_prob.addDriver(driver='scipy') + super_prob.setup() + super_prob.setICs() + solfiles.append(f'weightsSol_{i}.db') + simfiles.append(f'weightsSim_{i}.db') + dm.run_problem(super_prob, simulate=True, + solution_record_file=solfiles[-1], + simulation_record_file=simfiles[-1]) + + fig = plt.figure() + colores = [['r', 'b'], ['g', 'm']] + for i, (solfile, simfile, colors) in enumerate(zip(solfiles, simfiles, colores)): + make_min_time_climb_plot( + solfile=solfile, + simfile=[simfile, simfile.replace(".db", "_1.db")], + solprefix='group', omitpromote='traj', show=False, fig=fig, + extratitle=", ".join([str(w) for w in weights_to_test[i]]), + colors=colors) + + plt.show() + + def comparison(): + """Runs min time to climb problem for 2 heights individually, as well as with the + multi mission approach. Creates 2 figures showing the differences between the 2.""" heights = [10e3, 15e3] weights = [1, 1] optimize_wing = True @@ -130,5 +167,7 @@ def comparison(): if __name__ == '__main__': if "comparison" in sys.argv: comparison() + elif "weights" in sys.argv: + weightCompare() else: multiExample() diff --git a/min_time_climb_models/plot_helper.py b/min_time_climb_models/plot_helper.py index 695991d0f..e8acc460e 100644 --- a/min_time_climb_models/plot_helper.py +++ b/min_time_climb_models/plot_helper.py @@ -4,7 +4,7 @@ def make_min_time_climb_plot( solfile='dymos_solution.db', simfile='dymos_simulation.db', solprefix='', - omitpromote=None, show=True, fig=None, extratitle=''): + omitpromote=None, show=True, fig=None, extratitle='', colors=['r', 'b', 'g', 'm']): singleprob, multiprob, multitraj = True, False, False if isinstance(solfile, list) and isinstance(simfile, list): @@ -23,6 +23,8 @@ def make_min_time_climb_plot( if singleprob: solfile, simfile = [solfile], [simfile] + if fig is None: + fig = plt.figure() plotvars = [('r', 'h'), ('time', 'h'), ('time', 'v'), @@ -38,18 +40,18 @@ def make_min_time_climb_plot( ('s', 'deg')] numplots = len(plotvars) - axes = [None]*numplots + axes = fig.axes + if len(axes) == 0: + axes = [None]*len(plotvars) tsprefix = 'traj.phase0.timeseries.' sols = [CaseReader(file).get_case('final') for file in solfile] sims = [CaseReader(file).get_case('final') for file in simfile] - colors = ['r', 'b', 'g', 'm'] + legend = [] areas = [] heights = [None]*len(simfile) - if fig is None: - fig = plt.figure() for i, (solf, simf) in enumerate(zip(sols, sims)): for j, ((xvar, yvar), (xunit, yunit)) in enumerate(zip(plotvars, plotunits)): if axes[j] is None: diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index c7bc8daf3..b9f58b812 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -68,12 +68,12 @@ def add_design_variables(self): def add_driver(self): self.driver = om.pyOptSparseDriver() - self.driver.options['optimizer'] = 'IPOPT' + self.driver.options['optimizer'] = 'SLSQP' self.driver.declare_coloring() # self.model.linear_solver = om.DirectSolver() def add_objective(self): - weights = self.weights + weights = [float(weight/sum(self.weights)) for weight in self.weights] fuel_burned_vars = [f"fuel_{i}" for i in range(self.num_missions)] weighted_str = "+".join([f"{fuel}*{weight}" for fuel, weight in zip(fuel_burned_vars, weights)]) @@ -87,7 +87,7 @@ def add_objective(self): # connecting each subcomponent's fuel burn to super problem's unique fuel variables self.model.connect( self.group_prefix+f"_{i}.mission:summary:fuel_burned", f"fuel_{i}") - self.model.add_objective('compound') + self.model.add_objective('compound', scaler=1.) def setup_wrapper(self): """Wrapper for om.Problem setup with warning ignoring and setting options""" From 6cb7800848e4db1817e58fb4c2f2af2d0239f544 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Mon, 5 Aug 2024 15:26:33 -0400 Subject: [PATCH 028/113] easier phase infos --- easy_phase_info_inter.py | 83 +++++++++++++++++++ easy_phase_info_max.py | 83 +++++++++++++++++++ .../multi_min_time_to_climb.py | 4 +- multi_aviary_copymodel.py | 31 ++++--- 4 files changed, 187 insertions(+), 14 deletions(-) create mode 100644 easy_phase_info_inter.py create mode 100644 easy_phase_info_max.py diff --git a/easy_phase_info_inter.py b/easy_phase_info_inter.py new file mode 100644 index 000000000..6589101a8 --- /dev/null +++ b/easy_phase_info_inter.py @@ -0,0 +1,83 @@ +phase_info = { + "pre_mission": {"include_takeoff": False, "optimize_mass": True}, + "climb_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.3, "unitless"), + "final_mach": (0.7, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.72), "unitless"), + "initial_altitude": (0.0, "ft"), + "final_altitude": (24500.0, "ft"), + "altitude_bounds": ((0.0, 25000.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": True, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((0.0, 0.0), "min"), + "duration_bounds": ((35.0, 105.0), "min"), + }, + "initial_guesses": {"time": ([0.0, 70.0], "min")}, + }, + "climb_2": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.7, "unitless"), + "final_mach": (0.7, "unitless"), + "mach_bounds": ((0.6799999999999999, 0.72), "unitless"), + "initial_altitude": (24500.0, "ft"), + "final_altitude": (25000.0, "ft"), + "altitude_bounds": ((24000.0, 25500.0), "ft"), + "throttle_enforcement": "boundary_constraint", + "fix_initial": False, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((35.0, 105.0), "min"), + "duration_bounds": ((245.0, 735.0), "min"), + }, + "initial_guesses": {"time": ([70.0, 490.0], "min")}, + }, + "descent_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.7, "unitless"), + "final_mach": (0.3, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.72), "unitless"), + "initial_altitude": (25000.0, "ft"), + "final_altitude": (0.0, "ft"), + "altitude_bounds": ((0.0, 25500.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": False, + "constrain_final": True, + "fix_duration": False, + "initial_bounds": ((280.0, 840.0), "min"), + "duration_bounds": ((15.0, 45.0), "min"), + }, + "initial_guesses": {"time": ([560.0, 30.0], "min")}, + }, + "post_mission": { + "include_landing": False, + "constrain_range": True, + "target_range": (4367.14, "nmi"), + }, +} diff --git a/easy_phase_info_max.py b/easy_phase_info_max.py new file mode 100644 index 000000000..1f7df7f8e --- /dev/null +++ b/easy_phase_info_max.py @@ -0,0 +1,83 @@ +phase_info = { + "pre_mission": {"include_takeoff": False, "optimize_mass": True}, + "climb_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.3, "unitless"), + "final_mach": (0.7, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.72), "unitless"), + "initial_altitude": (0.0, "ft"), + "final_altitude": (24500.0, "ft"), + "altitude_bounds": ((0.0, 25000.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": True, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((0.0, 0.0), "min"), + "duration_bounds": ((35.0, 105.0), "min"), + }, + "initial_guesses": {"time": ([0.0, 70.0], "min")}, + }, + "climb_2": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.7, "unitless"), + "final_mach": (0.7, "unitless"), + "mach_bounds": ((0.6799999999999999, 0.72), "unitless"), + "initial_altitude": (24500.0, "ft"), + "final_altitude": (25000.0, "ft"), + "altitude_bounds": ((24000.0, 25500.0), "ft"), + "throttle_enforcement": "boundary_constraint", + "fix_initial": False, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((35.0, 105.0), "min"), + "duration_bounds": ((95.0, 285.0), "min"), + }, + "initial_guesses": {"time": ([70.0, 190.0], "min")}, + }, + "descent_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.7, "unitless"), + "final_mach": (0.3, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.72), "unitless"), + "initial_altitude": (25000.0, "ft"), + "final_altitude": (0.0, "ft"), + "altitude_bounds": ((0.0, 25500.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": False, + "constrain_final": True, + "fix_duration": False, + "initial_bounds": ((130.0, 390.0), "min"), + "duration_bounds": ((10.0, 30.0), "min"), + }, + "initial_guesses": {"time": ([260.0, 20.0], "min")}, + }, + "post_mission": { + "include_landing": False, + "constrain_range": True, + "target_range": (1977.99, "nmi"), + }, +} diff --git a/min_time_climb_models/multi_min_time_to_climb.py b/min_time_climb_models/multi_min_time_to_climb.py index bb6431f67..99b467850 100644 --- a/min_time_climb_models/multi_min_time_to_climb.py +++ b/min_time_climb_models/multi_min_time_to_climb.py @@ -61,8 +61,8 @@ def setICs(self): def multiExample(): """Example of multi mission min time to climb problem.""" makeN2 = True if "n2" in sys.argv else False - super_prob = MultiMinTime(heights=[6e3, 18e3], weights=[1, 1], - optWing=True, modelinfo={'m_initial': 20e3}) + super_prob = MultiMinTime(heights=[10e3, 15e3], weights=[1, 1], + optWing=True, modelinfo={'m_initial': 23e3}) super_prob.addCompoundObj() super_prob.addDriver() super_prob.setup() diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index b9f58b812..4ba8cd5c3 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -11,18 +11,11 @@ import openmdao.api as om import dymos as dm import numpy as np -from aviary.variable_info.enums import ProblemType, AnalysisScheme from c5_models.c5_ferry_phase_info import phase_info as c5_ferry_phase_info from c5_models.c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info from c5_models.c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info -from aviary.variable_info.variable_meta_data import _MetaData as MetaData -from aviary.variable_info.variables import Mission, Dynamic -from aviary.interface.methods_for_level2 import wrapped_convert_units -from aviary.variable_info.enums import EquationsOfMotion - -TWO_DEGREES_OF_FREEDOM = EquationsOfMotion.TWO_DEGREES_OF_FREEDOM -HEIGHT_ENERGY = EquationsOfMotion.HEIGHT_ENERGY -SOLVED_2DOF = EquationsOfMotion.SOLVED_2DOF +from easy_phase_info_inter import phase_info as easy_inter +from easy_phase_info_max import phase_info as easy_max # "comp?.a can be used to reference multiple comp1.a comp2.a etc" @@ -67,10 +60,23 @@ def add_design_variables(self): self.model.add_design_var('mission:design:gross_mass', lower=10., upper=900e3) def add_driver(self): + # pyoptsparse SLSQP errors out w pos directional derivative line search (obj scaler = 1) and + # inequality constraints incompatible (obj scaler = -1) - fuel burn obj + # pyoptsparse IPOPT keeps iterating (seen upto 1000+ iters) in the IPOPT.out file but no result + # scipy SLSQP reaches iter limit and fails optimization self.driver = om.pyOptSparseDriver() self.driver.options['optimizer'] = 'SLSQP' - self.driver.declare_coloring() + # self.driver.options['maxiter'] = 1e3 + # self.driver.declare_coloring() # self.model.linear_solver = om.DirectSolver() + """scipy SLSQP results + Iteration limit reached (Exit mode 9) + Current function value: -43.71865402878029 + Iterations: 200 + Function evaluations: 1018 + Gradient evaluations: 200 + Optimization FAILED. + Iteration limit reached""" def add_objective(self): weights = [float(weight/sum(self.weights)) for weight in self.weights] @@ -87,7 +93,7 @@ def add_objective(self): # connecting each subcomponent's fuel burn to super problem's unique fuel variables self.model.connect( self.group_prefix+f"_{i}.mission:summary:fuel_burned", f"fuel_{i}") - self.model.add_objective('compound', scaler=1.) + self.model.add_objective('compound', scaler=-1.) def setup_wrapper(self): """Wrapper for om.Problem setup with warning ignoring and setting options""" @@ -114,7 +120,8 @@ def run(self): if __name__ == '__main__': makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False planes = ['c5_models/c5_maxpayload.csv', 'c5_models/c5_intermediate.csv'] - phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] + # phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] + phase_infos = [easy_max, easy_inter] weights = [1, 1] super_prob = MultiMissionProblem(planes, phase_infos, weights) super_prob.add_driver() From 63a69c9c6f34de452f1f08b264d703138b7cbbf9 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Tue, 6 Aug 2024 09:04:10 -0400 Subject: [PATCH 029/113] added simple single aviary runfile --- multi_aviary_copymodel.py | 202 +++++++++++++++++++++++++++++++++++++- test_single_aviary.py | 22 +++++ 2 files changed, 222 insertions(+), 2 deletions(-) create mode 100644 test_single_aviary.py diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index 4ba8cd5c3..ead41f68e 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -93,7 +93,7 @@ def add_objective(self): # connecting each subcomponent's fuel burn to super problem's unique fuel variables self.model.connect( self.group_prefix+f"_{i}.mission:summary:fuel_burned", f"fuel_{i}") - self.model.add_objective('compound', scaler=-1.) + self.model.add_objective('compound', scaler=1.) def setup_wrapper(self): """Wrapper for om.Problem setup with warning ignoring and setting options""" @@ -114,7 +114,9 @@ def run(self): # self.run_model() # self.check_totals(method='fd', compact_print=True) self.model.set_solver_print(0) - dm.run_problem(self, make_plots=True) + + self.run_driver() + # dm.run_problem(self, make_plots=True) if __name__ == '__main__': @@ -137,6 +139,7 @@ def run(self): f"_{i}.aircraft:design:landing_to_takeoff_mass_ratio")) print(super_prob.get_val(super_prob.group_prefix + f"_{i}.mission:summary:range")) + # super_prob.final_setup() if makeN2: from createN2 import createN2 createN2(__file__, super_prob) @@ -455,3 +458,198 @@ def run(self): Cruise at M0.77 at 33k ft Max rate of climb: 2100 ft/min """ + + +""" +input disconnected error: +WARNING: The following inputs are not connected: + group_0.aircraft:air_conditioning:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.AC.aircraft:air_conditioning:mass_scaler) + group_0.aircraft:anti_icing:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.anti_icing.aircraft:anti_icing:mass_scaler) + group_0.aircraft:apu:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.apu.aircraft:apu:mass_scaler) + group_0.aircraft:avionics:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.avionics.aircraft:avionics:mass_scaler) + group_0.aircraft:canard:area (group_0.pre_mission.core_subsystems.core_geometry.canard.aircraft:canard:area) + group_0.aircraft:canard:area (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:canard:area) + group_0.aircraft:canard:area (group_0.pre_mission.core_subsystems.core_mass.canard.aircraft:canard:area) + group_0.aircraft:canard:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:canard:aspect_ratio) + group_0.aircraft:canard:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.canard.aircraft:canard:mass_scaler) + group_0.aircraft:canard:taper_ratio (group_0.pre_mission.core_subsystems.core_mass.canard.aircraft:canard:taper_ratio) + group_0.aircraft:canard:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.canard.aircraft:canard:thickness_to_chord) + group_0.aircraft:canard:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:canard:thickness_to_chord) + group_0.aircraft:canard:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.canard.aircraft:canard:wetted_area_scaler) + group_0.aircraft:crew_and_payload:cargo_container_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.cargo_containers.aircraft:crew_and_payload:cargo_container_mass_scaler) + group_0.aircraft:crew_and_payload:cargo_mass (group_0.pre_mission.core_subsystems.core_mass.cargo_containers.aircraft:crew_and_payload:cargo_mass) + group_0.aircraft:crew_and_payload:cargo_mass (group_0.pre_mission.core_subsystems.core_mass.total_mass.zero_fuel_mass.aircraft:crew_and_payload:cargo_mass) + group_0.aircraft:crew_and_payload:flight_crew_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.flight_crew.aircraft:crew_and_payload:flight_crew_mass_scaler) + group_0.aircraft:crew_and_payload:misc_cargo (group_0.pre_mission.core_subsystems.core_mass.cargo.aircraft:crew_and_payload:misc_cargo) + group_0.aircraft:crew_and_payload:non_flight_crew_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.nonflight_crew.aircraft:crew_and_payload:non_flight_crew_mass_scaler) + group_0.aircraft:crew_and_payload:passenger_service_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.pass_service.aircraft:crew_and_payload:passenger_service_mass_scaler) + group_0.aircraft:crew_and_payload:wing_cargo (group_0.pre_mission.core_subsystems.core_mass.cargo.aircraft:crew_and_payload:wing_cargo) + group_0.aircraft:design:base_area (group_0.traj.param_comp.parameters:aircraft:design:base_area) + group_0.aircraft:design:empty_mass_margin_scaler (group_0.pre_mission.core_subsystems.core_mass.total_mass.empty_mass_margin.aircraft:design:empty_mass_margin_scaler) + group_0.aircraft:design:external_subsystems_mass (group_0.pre_mission.core_subsystems.core_mass.total_mass.system_equip_mass.aircraft:design:external_subsystems_mass) + group_0.aircraft:design:lift_dependent_drag_coeff_factor (group_0.traj.param_comp.parameters:aircraft:design:lift_dependent_drag_coeff_factor) + group_0.aircraft:design:reserve_fuel_additional (group_0.post_mission.reserve_fuel.reserve_fuel_additional) + group_0.aircraft:design:subsonic_drag_coeff_factor (group_0.traj.param_comp.parameters:aircraft:design:subsonic_drag_coeff_factor) + group_0.aircraft:design:supersonic_drag_coeff_factor (group_0.traj.param_comp.parameters:aircraft:design:supersonic_drag_coeff_factor) + group_0.aircraft:design:zero_lift_drag_coeff_factor (group_0.traj.param_comp.parameters:aircraft:design:zero_lift_drag_coeff_factor) + group_0.aircraft:electrical:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.electrical.aircraft:electrical:mass_scaler) + group_0.aircraft:engine:mass (group_0.pre_mission.core_subsystems.core_mass.wing_group.engine_pod_mass.aircraft:engine:mass) + group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_propulsion.CF6.aircraft:engine:scaled_sls_thrust) + group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_propulsion.propulsion_sum.aircraft:engine:scaled_sls_thrust) + group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_subsystems.core_mass.engine_mass.aircraft:engine:scaled_sls_thrust) + group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_subsystems.core_mass.nacelle.aircraft:engine:scaled_sls_thrust) + group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_subsystems.core_mass.thrust_rev.aircraft:engine:scaled_sls_thrust) + group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_subsystems.core_mass.wing_group.engine_pod_mass.aircraft:engine:scaled_sls_thrust) + group_0.aircraft:engine:thrust_reversers_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.thrust_rev.aircraft:engine:thrust_reversers_mass_scaler) + group_0.aircraft:engine:wing_locations (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:engine:wing_locations) + group_0.aircraft:engine:wing_locations (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:engine:wing_locations) + group_0.aircraft:fins:area (group_0.pre_mission.core_subsystems.core_mass.fin.aircraft:fins:area) + group_0.aircraft:fins:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.fin.aircraft:fins:mass_scaler) + group_0.aircraft:fins:taper_ratio (group_0.pre_mission.core_subsystems.core_mass.fin.aircraft:fins:taper_ratio) + group_0.aircraft:fuel:auxiliary_fuel_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.total_fuel_capacity.aircraft:fuel:auxiliary_fuel_capacity) + group_0.aircraft:fuel:capacity_factor (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:capacity_factor) + group_0.aircraft:fuel:density_ratio (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:density_ratio) + group_0.aircraft:fuel:density_ratio (group_0.pre_mission.core_subsystems.core_mass.unusable_fuel.aircraft:fuel:density_ratio) + group_0.aircraft:fuel:fuel_margin (group_0.post_mission.fuel_calc.fuel_margin) + group_0.aircraft:fuel:fuel_system_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.fuel_system.aircraft:fuel:fuel_system_mass_scaler) + group_0.aircraft:fuel:fuselage_fuel_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.auxiliary_fuel_capacity.aircraft:fuel:fuselage_fuel_capacity) + group_0.aircraft:fuel:fuselage_fuel_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.total_fuel_capacity.aircraft:fuel:fuselage_fuel_capacity) + group_0.aircraft:fuel:total_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.auxiliary_fuel_capacity.aircraft:fuel:total_capacity) + group_0.aircraft:fuel:total_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.fuselage_fuel_capacity.aircraft:fuel:total_capacity) + group_0.aircraft:fuel:total_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_system.aircraft:fuel:total_capacity) + group_0.aircraft:fuel:total_capacity (group_0.pre_mission.core_subsystems.core_mass.unusable_fuel.aircraft:fuel:total_capacity) + group_0.aircraft:fuel:unusable_fuel_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.unusable_fuel.aircraft:fuel:unusable_fuel_mass_scaler) + group_0.aircraft:fuel:wing_ref_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:wing_ref_capacity) + group_0.aircraft:fuel:wing_ref_capacity_area (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:wing_ref_capacity_area) + group_0.aircraft:fuel:wing_ref_capacity_term_A (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:wing_ref_capacity_term_A) + group_0.aircraft:fuel:wing_ref_capacity_term_B (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:wing_ref_capacity_term_B) + group_0.aircraft:furnishings:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.furnishings.aircraft:furnishings:mass_scaler) + group_0.aircraft:fuselage:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:fuselage:laminar_flow_lower) + group_0.aircraft:fuselage:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:fuselage:laminar_flow_upper) + group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:fuselage:length) + group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:fuselage:length) + group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_geometry.fuselage_prelim.aircraft:fuselage:length) + group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_mass.electrical.aircraft:fuselage:length) + group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_mass.fuselage.aircraft:fuselage:length) + group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:fuselage:length) + group_0.aircraft:fuselage:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.fuselage.aircraft:fuselage:mass_scaler) + group_0.aircraft:fuselage:max_height (group_0.pre_mission.core_subsystems.core_geometry.fuselage_prelim.aircraft:fuselage:max_height) + group_0.aircraft:fuselage:max_height (group_0.pre_mission.core_subsystems.core_mass.AC.aircraft:fuselage:max_height) + group_0.aircraft:fuselage:max_height (group_0.pre_mission.core_subsystems.core_mass.furnishings.aircraft:fuselage:max_height) + group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_geometry.fuselage_prelim.aircraft:fuselage:max_width) + group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:fuselage:max_width) + group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_mass.anti_icing.aircraft:fuselage:max_width) + group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_mass.electrical.aircraft:fuselage:max_width) + group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_mass.furnishings.aircraft:fuselage:max_width) + group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:fuselage:max_width) + group_0.aircraft:fuselage:passenger_compartment_length (group_0.pre_mission.core_subsystems.core_mass.furnishings.aircraft:fuselage:passenger_compartment_length) + group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.AC.aircraft:fuselage:planform_area) + group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.apu.aircraft:fuselage:planform_area) + group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.avionics.aircraft:fuselage:planform_area) + group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.hydraulics.aircraft:fuselage:planform_area) + group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.instruments.aircraft:fuselage:planform_area) + group_0.aircraft:fuselage:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:fuselage:wetted_area_scaler) + group_0.aircraft:horizontal_tail:area (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:horizontal_tail:area) + group_0.aircraft:horizontal_tail:area (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:horizontal_tail:area) + group_0.aircraft:horizontal_tail:area (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:horizontal_tail:area) + group_0.aircraft:horizontal_tail:area (group_0.pre_mission.core_subsystems.core_mass.htail.aircraft:horizontal_tail:area) + group_0.aircraft:horizontal_tail:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:horizontal_tail:aspect_ratio) + group_0.aircraft:horizontal_tail:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:horizontal_tail:aspect_ratio) + group_0.aircraft:horizontal_tail:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:horizontal_tail:laminar_flow_lower) + group_0.aircraft:horizontal_tail:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:horizontal_tail:laminar_flow_upper) + group_0.aircraft:horizontal_tail:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.htail.aircraft:horizontal_tail:mass_scaler) + group_0.aircraft:horizontal_tail:taper_ratio (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:horizontal_tail:taper_ratio) + group_0.aircraft:horizontal_tail:taper_ratio (group_0.pre_mission.core_subsystems.core_mass.htail.aircraft:horizontal_tail:taper_ratio) + group_0.aircraft:horizontal_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:horizontal_tail:thickness_to_chord) + group_0.aircraft:horizontal_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:horizontal_tail:thickness_to_chord) + group_0.aircraft:horizontal_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:horizontal_tail:thickness_to_chord) + group_0.aircraft:horizontal_tail:vertical_tail_fraction (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:horizontal_tail:vertical_tail_fraction) + group_0.aircraft:horizontal_tail:vertical_tail_fraction (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:horizontal_tail:vertical_tail_fraction) + group_0.aircraft:horizontal_tail:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:horizontal_tail:wetted_area_scaler) + group_0.aircraft:hydraulics:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.hydraulics.aircraft:hydraulics:mass_scaler) + group_0.aircraft:hydraulics:system_pressure (group_0.pre_mission.core_subsystems.core_mass.hydraulics.aircraft:hydraulics:system_pressure) + group_0.aircraft:instruments:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.instruments.aircraft:instruments:mass_scaler) + group_0.aircraft:landing_gear:main_gear_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.landing_group.landing_gear.aircraft:landing_gear:main_gear_mass_scaler) + group_0.aircraft:landing_gear:nose_gear_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.landing_group.landing_gear.aircraft:landing_gear:nose_gear_mass_scaler) + group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:nacelle:avg_diameter) + group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_geometry.nacelles.aircraft:nacelle:avg_diameter) + group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_mass.anti_icing.aircraft:nacelle:avg_diameter) + group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:nacelle:avg_diameter) + group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_mass.nacelle.aircraft:nacelle:avg_diameter) + group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_mass.starter.aircraft:nacelle:avg_diameter) + group_0.aircraft:nacelle:avg_length (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:nacelle:avg_length) + group_0.aircraft:nacelle:avg_length (group_0.pre_mission.core_subsystems.core_geometry.nacelles.aircraft:nacelle:avg_length) + group_0.aircraft:nacelle:avg_length (group_0.pre_mission.core_subsystems.core_mass.nacelle.aircraft:nacelle:avg_length) + group_0.aircraft:nacelle:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:nacelle:laminar_flow_lower) + group_0.aircraft:nacelle:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:nacelle:laminar_flow_upper) + group_0.aircraft:nacelle:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.nacelle.aircraft:nacelle:mass_scaler) + group_0.aircraft:nacelle:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.nacelles.aircraft:nacelle:wetted_area_scaler) + group_0.aircraft:paint:mass_per_unit_area (group_0.pre_mission.core_subsystems.core_mass.paint.aircraft:paint:mass_per_unit_area) + group_0.aircraft:propulsion:engine_oil_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.engine_oil.aircraft:propulsion:engine_oil_mass_scaler) + group_0.aircraft:propulsion:misc_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.misc_engine.aircraft:propulsion:misc_mass_scaler) + group_0.aircraft:vertical_tail:area (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:vertical_tail:area) + group_0.aircraft:vertical_tail:area (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:vertical_tail:area) + group_0.aircraft:vertical_tail:area (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:vertical_tail:area) + group_0.aircraft:vertical_tail:area (group_0.pre_mission.core_subsystems.core_mass.vert_tail.aircraft:vertical_tail:area) + group_0.aircraft:vertical_tail:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:vertical_tail:aspect_ratio) + group_0.aircraft:vertical_tail:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:vertical_tail:aspect_ratio) + group_0.aircraft:vertical_tail:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:vertical_tail:laminar_flow_lower) + group_0.aircraft:vertical_tail:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:vertical_tail:laminar_flow_upper) + group_0.aircraft:vertical_tail:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.vert_tail.aircraft:vertical_tail:mass_scaler) + group_0.aircraft:vertical_tail:taper_ratio (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:vertical_tail:taper_ratio) + group_0.aircraft:vertical_tail:taper_ratio (group_0.pre_mission.core_subsystems.core_mass.vert_tail.aircraft:vertical_tail:taper_ratio) + group_0.aircraft:vertical_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:vertical_tail:thickness_to_chord) + group_0.aircraft:vertical_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:vertical_tail:thickness_to_chord) + group_0.aircraft:vertical_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:vertical_tail:thickness_to_chord) + group_0.aircraft:vertical_tail:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:vertical_tail:wetted_area_scaler) + group_0.aircraft:wing:aeroelastic_tailoring_factor (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:aeroelastic_tailoring_factor) + group_0.aircraft:wing:aeroelastic_tailoring_factor (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:aeroelastic_tailoring_factor) + group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:wing:area) + group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:wing:area) + group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:wing:area) + group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.wing.aircraft:wing:area) + group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.wing_prelim.aircraft:wing:area) + group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:wing:area) + group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.hydraulics.aircraft:wing:area) + group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.surf_ctrl.aircraft:wing:area) + group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.unusable_fuel.aircraft:wing:area) + group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_misc.aircraft:wing:area) + group_0.aircraft:wing:area (group_0.traj.param_comp.parameters:aircraft:wing:area) + group_0.aircraft:wing:aspect_ratio (group_0.pre_mission.core_subsystems.core_aerodynamics.design.aircraft:wing:aspect_ratio) + group_0.aircraft:wing:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:wing:aspect_ratio) + group_0.aircraft:wing:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:wing:aspect_ratio) + group_0.aircraft:wing:aspect_ratio (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:aspect_ratio) + group_0.aircraft:wing:aspect_ratio (group_0.traj.param_comp.parameters:aircraft:wing:aspect_ratio) + group_0.aircraft:wing:aspect_ratio_reference (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:aspect_ratio_reference) + group_0.aircraft:wing:bending_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:bending_mass_scaler) + group_0.aircraft:wing:bwb_aft_body_mass (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_total.aircraft:wing:bwb_aft_body_mass) + group_0.aircraft:wing:chord_per_semispan (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:chord_per_semispan) + group_0.aircraft:wing:composite_fraction (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:composite_fraction) + group_0.aircraft:wing:composite_fraction (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_misc.aircraft:wing:composite_fraction) + group_0.aircraft:wing:composite_fraction (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_shear_control.aircraft:wing:composite_fraction) + group_0.aircraft:wing:control_surface_area (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_shear_control.aircraft:wing:control_surface_area) + group_0.aircraft:wing:control_surface_area_ratio (group_0.pre_mission.core_subsystems.core_mass.surf_ctrl.aircraft:wing:control_surface_area_ratio) + group_0.aircraft:wing:dihedral (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:wing:dihedral) + group_0.aircraft:wing:glove_and_bat (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:wing:glove_and_bat) + group_0.aircraft:wing:glove_and_bat (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:wing:glove_and_bat) + group_0.aircraft:wing:glove_and_bat (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:wing:glove_and_bat) + group_0.aircraft:wing:glove_and_bat (group_0.pre_mission.core_subsystems.core_geometry.wing_prelim.aircraft:wing:glove_and_bat) + group_0.aircraft:wing:incidence (group_0.traj.param_comp.parameters:aircraft:wing:incidence) + group_0.aircraft:wing:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:wing:laminar_flow_lower) + group_0.aircraft:wing:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:wing:laminar_flow_upper) + group_0.aircraft:wing:load_fraction (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:load_fraction) + group_0.aircraft:wing:load_path_sweep_dist (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:load_path_sweep_dist) + group_0.aircraft:wing:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_total.aircraft:wing:mass_scaler) + group_0.aircraft:wing:max_camber_at_70_semispan (group_0.pre_mission.core_subsystems.core_aerodynamics.design.aircraft:wing:max_camber_at_70_semispan) + group_0.aircraft:wing:max_camber_at_70_semispan (group_0.traj.param_comp.parameters:aircraft:wing:max_camber_at_70_semispan) + group_0.aircraft:wing:misc_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:misc_mass_scaler) + group_0.aircraft:wing:misc_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_misc.aircraft:wing:misc_mass_scaler) + group_0.aircraft:wing:shear_control_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:shear_control_mass_scaler) + group_0.aircraft:wing:shear_control_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_shear_control.aircraft:wing:shear_control_mass_scaler) + group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:wing:span) + group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_geometry.wing_prelim.aircraft:wing:span) + group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_mass.anti_icing.aircraft:wing:span) + group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:wing:span) + group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:wing:span) + group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:span) +""" diff --git a/test_single_aviary.py b/test_single_aviary.py new file mode 100644 index 000000000..a06ffd6a1 --- /dev/null +++ b/test_single_aviary.py @@ -0,0 +1,22 @@ +import aviary.api as av +from easy_phase_info_max import phase_info + + +prob = av.AviaryProblem() +prob.load_inputs("c5_models/c5_maxpayload.csv", phase_info) +prob.check_and_preprocess_inputs() +prob.add_pre_mission_systems() +prob.add_phases() +prob.add_post_mission_systems() +prob.link_phases() +prob.add_design_variables() + +# Load optimization problem formulation +# Detail which variables the optimizer can control +prob.add_objective() + +prob.setup() + +prob.set_initial_guesses() +# prob.final_setup() +prob.run_aviary_problem() From 19fd974a735ce761eb73f71087e628dbbfef2a35 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Tue, 6 Aug 2024 09:55:46 -0400 Subject: [PATCH 030/113] updated objective to use Aviary's fuel obj --- multi_aviary_copymodel.py | 15 +++++++++++---- 1 file changed, 11 insertions(+), 4 deletions(-) diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index ead41f68e..f06b1ec75 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -16,6 +16,7 @@ from c5_models.c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info from easy_phase_info_inter import phase_info as easy_inter from easy_phase_info_max import phase_info as easy_max +from aviary.variable_info.variables import Mission, Aircraft # "comp?.a can be used to reference multiple comp1.a comp2.a etc" @@ -92,8 +93,8 @@ def add_objective(self): for i in range(self.num_missions): # connecting each subcomponent's fuel burn to super problem's unique fuel variables self.model.connect( - self.group_prefix+f"_{i}.mission:summary:fuel_burned", f"fuel_{i}") - self.model.add_objective('compound', scaler=1.) + self.group_prefix+f"_{i}.{Mission.Objectives.FUEL}", f"fuel_{i}") + self.model.add_objective('compound', ref=1e4) def setup_wrapper(self): """Wrapper for om.Problem setup with warning ignoring and setting options""" @@ -115,8 +116,8 @@ def run(self): # self.check_totals(method='fd', compact_print=True) self.model.set_solver_print(0) - self.run_driver() - # dm.run_problem(self, make_plots=True) + # self.run_driver() + dm.run_problem(self, make_plots=True) if __name__ == '__main__': @@ -145,6 +146,12 @@ def run(self): createN2(__file__, super_prob) super_prob.run() + print("\n\n=========================\nEmpty masses:") + print(super_prob.get_val(f'group_0.{Aircraft.Design.EMPTY_MASS}')) + print(super_prob.get_val(f'group_1.{Aircraft.Design.EMPTY_MASS}')) + print("Fuel burned") + print(super_prob.get_val(f'group_0.{Mission.Summary.FUEL_BURNED}')) + print(super_prob.get_val(f'group_1.{Mission.Summary.FUEL_BURNED}')) # def initvals(self): # """attempting to copy over aviary code for setting initial values and changing references""" # for i, prob in enumerate(self.probs): From b1d227e050a7cf9d366a644d2489b0fd8c680063 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Tue, 6 Aug 2024 10:11:00 -0400 Subject: [PATCH 031/113] comparable outputs for multi mission and single missions --- multi_aviary_copymodel.py | 561 +++++++++++++++++++------------------- test_single_aviary.py | 57 ++-- 2 files changed, 327 insertions(+), 291 deletions(-) diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index f06b1ec75..40ea1ad61 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -146,284 +146,295 @@ def run(self): createN2(__file__, super_prob) super_prob.run() - print("\n\n=========================\nEmpty masses:") - print(super_prob.get_val(f'group_0.{Aircraft.Design.EMPTY_MASS}')) - print(super_prob.get_val(f'group_1.{Aircraft.Design.EMPTY_MASS}')) - print("Fuel burned") - print(super_prob.get_val(f'group_0.{Mission.Summary.FUEL_BURNED}')) - print(super_prob.get_val(f'group_1.{Mission.Summary.FUEL_BURNED}')) - # def initvals(self): - # """attempting to copy over aviary code for setting initial values and changing references""" - # for i, prob in enumerate(self.probs): - # setvalprob.set_val(parent_prefix+self.group_prefix + - # f'_{i}.aircraft:design:landing_to_takeoff_mass_ratio', 0.5) - # # Grab the trajectory object from the model - # traj = prob.model.traj - - # # Determine which phases to loop over, fetching them from the trajectory - # phase_items = traj._phases.items() - - # # Loop over each phase and set initial guesses for the state and control variables - # for idx, (phase_name, phase) in enumerate(phase_items): - # # If not, fetch the initial guesses specific to the phase - # # check if guesses exist for this phase - # if "initial_guesses" in prob.phase_info[phase_name]: - # guesses = prob.phase_info[phase_name]['initial_guesses'] - # else: - # guesses = {} - - # # ||||||||||||| _add_subsystem_guesses - # # Get all subsystems associated with the phase - # all_subsystems = prob._get_all_subsystems( - # prob.phase_info[phase_name]['external_subsystems']) - - # # Loop over each subsystem - # for subsystem in all_subsystems: - # # Fetch the initial guesses for the subsystem - # initial_guesses = subsystem.get_initial_guesses() - - # # Loop over each guess - # for key, val in initial_guesses.items(): - # # Identify the type of the guess (state or control) - # type = val.pop('type') - # if 'state' in type: - # path_string = 'states' - # elif 'control' in type: - # path_string = 'controls' - - # # Process the guess variable (handles array interpolation) - # val['val'] = prob._process_guess_var(val['val'], key, phase) - - # # Set the initial guess in the problem - # setvalprob.set_val(parent_prefix+ - # self.group_prefix + - # f'_{i}.traj.{phase_name}.{path_string}:{key}', **val) - - # # Set initial guesses for states and controls for each phase - - # # |||||||||||||||||||||| _add_guesses - # # If using the GASP model, set initial guesses for the rotation mass and flight duration - # if prob.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): - # control_keys = ["mach", "altitude"] - # state_keys = ["mass", Dynamic.Mission.DISTANCE] - # prob_keys = ["tau_gear", "tau_flaps"] - - # # for the simple mission method, use the provided initial and final mach and altitude values from phase_info - # if prob.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): - # initial_altitude = wrapped_convert_units( - # prob.phase_info[phase_name]['user_options'] - # ['initial_altitude'], - # 'ft') - # final_altitude = wrapped_convert_units( - # prob.phase_info[phase_name]['user_options']['final_altitude'], 'ft') - # initial_mach = prob.phase_info[phase_name]['user_options'][ - # 'initial_mach'] - # final_mach = prob.phase_info[phase_name]['user_options'][ - # 'final_mach'] - - # guesses["mach"] = ([initial_mach[0], final_mach[0]], "unitless") - # guesses["altitude"] = ([initial_altitude, final_altitude], 'ft') - - # if prob.mission_method is HEIGHT_ENERGY: - # # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds - # if 'time' not in guesses: - # initial_bounds = wrapped_convert_units( - # prob.phase_info[phase_name]['user_options']['initial_bounds'], 's') - # duration_bounds = wrapped_convert_units( - # prob.phase_info[phase_name]['user_options']['duration_bounds'], 's') - # guesses["time"] = ([np.mean(initial_bounds[0]), np.mean( - # duration_bounds[0])], 's') - - # # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds - # if 'time' not in guesses: - # initial_bounds = prob.phase_info[phase_name]['user_options'][ - # 'initial_bounds'] - # duration_bounds = prob.phase_info[phase_name]['user_options'][ - # 'duration_bounds'] - # # Add a check for the initial and duration bounds, raise an error if they are not consistent - # if initial_bounds[1] != duration_bounds[1]: - # raise ValueError( - # f"Initial and duration bounds for {phase_name} are not consistent.") - # guesses["time"] = ([np.mean(initial_bounds[0]), np.mean( - # duration_bounds[0])], initial_bounds[1]) - - # for guess_key, guess_data in guesses.items(): - # val, units = guess_data - - # # Set initial guess for time variables - # if 'time' == guess_key and prob.mission_method is not SOLVED_2DOF: - # setvalprob.set_val(parent_prefix+ - # self.group_prefix + f'_{i}.traj.{phase_name}.t_initial', - # val[0], - # units=units) - # setvalprob.set_val(parent_prefix+ - # self.group_prefix + f'_{i}.traj.{phase_name}.t_duration', - # val[1], - # units=units) - - # else: - # # Set initial guess for control variables - # if guess_key in control_keys: - # try: - # setvalprob.set_val(parent_prefix+self.group_prefix + - # f'_{i}.traj.{phase_name}.controls:{guess_key}', - # prob._process_guess_var( - # val, guess_key, phase), - # units=units) - # except KeyError: - # try: - # setvalprob.set_val(parent_prefix+ - # self.group_prefix + - # f'_{i}.traj.{phase_name}.polynomial_controls:{guess_key}', - # prob._process_guess_var(val, guess_key, phase), - # units=units) - # except KeyError: - # setvalprob.set_val(parent_prefix+ - # self.group_prefix + - # f'_{i}.traj.{phase_name}.bspline_controls:{guess_key}', - # prob._process_guess_var(val, guess_key, phase), - # units=units) - - # if guess_key in control_keys: - # pass - # # Set initial guess for state variables - # elif guess_key in state_keys: - # setvalprob.set_val(parent_prefix+self.group_prefix + - # f'_{i}.traj.{phase_name}.states:{guess_key}', - # prob._process_guess_var( - # val, guess_key, phase), - # units=units) - # elif guess_key in prob_keys: - # setvalprob.set_val(parent_prefix+ - # self.group_prefix+f'_{i}.'+guess_key, val, units=units) - # elif ":" in guess_key: - # setvalprob.set_val(parent_prefix+ - # self.group_prefix + f'_{i}.traj.{phase_name}.{guess_key}', - # prob._process_guess_var(val, guess_key, phase), - # units=units) - # else: - # # raise error if the guess key is not recognized - # raise ValueError( - # f"Initial guess key {guess_key} in {phase_name} is not recognized.") - - # # We need some special logic for these following variables because GASP computes - # # initial guesses using some knowledge of the mission duration and other variables - # # that are only available after calling `create_vehicle`. Thus these initial guess - # # values are not included in the `phase_info` object. - - # base_phase = phase_name - # if 'mass' not in guesses: - # mass_guess = prob.aviary_inputs.get_val( - # Mission.Design.GROSS_MASS, units='lbm') - # # Set the mass guess as the initial value for the mass state variable - # setvalprob.set_val(parent_prefix+self.group_prefix+f'_{i}.traj.{phase_name}.states:mass', - # mass_guess, units='lbm') - - # # if 'time' not in guesses: - # # # Determine initial time and duration guesses depending on the phase name - # # if 'desc1' == base_phase: - # # t_initial = flight_duration*.9 - # # t_duration = flight_duration*.04 - # # elif 'desc2' in base_phase: - # # t_initial = flight_duration*.94 - # # t_duration = 5000 - # # # Set the time guesses as the initial values for the time-related trajectory variables - # # setvalprob.set_val(parent_prefix+f"traj.{phase_name}.t_initial", - # # t_initial, units='s') - # # setvalprob.set_val(parent_prefix+f"traj.{phase_name}.t_duration", - # # t_duration, units='s') + outputs = {Mission.Summary.FUEL_BURNED: [], + Aircraft.Design.EMPTY_MASS: []} + + print("\n\n=========================\n") + for key in outputs.keys(): + val1 = super_prob.get_val(f'group_0.{key}')[0] + val2 = super_prob.get_val(f'group_1.{key}')[0] + print(f"Variable: {key}") + print(f"Values: {val1}, {val2}") + +""" +Variable: mission:summary:fuel_burned +Values: 13730.910584707046, 15740.545749454643 +Variable: aircraft:design:empty_mass +Values: 336859.7179064408, 337047.85745526763 +""" + +# def initvals(self): +# """attempting to copy over aviary code for setting initial values and changing references""" +# for i, prob in enumerate(self.probs): +# setvalprob.set_val(parent_prefix+self.group_prefix + +# f'_{i}.aircraft:design:landing_to_takeoff_mass_ratio', 0.5) +# # Grab the trajectory object from the model +# traj = prob.model.traj + +# # Determine which phases to loop over, fetching them from the trajectory +# phase_items = traj._phases.items() + +# # Loop over each phase and set initial guesses for the state and control variables +# for idx, (phase_name, phase) in enumerate(phase_items): +# # If not, fetch the initial guesses specific to the phase +# # check if guesses exist for this phase +# if "initial_guesses" in prob.phase_info[phase_name]: +# guesses = prob.phase_info[phase_name]['initial_guesses'] +# else: +# guesses = {} + +# # ||||||||||||| _add_subsystem_guesses +# # Get all subsystems associated with the phase +# all_subsystems = prob._get_all_subsystems( +# prob.phase_info[phase_name]['external_subsystems']) + +# # Loop over each subsystem +# for subsystem in all_subsystems: +# # Fetch the initial guesses for the subsystem +# initial_guesses = subsystem.get_initial_guesses() + +# # Loop over each guess +# for key, val in initial_guesses.items(): +# # Identify the type of the guess (state or control) +# type = val.pop('type') +# if 'state' in type: +# path_string = 'states' +# elif 'control' in type: +# path_string = 'controls' + +# # Process the guess variable (handles array interpolation) +# val['val'] = prob._process_guess_var(val['val'], key, phase) + +# # Set the initial guess in the problem +# setvalprob.set_val(parent_prefix+ +# self.group_prefix + +# f'_{i}.traj.{phase_name}.{path_string}:{key}', **val) + +# # Set initial guesses for states and controls for each phase + +# # |||||||||||||||||||||| _add_guesses +# # If using the GASP model, set initial guesses for the rotation mass and flight duration +# if prob.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): +# control_keys = ["mach", "altitude"] +# state_keys = ["mass", Dynamic.Mission.DISTANCE] +# prob_keys = ["tau_gear", "tau_flaps"] + +# # for the simple mission method, use the provided initial and final mach and altitude values from phase_info +# if prob.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): +# initial_altitude = wrapped_convert_units( +# prob.phase_info[phase_name]['user_options'] +# ['initial_altitude'], +# 'ft') +# final_altitude = wrapped_convert_units( +# prob.phase_info[phase_name]['user_options']['final_altitude'], 'ft') +# initial_mach = prob.phase_info[phase_name]['user_options'][ +# 'initial_mach'] +# final_mach = prob.phase_info[phase_name]['user_options'][ +# 'final_mach'] + +# guesses["mach"] = ([initial_mach[0], final_mach[0]], "unitless") +# guesses["altitude"] = ([initial_altitude, final_altitude], 'ft') + +# if prob.mission_method is HEIGHT_ENERGY: +# # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds +# if 'time' not in guesses: +# initial_bounds = wrapped_convert_units( +# prob.phase_info[phase_name]['user_options']['initial_bounds'], 's') +# duration_bounds = wrapped_convert_units( +# prob.phase_info[phase_name]['user_options']['duration_bounds'], 's') +# guesses["time"] = ([np.mean(initial_bounds[0]), np.mean( +# duration_bounds[0])], 's') + +# # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds +# if 'time' not in guesses: +# initial_bounds = prob.phase_info[phase_name]['user_options'][ +# 'initial_bounds'] +# duration_bounds = prob.phase_info[phase_name]['user_options'][ +# 'duration_bounds'] +# # Add a check for the initial and duration bounds, raise an error if they are not consistent +# if initial_bounds[1] != duration_bounds[1]: +# raise ValueError( +# f"Initial and duration bounds for {phase_name} are not consistent.") +# guesses["time"] = ([np.mean(initial_bounds[0]), np.mean( +# duration_bounds[0])], initial_bounds[1]) + +# for guess_key, guess_data in guesses.items(): +# val, units = guess_data + +# # Set initial guess for time variables +# if 'time' == guess_key and prob.mission_method is not SOLVED_2DOF: +# setvalprob.set_val(parent_prefix+ +# self.group_prefix + f'_{i}.traj.{phase_name}.t_initial', +# val[0], +# units=units) +# setvalprob.set_val(parent_prefix+ +# self.group_prefix + f'_{i}.traj.{phase_name}.t_duration', +# val[1], +# units=units) + +# else: +# # Set initial guess for control variables +# if guess_key in control_keys: +# try: +# setvalprob.set_val(parent_prefix+self.group_prefix + +# f'_{i}.traj.{phase_name}.controls:{guess_key}', +# prob._process_guess_var( +# val, guess_key, phase), +# units=units) +# except KeyError: +# try: +# setvalprob.set_val(parent_prefix+ +# self.group_prefix + +# f'_{i}.traj.{phase_name}.polynomial_controls:{guess_key}', +# prob._process_guess_var(val, guess_key, phase), +# units=units) +# except KeyError: +# setvalprob.set_val(parent_prefix+ +# self.group_prefix + +# f'_{i}.traj.{phase_name}.bspline_controls:{guess_key}', +# prob._process_guess_var(val, guess_key, phase), +# units=units) + +# if guess_key in control_keys: +# pass +# # Set initial guess for state variables +# elif guess_key in state_keys: +# setvalprob.set_val(parent_prefix+self.group_prefix + +# f'_{i}.traj.{phase_name}.states:{guess_key}', +# prob._process_guess_var( +# val, guess_key, phase), +# units=units) +# elif guess_key in prob_keys: +# setvalprob.set_val(parent_prefix+ +# self.group_prefix+f'_{i}.'+guess_key, val, units=units) +# elif ":" in guess_key: +# setvalprob.set_val(parent_prefix+ +# self.group_prefix + f'_{i}.traj.{phase_name}.{guess_key}', +# prob._process_guess_var(val, guess_key, phase), +# units=units) +# else: +# # raise error if the guess key is not recognized +# raise ValueError( +# f"Initial guess key {guess_key} in {phase_name} is not recognized.") + +# # We need some special logic for these following variables because GASP computes +# # initial guesses using some knowledge of the mission duration and other variables +# # that are only available after calling `create_vehicle`. Thus these initial guess +# # values are not included in the `phase_info` object. + +# base_phase = phase_name +# if 'mass' not in guesses: +# mass_guess = prob.aviary_inputs.get_val( +# Mission.Design.GROSS_MASS, units='lbm') +# # Set the mass guess as the initial value for the mass state variable +# setvalprob.set_val(parent_prefix+self.group_prefix+f'_{i}.traj.{phase_name}.states:mass', +# mass_guess, units='lbm') + +# # if 'time' not in guesses: +# # # Determine initial time and duration guesses depending on the phase name +# # if 'desc1' == base_phase: +# # t_initial = flight_duration*.9 +# # t_duration = flight_duration*.04 +# # elif 'desc2' in base_phase: +# # t_initial = flight_duration*.94 +# # t_duration = 5000 +# # # Set the time guesses as the initial values for the time-related trajectory variables +# # setvalprob.set_val(parent_prefix+f"traj.{phase_name}.t_initial", +# # t_initial, units='s') +# # setvalprob.set_val(parent_prefix+f"traj.{phase_name}.t_duration", +# # t_duration, units='s') # ========================================================================= old code - # super_prob = om.Problem() - # num_missions = len(weights) - # probs = [] - # prefix = "problem_" - - # makeN2 = False - # if len(sys.argv) > 1: - # if "n2" in sys.argv: - # makeN2 = True - - # # define individual aviary problems - # for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): - # prob = av.AviaryProblem() - # prob.load_inputs(plane, phase_info) - # prob.check_and_preprocess_inputs() - # prob.add_pre_mission_systems() - # traj = prob.add_phases() # save dymos traj to add to super problem as a subsystem - # prob.add_post_mission_systems() - # prob.link_phases() # this is half working / connect statements from outside of traj to inside are failing - # prob.problem_type = ProblemType.ALTERNATE # adds summary gross mass as design var - # prob.add_design_variables() - # probs.append(prob) - - # group = om.Group() # this group will contain all the promoted aviary vars - # group.add_subsystem("pre", prob.pre_mission) - # group.add_subsystem("traj", traj) - # group.add_subsystem("post", prob.post_mission) - - # # setting defaults for these variables to suppress errors - # longlst = [ - # 'mission:summary:gross_mass', 'aircraft:wing:sweep', - # 'aircraft:wing:thickness_to_chord', 'aircraft:wing:area', - # 'aircraft:wing:taper_ratio', 'mission:design:gross_mass'] - # for var in longlst: - # group.set_input_defaults( - # var, val=MetaData[var]['default_value'], - # units=MetaData[var]['units']) - - # # add group and promote design gross mass (common input amongst multiple missions) - # # in this way it represents the MTOW - # super_prob.model.add_subsystem(prefix+f'{i}', group, promotes=[ - # 'mission:design:gross_mass']) - - # # add design gross mass as a design var - # super_prob.model.add_design_var( - # 'mission:design:gross_mass', lower=100e3, upper=1000e3) - - # for i in range(num_missions): - # # connecting each subcomponent's fuel burn to super problem's unique fuel variables - # super_prob.model.connect( - # prefix+f"{i}.mission:summary:fuel_burned", f"fuel_{i}") - - # # create constraint to force each mission's summary gross mass to not - # # exceed the common mission design gross mass (aka MTOW) - # super_prob.model.add_subsystem(f'MTOW_constraint{i}', om.ExecComp( - # 'mtow_resid = design_gross_mass - summary_gross_mass'), - # promotes=[('summary_gross_mass', prefix+f'{i}.mission:summary:gross_mass'), - # ('design_gross_mass', 'mission:design:gross_mass')]) - - # super_prob.model.add_constraint(f'MTOW_constraint{i}.mtow_resid', lower=0.) - - # # creating variable strings that will represent fuel burn from each mission - # fuel_burned_vars = [f"fuel_{i}" for i in range(num_missions)] - # weighted_str = "+".join([f"{fuel}*{weight}" - # for fuel, weight in zip(fuel_burned_vars, weights)]) - # # weighted_str looks like: fuel_0 * weight[0] + fuel_1 * weight[1] - - # # adding compound execComp to super problem - # super_prob.model.add_subsystem('compound_fuel_burn_objective', om.ExecComp( - # "compound = "+weighted_str), promotes=["compound", *fuel_burned_vars]) - - # super_prob.driver = om.ScipyOptimizeDriver() - # super_prob.driver.options['optimizer'] = 'SLSQP' - # super_prob.model.add_objective('compound') # output from execcomp goes here - - # with warnings.catch_warnings(): - # warnings.simplefilter("ignore", om.OpenMDAOWarning) - # warnings.simplefilter("ignore", om.PromotionWarning) - # super_prob.setup() - - # if makeN2: - # om.n2(super_prob, outfile="multi_mission_importTraj_N2.html") # create N2 diagram - - # # cannot use this b/c initial guesses (i.e. setval func) has to be called on super prob level - # # for prob in probs: - # # # prob.setup() - # # prob.set_initial_guesses() - - # # dm.run_problem(super_prob) +# super_prob = om.Problem() +# num_missions = len(weights) +# probs = [] +# prefix = "problem_" + +# makeN2 = False +# if len(sys.argv) > 1: +# if "n2" in sys.argv: +# makeN2 = True + +# # define individual aviary problems +# for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): +# prob = av.AviaryProblem() +# prob.load_inputs(plane, phase_info) +# prob.check_and_preprocess_inputs() +# prob.add_pre_mission_systems() +# traj = prob.add_phases() # save dymos traj to add to super problem as a subsystem +# prob.add_post_mission_systems() +# prob.link_phases() # this is half working / connect statements from outside of traj to inside are failing +# prob.problem_type = ProblemType.ALTERNATE # adds summary gross mass as design var +# prob.add_design_variables() +# probs.append(prob) + +# group = om.Group() # this group will contain all the promoted aviary vars +# group.add_subsystem("pre", prob.pre_mission) +# group.add_subsystem("traj", traj) +# group.add_subsystem("post", prob.post_mission) + +# # setting defaults for these variables to suppress errors +# longlst = [ +# 'mission:summary:gross_mass', 'aircraft:wing:sweep', +# 'aircraft:wing:thickness_to_chord', 'aircraft:wing:area', +# 'aircraft:wing:taper_ratio', 'mission:design:gross_mass'] +# for var in longlst: +# group.set_input_defaults( +# var, val=MetaData[var]['default_value'], +# units=MetaData[var]['units']) + +# # add group and promote design gross mass (common input amongst multiple missions) +# # in this way it represents the MTOW +# super_prob.model.add_subsystem(prefix+f'{i}', group, promotes=[ +# 'mission:design:gross_mass']) + +# # add design gross mass as a design var +# super_prob.model.add_design_var( +# 'mission:design:gross_mass', lower=100e3, upper=1000e3) + +# for i in range(num_missions): +# # connecting each subcomponent's fuel burn to super problem's unique fuel variables +# super_prob.model.connect( +# prefix+f"{i}.mission:summary:fuel_burned", f"fuel_{i}") + +# # create constraint to force each mission's summary gross mass to not +# # exceed the common mission design gross mass (aka MTOW) +# super_prob.model.add_subsystem(f'MTOW_constraint{i}', om.ExecComp( +# 'mtow_resid = design_gross_mass - summary_gross_mass'), +# promotes=[('summary_gross_mass', prefix+f'{i}.mission:summary:gross_mass'), +# ('design_gross_mass', 'mission:design:gross_mass')]) + +# super_prob.model.add_constraint(f'MTOW_constraint{i}.mtow_resid', lower=0.) + +# # creating variable strings that will represent fuel burn from each mission +# fuel_burned_vars = [f"fuel_{i}" for i in range(num_missions)] +# weighted_str = "+".join([f"{fuel}*{weight}" +# for fuel, weight in zip(fuel_burned_vars, weights)]) +# # weighted_str looks like: fuel_0 * weight[0] + fuel_1 * weight[1] + +# # adding compound execComp to super problem +# super_prob.model.add_subsystem('compound_fuel_burn_objective', om.ExecComp( +# "compound = "+weighted_str), promotes=["compound", *fuel_burned_vars]) + +# super_prob.driver = om.ScipyOptimizeDriver() +# super_prob.driver.options['optimizer'] = 'SLSQP' +# super_prob.model.add_objective('compound') # output from execcomp goes here + +# with warnings.catch_warnings(): +# warnings.simplefilter("ignore", om.OpenMDAOWarning) +# warnings.simplefilter("ignore", om.PromotionWarning) +# super_prob.setup() + +# if makeN2: +# om.n2(super_prob, outfile="multi_mission_importTraj_N2.html") # create N2 diagram + +# # cannot use this b/c initial guesses (i.e. setval func) has to be called on super prob level +# # for prob in probs: +# # # prob.setup() +# # prob.set_initial_guesses() + +# # dm.run_problem(super_prob) """ diff --git a/test_single_aviary.py b/test_single_aviary.py index a06ffd6a1..82406d682 100644 --- a/test_single_aviary.py +++ b/test_single_aviary.py @@ -1,22 +1,47 @@ import aviary.api as av -from easy_phase_info_max import phase_info +from easy_phase_info_max import phase_info as max_phase_info +from easy_phase_info_inter import phase_info as inter_phase_info +from aviary.variable_info.variables import Mission, Aircraft -prob = av.AviaryProblem() -prob.load_inputs("c5_models/c5_maxpayload.csv", phase_info) -prob.check_and_preprocess_inputs() -prob.add_pre_mission_systems() -prob.add_phases() -prob.add_post_mission_systems() -prob.link_phases() -prob.add_design_variables() +outputs = {Mission.Summary.FUEL_BURNED: [], + Aircraft.Design.EMPTY_MASS: []} +for plane, phase_info in zip( + ['c5_maxpayload', 'c5_intermediate'], + [max_phase_info, inter_phase_info]): -# Load optimization problem formulation -# Detail which variables the optimizer can control -prob.add_objective() + prob = av.AviaryProblem() + prob.load_inputs(f"c5_models/{plane}.csv", phase_info) + prob.check_and_preprocess_inputs() + prob.add_pre_mission_systems() + prob.add_phases() + prob.add_post_mission_systems() + prob.link_phases() + prob.add_driver('SLSQP') + prob.add_design_variables() -prob.setup() + # Load optimization problem formulation + # Detail which variables the optimizer can control + prob.add_objective() -prob.set_initial_guesses() -# prob.final_setup() -prob.run_aviary_problem() + prob.setup() + + prob.set_initial_guesses() + # prob.final_setup() + prob.run_aviary_problem() + + for key in outputs.keys(): + outputs[key].append(prob.get_val(key)[0]) + +print("\n\n=============================\n") +for key, item in outputs.items(): + print(f"Variable: {key}") + print(f"Values: {item}") + +""" +Current output: +Variable: mission:summary:fuel_burned +Values: [140116.12301917037, 276762.7974282048] +Variable: aircraft:design:empty_mass +Values: [302105.1606792437, 315604.5402712884] +""" From 40aeca130f6b4b5ddb739a1b87c6c5626a4ab428 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Tue, 6 Aug 2024 10:38:47 -0400 Subject: [PATCH 032/113] 0/1 unknown results but need to save --- aviary/mission/flight_phase_builder.py | 4 +- multi_aviary_copymodel.py | 526 +------------------------ 2 files changed, 15 insertions(+), 515 deletions(-) diff --git a/aviary/mission/flight_phase_builder.py b/aviary/mission/flight_phase_builder.py index 17027fbeb..b7f4e3b9e 100644 --- a/aviary/mission/flight_phase_builder.py +++ b/aviary/mission/flight_phase_builder.py @@ -121,7 +121,7 @@ def build_phase(self, aviary_options: AviaryValues = None, phase_type=EquationsO phase.add_state( Dynamic.Mission.MASS, fix_initial=fix_initial_mass, fix_final=False, - lower=0.0, ref=1e4, defect_ref=1e6, units='kg', + lower=0.0, ref=1e4, defect_ref=1e4, units='kg', rate_source=rate_source, targets=Dynamic.Mission.MASS, input_initial=input_initial_mass, @@ -133,7 +133,7 @@ def build_phase(self, aviary_options: AviaryValues = None, phase_type=EquationsO fix_initial, Dynamic.Mission.DISTANCE, True) phase.add_state( Dynamic.Mission.DISTANCE, fix_initial=fix_initial_distance, fix_final=False, - lower=0.0, ref=1e6, defect_ref=1e8, units='m', + lower=0.0, ref=1e6, defect_ref=1e6, units='m', rate_source=Dynamic.Mission.DISTANCE_RATE, input_initial=input_initial_distance, solve_segments='forward' if solve_for_distance else None, diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index f06b1ec75..656bd9703 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -17,6 +17,7 @@ from easy_phase_info_inter import phase_info as easy_inter from easy_phase_info_max import phase_info as easy_max from aviary.variable_info.variables import Mission, Aircraft +from aviary.variable_info.enums import ProblemType # "comp?.a can be used to reference multiple comp1.a comp2.a etc" @@ -50,6 +51,7 @@ def __init__(self, planes, phase_infos, weights): prob.add_phases() prob.add_post_mission_systems() prob.link_phases() + prob.problem_type = ProblemType.ALTERNATE prob.add_design_variables() # should not work at super prob level self.probs.append(prob) @@ -61,12 +63,18 @@ def add_design_variables(self): self.model.add_design_var('mission:design:gross_mass', lower=10., upper=900e3) def add_driver(self): - # pyoptsparse SLSQP errors out w pos directional derivative line search (obj scaler = 1) and - # inequality constraints incompatible (obj scaler = -1) - fuel burn obj - # pyoptsparse IPOPT keeps iterating (seen upto 1000+ iters) in the IPOPT.out file but no result - # scipy SLSQP reaches iter limit and fails optimization self.driver = om.pyOptSparseDriver() - self.driver.options['optimizer'] = 'SLSQP' + + self.driver.options["optimizer"] = "SNOPT" + # driver.declare_coloring(True) # do we need this anymore of we're specifying the below? + # maybe we're getting matrixes that are too sparse, decrease tolerance to avoid missing corellatiton + # set coloring at this value. 1e-45 didn't seem to make much difference + self.driver.declare_coloring(tol=1e-25, orders=None) + self.driver.opt_settings["Major iterations limit"] = 60 + self.driver.opt_settings["Major optimality tolerance"] = 5e-4 + self.driver.opt_settings["Major feasibility tolerance"] = 4e-5 + self.driver.opt_settings["iSumm"] = 6 + self.driver.opt_settings['Verify level'] = -1 # self.driver.options['maxiter'] = 1e3 # self.driver.declare_coloring() # self.model.linear_solver = om.DirectSolver() @@ -152,511 +160,3 @@ def run(self): print("Fuel burned") print(super_prob.get_val(f'group_0.{Mission.Summary.FUEL_BURNED}')) print(super_prob.get_val(f'group_1.{Mission.Summary.FUEL_BURNED}')) - # def initvals(self): - # """attempting to copy over aviary code for setting initial values and changing references""" - # for i, prob in enumerate(self.probs): - # setvalprob.set_val(parent_prefix+self.group_prefix + - # f'_{i}.aircraft:design:landing_to_takeoff_mass_ratio', 0.5) - # # Grab the trajectory object from the model - # traj = prob.model.traj - - # # Determine which phases to loop over, fetching them from the trajectory - # phase_items = traj._phases.items() - - # # Loop over each phase and set initial guesses for the state and control variables - # for idx, (phase_name, phase) in enumerate(phase_items): - # # If not, fetch the initial guesses specific to the phase - # # check if guesses exist for this phase - # if "initial_guesses" in prob.phase_info[phase_name]: - # guesses = prob.phase_info[phase_name]['initial_guesses'] - # else: - # guesses = {} - - # # ||||||||||||| _add_subsystem_guesses - # # Get all subsystems associated with the phase - # all_subsystems = prob._get_all_subsystems( - # prob.phase_info[phase_name]['external_subsystems']) - - # # Loop over each subsystem - # for subsystem in all_subsystems: - # # Fetch the initial guesses for the subsystem - # initial_guesses = subsystem.get_initial_guesses() - - # # Loop over each guess - # for key, val in initial_guesses.items(): - # # Identify the type of the guess (state or control) - # type = val.pop('type') - # if 'state' in type: - # path_string = 'states' - # elif 'control' in type: - # path_string = 'controls' - - # # Process the guess variable (handles array interpolation) - # val['val'] = prob._process_guess_var(val['val'], key, phase) - - # # Set the initial guess in the problem - # setvalprob.set_val(parent_prefix+ - # self.group_prefix + - # f'_{i}.traj.{phase_name}.{path_string}:{key}', **val) - - # # Set initial guesses for states and controls for each phase - - # # |||||||||||||||||||||| _add_guesses - # # If using the GASP model, set initial guesses for the rotation mass and flight duration - # if prob.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): - # control_keys = ["mach", "altitude"] - # state_keys = ["mass", Dynamic.Mission.DISTANCE] - # prob_keys = ["tau_gear", "tau_flaps"] - - # # for the simple mission method, use the provided initial and final mach and altitude values from phase_info - # if prob.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): - # initial_altitude = wrapped_convert_units( - # prob.phase_info[phase_name]['user_options'] - # ['initial_altitude'], - # 'ft') - # final_altitude = wrapped_convert_units( - # prob.phase_info[phase_name]['user_options']['final_altitude'], 'ft') - # initial_mach = prob.phase_info[phase_name]['user_options'][ - # 'initial_mach'] - # final_mach = prob.phase_info[phase_name]['user_options'][ - # 'final_mach'] - - # guesses["mach"] = ([initial_mach[0], final_mach[0]], "unitless") - # guesses["altitude"] = ([initial_altitude, final_altitude], 'ft') - - # if prob.mission_method is HEIGHT_ENERGY: - # # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds - # if 'time' not in guesses: - # initial_bounds = wrapped_convert_units( - # prob.phase_info[phase_name]['user_options']['initial_bounds'], 's') - # duration_bounds = wrapped_convert_units( - # prob.phase_info[phase_name]['user_options']['duration_bounds'], 's') - # guesses["time"] = ([np.mean(initial_bounds[0]), np.mean( - # duration_bounds[0])], 's') - - # # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds - # if 'time' not in guesses: - # initial_bounds = prob.phase_info[phase_name]['user_options'][ - # 'initial_bounds'] - # duration_bounds = prob.phase_info[phase_name]['user_options'][ - # 'duration_bounds'] - # # Add a check for the initial and duration bounds, raise an error if they are not consistent - # if initial_bounds[1] != duration_bounds[1]: - # raise ValueError( - # f"Initial and duration bounds for {phase_name} are not consistent.") - # guesses["time"] = ([np.mean(initial_bounds[0]), np.mean( - # duration_bounds[0])], initial_bounds[1]) - - # for guess_key, guess_data in guesses.items(): - # val, units = guess_data - - # # Set initial guess for time variables - # if 'time' == guess_key and prob.mission_method is not SOLVED_2DOF: - # setvalprob.set_val(parent_prefix+ - # self.group_prefix + f'_{i}.traj.{phase_name}.t_initial', - # val[0], - # units=units) - # setvalprob.set_val(parent_prefix+ - # self.group_prefix + f'_{i}.traj.{phase_name}.t_duration', - # val[1], - # units=units) - - # else: - # # Set initial guess for control variables - # if guess_key in control_keys: - # try: - # setvalprob.set_val(parent_prefix+self.group_prefix + - # f'_{i}.traj.{phase_name}.controls:{guess_key}', - # prob._process_guess_var( - # val, guess_key, phase), - # units=units) - # except KeyError: - # try: - # setvalprob.set_val(parent_prefix+ - # self.group_prefix + - # f'_{i}.traj.{phase_name}.polynomial_controls:{guess_key}', - # prob._process_guess_var(val, guess_key, phase), - # units=units) - # except KeyError: - # setvalprob.set_val(parent_prefix+ - # self.group_prefix + - # f'_{i}.traj.{phase_name}.bspline_controls:{guess_key}', - # prob._process_guess_var(val, guess_key, phase), - # units=units) - - # if guess_key in control_keys: - # pass - # # Set initial guess for state variables - # elif guess_key in state_keys: - # setvalprob.set_val(parent_prefix+self.group_prefix + - # f'_{i}.traj.{phase_name}.states:{guess_key}', - # prob._process_guess_var( - # val, guess_key, phase), - # units=units) - # elif guess_key in prob_keys: - # setvalprob.set_val(parent_prefix+ - # self.group_prefix+f'_{i}.'+guess_key, val, units=units) - # elif ":" in guess_key: - # setvalprob.set_val(parent_prefix+ - # self.group_prefix + f'_{i}.traj.{phase_name}.{guess_key}', - # prob._process_guess_var(val, guess_key, phase), - # units=units) - # else: - # # raise error if the guess key is not recognized - # raise ValueError( - # f"Initial guess key {guess_key} in {phase_name} is not recognized.") - - # # We need some special logic for these following variables because GASP computes - # # initial guesses using some knowledge of the mission duration and other variables - # # that are only available after calling `create_vehicle`. Thus these initial guess - # # values are not included in the `phase_info` object. - - # base_phase = phase_name - # if 'mass' not in guesses: - # mass_guess = prob.aviary_inputs.get_val( - # Mission.Design.GROSS_MASS, units='lbm') - # # Set the mass guess as the initial value for the mass state variable - # setvalprob.set_val(parent_prefix+self.group_prefix+f'_{i}.traj.{phase_name}.states:mass', - # mass_guess, units='lbm') - - # # if 'time' not in guesses: - # # # Determine initial time and duration guesses depending on the phase name - # # if 'desc1' == base_phase: - # # t_initial = flight_duration*.9 - # # t_duration = flight_duration*.04 - # # elif 'desc2' in base_phase: - # # t_initial = flight_duration*.94 - # # t_duration = 5000 - # # # Set the time guesses as the initial values for the time-related trajectory variables - # # setvalprob.set_val(parent_prefix+f"traj.{phase_name}.t_initial", - # # t_initial, units='s') - # # setvalprob.set_val(parent_prefix+f"traj.{phase_name}.t_duration", - # # t_duration, units='s') - - -# ========================================================================= old code - # super_prob = om.Problem() - # num_missions = len(weights) - # probs = [] - # prefix = "problem_" - - # makeN2 = False - # if len(sys.argv) > 1: - # if "n2" in sys.argv: - # makeN2 = True - - # # define individual aviary problems - # for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): - # prob = av.AviaryProblem() - # prob.load_inputs(plane, phase_info) - # prob.check_and_preprocess_inputs() - # prob.add_pre_mission_systems() - # traj = prob.add_phases() # save dymos traj to add to super problem as a subsystem - # prob.add_post_mission_systems() - # prob.link_phases() # this is half working / connect statements from outside of traj to inside are failing - # prob.problem_type = ProblemType.ALTERNATE # adds summary gross mass as design var - # prob.add_design_variables() - # probs.append(prob) - - # group = om.Group() # this group will contain all the promoted aviary vars - # group.add_subsystem("pre", prob.pre_mission) - # group.add_subsystem("traj", traj) - # group.add_subsystem("post", prob.post_mission) - - # # setting defaults for these variables to suppress errors - # longlst = [ - # 'mission:summary:gross_mass', 'aircraft:wing:sweep', - # 'aircraft:wing:thickness_to_chord', 'aircraft:wing:area', - # 'aircraft:wing:taper_ratio', 'mission:design:gross_mass'] - # for var in longlst: - # group.set_input_defaults( - # var, val=MetaData[var]['default_value'], - # units=MetaData[var]['units']) - - # # add group and promote design gross mass (common input amongst multiple missions) - # # in this way it represents the MTOW - # super_prob.model.add_subsystem(prefix+f'{i}', group, promotes=[ - # 'mission:design:gross_mass']) - - # # add design gross mass as a design var - # super_prob.model.add_design_var( - # 'mission:design:gross_mass', lower=100e3, upper=1000e3) - - # for i in range(num_missions): - # # connecting each subcomponent's fuel burn to super problem's unique fuel variables - # super_prob.model.connect( - # prefix+f"{i}.mission:summary:fuel_burned", f"fuel_{i}") - - # # create constraint to force each mission's summary gross mass to not - # # exceed the common mission design gross mass (aka MTOW) - # super_prob.model.add_subsystem(f'MTOW_constraint{i}', om.ExecComp( - # 'mtow_resid = design_gross_mass - summary_gross_mass'), - # promotes=[('summary_gross_mass', prefix+f'{i}.mission:summary:gross_mass'), - # ('design_gross_mass', 'mission:design:gross_mass')]) - - # super_prob.model.add_constraint(f'MTOW_constraint{i}.mtow_resid', lower=0.) - - # # creating variable strings that will represent fuel burn from each mission - # fuel_burned_vars = [f"fuel_{i}" for i in range(num_missions)] - # weighted_str = "+".join([f"{fuel}*{weight}" - # for fuel, weight in zip(fuel_burned_vars, weights)]) - # # weighted_str looks like: fuel_0 * weight[0] + fuel_1 * weight[1] - - # # adding compound execComp to super problem - # super_prob.model.add_subsystem('compound_fuel_burn_objective', om.ExecComp( - # "compound = "+weighted_str), promotes=["compound", *fuel_burned_vars]) - - # super_prob.driver = om.ScipyOptimizeDriver() - # super_prob.driver.options['optimizer'] = 'SLSQP' - # super_prob.model.add_objective('compound') # output from execcomp goes here - - # with warnings.catch_warnings(): - # warnings.simplefilter("ignore", om.OpenMDAOWarning) - # warnings.simplefilter("ignore", om.PromotionWarning) - # super_prob.setup() - - # if makeN2: - # om.n2(super_prob, outfile="multi_mission_importTraj_N2.html") # create N2 diagram - - # # cannot use this b/c initial guesses (i.e. setval func) has to be called on super prob level - # # for prob in probs: - # # # prob.setup() - # # prob.set_initial_guesses() - - # # dm.run_problem(super_prob) - - -""" -Ferry mission phase info: -Times (min): 0, 50, 812, 843 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 7001 nmi -Notes: 32k in 30 mins too fast for aviary, climb to low alt then slow rise through cruise - -Intermediate mission phase info: -Times (min): 0, 50, 560, 590 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 4839 nmi - -Max Payload mission phase info: -Times (min): 0, 50, 260, 290 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 2272 nmi - -Hard to find multiple payload/range values for FwFm (737), so use C-5 instead -Based on: - https://en.wikipedia.org/wiki/Lockheed_C-5_Galaxy#Specifications_(C-5M), - https://www.af.mil/About-Us/Fact-Sheets/Display/Article/1529718/c-5-abc-galaxy-and-c-5m-super-galaxy/ - -MTOW: 840,000 lb -Max Payload: 281,000 lb -Max Fuel: 341,446 lb -Empty Weight: 380,000 lb -> leaves 460,000 lb for fuel+payload (max fuel + max payload = 622,446 lb) - -Payload/range: - 281,000 lb payload -> 2,150 nmi range (AF.mil) [max payload case] - 120,000 lb payload -> 4,800 nmi range (AF.mil) [intermediate case] - 0 lb payload -> 7,000 nmi range (AF.mil) [ferry case] - -Flight characteristics: - Cruise at M0.77 at 33k ft - Max rate of climb: 2100 ft/min -""" - - -""" -input disconnected error: -WARNING: The following inputs are not connected: - group_0.aircraft:air_conditioning:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.AC.aircraft:air_conditioning:mass_scaler) - group_0.aircraft:anti_icing:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.anti_icing.aircraft:anti_icing:mass_scaler) - group_0.aircraft:apu:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.apu.aircraft:apu:mass_scaler) - group_0.aircraft:avionics:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.avionics.aircraft:avionics:mass_scaler) - group_0.aircraft:canard:area (group_0.pre_mission.core_subsystems.core_geometry.canard.aircraft:canard:area) - group_0.aircraft:canard:area (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:canard:area) - group_0.aircraft:canard:area (group_0.pre_mission.core_subsystems.core_mass.canard.aircraft:canard:area) - group_0.aircraft:canard:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:canard:aspect_ratio) - group_0.aircraft:canard:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.canard.aircraft:canard:mass_scaler) - group_0.aircraft:canard:taper_ratio (group_0.pre_mission.core_subsystems.core_mass.canard.aircraft:canard:taper_ratio) - group_0.aircraft:canard:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.canard.aircraft:canard:thickness_to_chord) - group_0.aircraft:canard:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:canard:thickness_to_chord) - group_0.aircraft:canard:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.canard.aircraft:canard:wetted_area_scaler) - group_0.aircraft:crew_and_payload:cargo_container_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.cargo_containers.aircraft:crew_and_payload:cargo_container_mass_scaler) - group_0.aircraft:crew_and_payload:cargo_mass (group_0.pre_mission.core_subsystems.core_mass.cargo_containers.aircraft:crew_and_payload:cargo_mass) - group_0.aircraft:crew_and_payload:cargo_mass (group_0.pre_mission.core_subsystems.core_mass.total_mass.zero_fuel_mass.aircraft:crew_and_payload:cargo_mass) - group_0.aircraft:crew_and_payload:flight_crew_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.flight_crew.aircraft:crew_and_payload:flight_crew_mass_scaler) - group_0.aircraft:crew_and_payload:misc_cargo (group_0.pre_mission.core_subsystems.core_mass.cargo.aircraft:crew_and_payload:misc_cargo) - group_0.aircraft:crew_and_payload:non_flight_crew_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.nonflight_crew.aircraft:crew_and_payload:non_flight_crew_mass_scaler) - group_0.aircraft:crew_and_payload:passenger_service_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.pass_service.aircraft:crew_and_payload:passenger_service_mass_scaler) - group_0.aircraft:crew_and_payload:wing_cargo (group_0.pre_mission.core_subsystems.core_mass.cargo.aircraft:crew_and_payload:wing_cargo) - group_0.aircraft:design:base_area (group_0.traj.param_comp.parameters:aircraft:design:base_area) - group_0.aircraft:design:empty_mass_margin_scaler (group_0.pre_mission.core_subsystems.core_mass.total_mass.empty_mass_margin.aircraft:design:empty_mass_margin_scaler) - group_0.aircraft:design:external_subsystems_mass (group_0.pre_mission.core_subsystems.core_mass.total_mass.system_equip_mass.aircraft:design:external_subsystems_mass) - group_0.aircraft:design:lift_dependent_drag_coeff_factor (group_0.traj.param_comp.parameters:aircraft:design:lift_dependent_drag_coeff_factor) - group_0.aircraft:design:reserve_fuel_additional (group_0.post_mission.reserve_fuel.reserve_fuel_additional) - group_0.aircraft:design:subsonic_drag_coeff_factor (group_0.traj.param_comp.parameters:aircraft:design:subsonic_drag_coeff_factor) - group_0.aircraft:design:supersonic_drag_coeff_factor (group_0.traj.param_comp.parameters:aircraft:design:supersonic_drag_coeff_factor) - group_0.aircraft:design:zero_lift_drag_coeff_factor (group_0.traj.param_comp.parameters:aircraft:design:zero_lift_drag_coeff_factor) - group_0.aircraft:electrical:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.electrical.aircraft:electrical:mass_scaler) - group_0.aircraft:engine:mass (group_0.pre_mission.core_subsystems.core_mass.wing_group.engine_pod_mass.aircraft:engine:mass) - group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_propulsion.CF6.aircraft:engine:scaled_sls_thrust) - group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_propulsion.propulsion_sum.aircraft:engine:scaled_sls_thrust) - group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_subsystems.core_mass.engine_mass.aircraft:engine:scaled_sls_thrust) - group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_subsystems.core_mass.nacelle.aircraft:engine:scaled_sls_thrust) - group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_subsystems.core_mass.thrust_rev.aircraft:engine:scaled_sls_thrust) - group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_subsystems.core_mass.wing_group.engine_pod_mass.aircraft:engine:scaled_sls_thrust) - group_0.aircraft:engine:thrust_reversers_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.thrust_rev.aircraft:engine:thrust_reversers_mass_scaler) - group_0.aircraft:engine:wing_locations (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:engine:wing_locations) - group_0.aircraft:engine:wing_locations (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:engine:wing_locations) - group_0.aircraft:fins:area (group_0.pre_mission.core_subsystems.core_mass.fin.aircraft:fins:area) - group_0.aircraft:fins:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.fin.aircraft:fins:mass_scaler) - group_0.aircraft:fins:taper_ratio (group_0.pre_mission.core_subsystems.core_mass.fin.aircraft:fins:taper_ratio) - group_0.aircraft:fuel:auxiliary_fuel_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.total_fuel_capacity.aircraft:fuel:auxiliary_fuel_capacity) - group_0.aircraft:fuel:capacity_factor (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:capacity_factor) - group_0.aircraft:fuel:density_ratio (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:density_ratio) - group_0.aircraft:fuel:density_ratio (group_0.pre_mission.core_subsystems.core_mass.unusable_fuel.aircraft:fuel:density_ratio) - group_0.aircraft:fuel:fuel_margin (group_0.post_mission.fuel_calc.fuel_margin) - group_0.aircraft:fuel:fuel_system_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.fuel_system.aircraft:fuel:fuel_system_mass_scaler) - group_0.aircraft:fuel:fuselage_fuel_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.auxiliary_fuel_capacity.aircraft:fuel:fuselage_fuel_capacity) - group_0.aircraft:fuel:fuselage_fuel_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.total_fuel_capacity.aircraft:fuel:fuselage_fuel_capacity) - group_0.aircraft:fuel:total_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.auxiliary_fuel_capacity.aircraft:fuel:total_capacity) - group_0.aircraft:fuel:total_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.fuselage_fuel_capacity.aircraft:fuel:total_capacity) - group_0.aircraft:fuel:total_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_system.aircraft:fuel:total_capacity) - group_0.aircraft:fuel:total_capacity (group_0.pre_mission.core_subsystems.core_mass.unusable_fuel.aircraft:fuel:total_capacity) - group_0.aircraft:fuel:unusable_fuel_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.unusable_fuel.aircraft:fuel:unusable_fuel_mass_scaler) - group_0.aircraft:fuel:wing_ref_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:wing_ref_capacity) - group_0.aircraft:fuel:wing_ref_capacity_area (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:wing_ref_capacity_area) - group_0.aircraft:fuel:wing_ref_capacity_term_A (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:wing_ref_capacity_term_A) - group_0.aircraft:fuel:wing_ref_capacity_term_B (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:wing_ref_capacity_term_B) - group_0.aircraft:furnishings:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.furnishings.aircraft:furnishings:mass_scaler) - group_0.aircraft:fuselage:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:fuselage:laminar_flow_lower) - group_0.aircraft:fuselage:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:fuselage:laminar_flow_upper) - group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:fuselage:length) - group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:fuselage:length) - group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_geometry.fuselage_prelim.aircraft:fuselage:length) - group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_mass.electrical.aircraft:fuselage:length) - group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_mass.fuselage.aircraft:fuselage:length) - group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:fuselage:length) - group_0.aircraft:fuselage:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.fuselage.aircraft:fuselage:mass_scaler) - group_0.aircraft:fuselage:max_height (group_0.pre_mission.core_subsystems.core_geometry.fuselage_prelim.aircraft:fuselage:max_height) - group_0.aircraft:fuselage:max_height (group_0.pre_mission.core_subsystems.core_mass.AC.aircraft:fuselage:max_height) - group_0.aircraft:fuselage:max_height (group_0.pre_mission.core_subsystems.core_mass.furnishings.aircraft:fuselage:max_height) - group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_geometry.fuselage_prelim.aircraft:fuselage:max_width) - group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:fuselage:max_width) - group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_mass.anti_icing.aircraft:fuselage:max_width) - group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_mass.electrical.aircraft:fuselage:max_width) - group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_mass.furnishings.aircraft:fuselage:max_width) - group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:fuselage:max_width) - group_0.aircraft:fuselage:passenger_compartment_length (group_0.pre_mission.core_subsystems.core_mass.furnishings.aircraft:fuselage:passenger_compartment_length) - group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.AC.aircraft:fuselage:planform_area) - group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.apu.aircraft:fuselage:planform_area) - group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.avionics.aircraft:fuselage:planform_area) - group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.hydraulics.aircraft:fuselage:planform_area) - group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.instruments.aircraft:fuselage:planform_area) - group_0.aircraft:fuselage:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:fuselage:wetted_area_scaler) - group_0.aircraft:horizontal_tail:area (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:horizontal_tail:area) - group_0.aircraft:horizontal_tail:area (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:horizontal_tail:area) - group_0.aircraft:horizontal_tail:area (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:horizontal_tail:area) - group_0.aircraft:horizontal_tail:area (group_0.pre_mission.core_subsystems.core_mass.htail.aircraft:horizontal_tail:area) - group_0.aircraft:horizontal_tail:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:horizontal_tail:aspect_ratio) - group_0.aircraft:horizontal_tail:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:horizontal_tail:aspect_ratio) - group_0.aircraft:horizontal_tail:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:horizontal_tail:laminar_flow_lower) - group_0.aircraft:horizontal_tail:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:horizontal_tail:laminar_flow_upper) - group_0.aircraft:horizontal_tail:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.htail.aircraft:horizontal_tail:mass_scaler) - group_0.aircraft:horizontal_tail:taper_ratio (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:horizontal_tail:taper_ratio) - group_0.aircraft:horizontal_tail:taper_ratio (group_0.pre_mission.core_subsystems.core_mass.htail.aircraft:horizontal_tail:taper_ratio) - group_0.aircraft:horizontal_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:horizontal_tail:thickness_to_chord) - group_0.aircraft:horizontal_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:horizontal_tail:thickness_to_chord) - group_0.aircraft:horizontal_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:horizontal_tail:thickness_to_chord) - group_0.aircraft:horizontal_tail:vertical_tail_fraction (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:horizontal_tail:vertical_tail_fraction) - group_0.aircraft:horizontal_tail:vertical_tail_fraction (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:horizontal_tail:vertical_tail_fraction) - group_0.aircraft:horizontal_tail:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:horizontal_tail:wetted_area_scaler) - group_0.aircraft:hydraulics:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.hydraulics.aircraft:hydraulics:mass_scaler) - group_0.aircraft:hydraulics:system_pressure (group_0.pre_mission.core_subsystems.core_mass.hydraulics.aircraft:hydraulics:system_pressure) - group_0.aircraft:instruments:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.instruments.aircraft:instruments:mass_scaler) - group_0.aircraft:landing_gear:main_gear_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.landing_group.landing_gear.aircraft:landing_gear:main_gear_mass_scaler) - group_0.aircraft:landing_gear:nose_gear_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.landing_group.landing_gear.aircraft:landing_gear:nose_gear_mass_scaler) - group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:nacelle:avg_diameter) - group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_geometry.nacelles.aircraft:nacelle:avg_diameter) - group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_mass.anti_icing.aircraft:nacelle:avg_diameter) - group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:nacelle:avg_diameter) - group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_mass.nacelle.aircraft:nacelle:avg_diameter) - group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_mass.starter.aircraft:nacelle:avg_diameter) - group_0.aircraft:nacelle:avg_length (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:nacelle:avg_length) - group_0.aircraft:nacelle:avg_length (group_0.pre_mission.core_subsystems.core_geometry.nacelles.aircraft:nacelle:avg_length) - group_0.aircraft:nacelle:avg_length (group_0.pre_mission.core_subsystems.core_mass.nacelle.aircraft:nacelle:avg_length) - group_0.aircraft:nacelle:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:nacelle:laminar_flow_lower) - group_0.aircraft:nacelle:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:nacelle:laminar_flow_upper) - group_0.aircraft:nacelle:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.nacelle.aircraft:nacelle:mass_scaler) - group_0.aircraft:nacelle:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.nacelles.aircraft:nacelle:wetted_area_scaler) - group_0.aircraft:paint:mass_per_unit_area (group_0.pre_mission.core_subsystems.core_mass.paint.aircraft:paint:mass_per_unit_area) - group_0.aircraft:propulsion:engine_oil_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.engine_oil.aircraft:propulsion:engine_oil_mass_scaler) - group_0.aircraft:propulsion:misc_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.misc_engine.aircraft:propulsion:misc_mass_scaler) - group_0.aircraft:vertical_tail:area (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:vertical_tail:area) - group_0.aircraft:vertical_tail:area (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:vertical_tail:area) - group_0.aircraft:vertical_tail:area (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:vertical_tail:area) - group_0.aircraft:vertical_tail:area (group_0.pre_mission.core_subsystems.core_mass.vert_tail.aircraft:vertical_tail:area) - group_0.aircraft:vertical_tail:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:vertical_tail:aspect_ratio) - group_0.aircraft:vertical_tail:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:vertical_tail:aspect_ratio) - group_0.aircraft:vertical_tail:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:vertical_tail:laminar_flow_lower) - group_0.aircraft:vertical_tail:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:vertical_tail:laminar_flow_upper) - group_0.aircraft:vertical_tail:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.vert_tail.aircraft:vertical_tail:mass_scaler) - group_0.aircraft:vertical_tail:taper_ratio (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:vertical_tail:taper_ratio) - group_0.aircraft:vertical_tail:taper_ratio (group_0.pre_mission.core_subsystems.core_mass.vert_tail.aircraft:vertical_tail:taper_ratio) - group_0.aircraft:vertical_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:vertical_tail:thickness_to_chord) - group_0.aircraft:vertical_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:vertical_tail:thickness_to_chord) - group_0.aircraft:vertical_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:vertical_tail:thickness_to_chord) - group_0.aircraft:vertical_tail:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:vertical_tail:wetted_area_scaler) - group_0.aircraft:wing:aeroelastic_tailoring_factor (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:aeroelastic_tailoring_factor) - group_0.aircraft:wing:aeroelastic_tailoring_factor (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:aeroelastic_tailoring_factor) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.wing.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.wing_prelim.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.hydraulics.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.surf_ctrl.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.unusable_fuel.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_misc.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.traj.param_comp.parameters:aircraft:wing:area) - group_0.aircraft:wing:aspect_ratio (group_0.pre_mission.core_subsystems.core_aerodynamics.design.aircraft:wing:aspect_ratio) - group_0.aircraft:wing:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:wing:aspect_ratio) - group_0.aircraft:wing:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:wing:aspect_ratio) - group_0.aircraft:wing:aspect_ratio (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:aspect_ratio) - group_0.aircraft:wing:aspect_ratio (group_0.traj.param_comp.parameters:aircraft:wing:aspect_ratio) - group_0.aircraft:wing:aspect_ratio_reference (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:aspect_ratio_reference) - group_0.aircraft:wing:bending_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:bending_mass_scaler) - group_0.aircraft:wing:bwb_aft_body_mass (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_total.aircraft:wing:bwb_aft_body_mass) - group_0.aircraft:wing:chord_per_semispan (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:chord_per_semispan) - group_0.aircraft:wing:composite_fraction (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:composite_fraction) - group_0.aircraft:wing:composite_fraction (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_misc.aircraft:wing:composite_fraction) - group_0.aircraft:wing:composite_fraction (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_shear_control.aircraft:wing:composite_fraction) - group_0.aircraft:wing:control_surface_area (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_shear_control.aircraft:wing:control_surface_area) - group_0.aircraft:wing:control_surface_area_ratio (group_0.pre_mission.core_subsystems.core_mass.surf_ctrl.aircraft:wing:control_surface_area_ratio) - group_0.aircraft:wing:dihedral (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:wing:dihedral) - group_0.aircraft:wing:glove_and_bat (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:wing:glove_and_bat) - group_0.aircraft:wing:glove_and_bat (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:wing:glove_and_bat) - group_0.aircraft:wing:glove_and_bat (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:wing:glove_and_bat) - group_0.aircraft:wing:glove_and_bat (group_0.pre_mission.core_subsystems.core_geometry.wing_prelim.aircraft:wing:glove_and_bat) - group_0.aircraft:wing:incidence (group_0.traj.param_comp.parameters:aircraft:wing:incidence) - group_0.aircraft:wing:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:wing:laminar_flow_lower) - group_0.aircraft:wing:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:wing:laminar_flow_upper) - group_0.aircraft:wing:load_fraction (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:load_fraction) - group_0.aircraft:wing:load_path_sweep_dist (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:load_path_sweep_dist) - group_0.aircraft:wing:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_total.aircraft:wing:mass_scaler) - group_0.aircraft:wing:max_camber_at_70_semispan (group_0.pre_mission.core_subsystems.core_aerodynamics.design.aircraft:wing:max_camber_at_70_semispan) - group_0.aircraft:wing:max_camber_at_70_semispan (group_0.traj.param_comp.parameters:aircraft:wing:max_camber_at_70_semispan) - group_0.aircraft:wing:misc_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:misc_mass_scaler) - group_0.aircraft:wing:misc_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_misc.aircraft:wing:misc_mass_scaler) - group_0.aircraft:wing:shear_control_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:shear_control_mass_scaler) - group_0.aircraft:wing:shear_control_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_shear_control.aircraft:wing:shear_control_mass_scaler) - group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:wing:span) - group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_geometry.wing_prelim.aircraft:wing:span) - group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_mass.anti_icing.aircraft:wing:span) - group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:wing:span) - group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:wing:span) - group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:span) -""" From d5d92b19d8144cceece4f497e1fe825ed1ee833f Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Tue, 6 Aug 2024 10:39:28 -0400 Subject: [PATCH 033/113] updated to use problem type alternate for gtow constraints --- multi_aviary_copymodel.py | 4 +++- test_single_aviary.py | 2 ++ 2 files changed, 5 insertions(+), 1 deletion(-) diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index 40ea1ad61..67cb3cbce 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -17,6 +17,7 @@ from easy_phase_info_inter import phase_info as easy_inter from easy_phase_info_max import phase_info as easy_max from aviary.variable_info.variables import Mission, Aircraft +from aviary.variable_info.enums import ProblemType # "comp?.a can be used to reference multiple comp1.a comp2.a etc" @@ -50,12 +51,13 @@ def __init__(self, planes, phase_infos, weights): prob.add_phases() prob.add_post_mission_systems() prob.link_phases() + prob.problem_type = ProblemType.ALTERNATE prob.add_design_variables() # should not work at super prob level self.probs.append(prob) self.model.add_subsystem( self.group_prefix + f'_{i}', prob.model, - promotes=['mission:design:gross_mass']) + promotes=[Mission.Design.GROSS_MASS]) def add_design_variables(self): self.model.add_design_var('mission:design:gross_mass', lower=10., upper=900e3) diff --git a/test_single_aviary.py b/test_single_aviary.py index 82406d682..10acfeeac 100644 --- a/test_single_aviary.py +++ b/test_single_aviary.py @@ -1,6 +1,8 @@ import aviary.api as av from easy_phase_info_max import phase_info as max_phase_info from easy_phase_info_inter import phase_info as inter_phase_info +# from c5_models.c5_maxpayload_phase_info import phase_info as max_phase_info +# from c5_models.c5_intermediate_phase_info import phase_info as inter_phase_info from aviary.variable_info.variables import Mission, Aircraft From 468f39b6677518b0bf96d8c8aeadd724c34bfce8 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Tue, 6 Aug 2024 10:53:47 -0400 Subject: [PATCH 034/113] remove scaling from flight_phase_builder b/c not needed --- aviary/mission/flight_phase_builder.py | 4 ++-- multi_aviary_copymodel.py | 9 ++++++--- 2 files changed, 8 insertions(+), 5 deletions(-) diff --git a/aviary/mission/flight_phase_builder.py b/aviary/mission/flight_phase_builder.py index b7f4e3b9e..17027fbeb 100644 --- a/aviary/mission/flight_phase_builder.py +++ b/aviary/mission/flight_phase_builder.py @@ -121,7 +121,7 @@ def build_phase(self, aviary_options: AviaryValues = None, phase_type=EquationsO phase.add_state( Dynamic.Mission.MASS, fix_initial=fix_initial_mass, fix_final=False, - lower=0.0, ref=1e4, defect_ref=1e4, units='kg', + lower=0.0, ref=1e4, defect_ref=1e6, units='kg', rate_source=rate_source, targets=Dynamic.Mission.MASS, input_initial=input_initial_mass, @@ -133,7 +133,7 @@ def build_phase(self, aviary_options: AviaryValues = None, phase_type=EquationsO fix_initial, Dynamic.Mission.DISTANCE, True) phase.add_state( Dynamic.Mission.DISTANCE, fix_initial=fix_initial_distance, fix_final=False, - lower=0.0, ref=1e6, defect_ref=1e6, units='m', + lower=0.0, ref=1e6, defect_ref=1e8, units='m', rate_source=Dynamic.Mission.DISTANCE_RATE, input_initial=input_initial_distance, solve_segments='forward' if solve_for_distance else None, diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index 656bd9703..63b147663 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -71,8 +71,8 @@ def add_driver(self): # set coloring at this value. 1e-45 didn't seem to make much difference self.driver.declare_coloring(tol=1e-25, orders=None) self.driver.opt_settings["Major iterations limit"] = 60 - self.driver.opt_settings["Major optimality tolerance"] = 5e-4 - self.driver.opt_settings["Major feasibility tolerance"] = 4e-5 + self.driver.opt_settings["Major optimality tolerance"] = 1e-6 + self.driver.opt_settings["Major feasibility tolerance"] = 1e-6 self.driver.opt_settings["iSumm"] = 6 self.driver.opt_settings['Verify level'] = -1 # self.driver.options['maxiter'] = 1e3 @@ -102,7 +102,7 @@ def add_objective(self): # connecting each subcomponent's fuel burn to super problem's unique fuel variables self.model.connect( self.group_prefix+f"_{i}.{Mission.Objectives.FUEL}", f"fuel_{i}") - self.model.add_objective('compound', ref=1e4) + self.model.add_objective('compound', ref=1) def setup_wrapper(self): """Wrapper for om.Problem setup with warning ignoring and setting options""" @@ -160,3 +160,6 @@ def run(self): print("Fuel burned") print(super_prob.get_val(f'group_0.{Mission.Summary.FUEL_BURNED}')) print(super_prob.get_val(f'group_1.{Mission.Summary.FUEL_BURNED}')) + print("Summary Gross Mass") + print(super_prob.get_val(f'group_0.{Mission.Summary.GROSS_MASS}')) + print(super_prob.get_val(f'group_1.{Mission.Summary.GROSS_MASS}')) From ec63557f80790d26cf1df32a0ddff5902035557f Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Tue, 6 Aug 2024 14:07:47 -0400 Subject: [PATCH 035/113] modification to mission.summary.range and mission.design.range to make sure both aircraft for each mission are designed the same. Previously avionics and landing gear were calculated based on different ranges which caused different masses of 184lb. Current mass from new results is exatly the same. Methods for level2 has residual errors based on removing mission.summary.range and replacing with actual_range. --- aviary/interface/methods_for_level2.py | 12 ++++++------ aviary/variable_info/variable_meta_data.py | 3 ++- multi_aviary_copymodel.py | 21 +++++++++++++-------- 3 files changed, 21 insertions(+), 15 deletions(-) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index 3f859fcdd..0a056f1ad 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -367,14 +367,14 @@ def load_inputs( ['actual_takeoff_mass'], units='lbm') if 'target_range' in self.post_mission_info: - aviary_inputs.set_val(Mission.Design.RANGE, wrapped_convert_units( + aviary_inputs.set_val(Mission.Summary.RANGE, wrapped_convert_units( phase_info['post_mission']['target_range'], 'NM'), units='NM') self.require_range_residual = True else: self.require_range_residual = False self.target_range = aviary_inputs.get_val( - Mission.Design.RANGE, units='NM') + Mission.Summary.RANGE, units='NM') return aviary_inputs @@ -1446,7 +1446,7 @@ def link_phases(self): connected=true_unless_mpi) self.model.connect(f'traj.{self.regular_phases[-1]}.timeseries.distance', - Mission.Summary.RANGE, + 'actual_range', src_indices=[-1], flat_src_indices=True) elif self.mission_method is SOLVED_2DOF: @@ -2472,7 +2472,7 @@ def _add_objectives(self): "val": self.target_range, "units": "NM"}, ), promotes_inputs=[ - ("actual_range", Mission.Summary.RANGE), + "actual_range", ("ascent_duration", Mission.Takeoff.ASCENT_DURATION), ], promotes_outputs=[("reg_objective", Mission.Objectives.RANGE)], @@ -2487,8 +2487,8 @@ def _add_objectives(self): range_resid={"val": 30, "units": "NM"}, ), promotes_inputs=[ - ("actual_range", Mission.Summary.RANGE), - ("target_range", Mission.Design.RANGE), + "actual_range", + ("target_range", Mission.Summary.RANGE), ], promotes_outputs=[ ("range_resid", Mission.Constraints.RANGE_RESIDUAL)], diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index 3459f1f37..e17f17509 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -3880,7 +3880,8 @@ "LEAPS1": 'aircraft.inputs.L0_overrides.landing_gear_main_weight' }, units='unitless', - desc='mass scaler of the main landing gear structure' + desc='mass scaler of the main landing gear structure', + default_value=1.0, ) add_meta_data( diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index 63b147663..6e3c45dbd 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -57,7 +57,7 @@ def __init__(self, planes, phase_infos, weights): self.model.add_subsystem( self.group_prefix + f'_{i}', prob.model, - promotes=['mission:design:gross_mass']) + promotes=['mission:design:gross_mass', 'mission:design:range']) def add_design_variables(self): self.model.add_design_var('mission:design:gross_mass', lower=10., upper=900e3) @@ -127,6 +127,14 @@ def run(self): # self.run_driver() dm.run_problem(self, make_plots=True) + def get_design_range(self, phase_infos): + design_range = 0 + for phase_info in phase_infos: + get_range = phase_info['post_mission']['target_range'][0] # TBD add units + if get_range > design_range: + design_range = get_range + return design_range + if __name__ == '__main__': makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False @@ -138,16 +146,12 @@ def run(self): super_prob.add_driver() super_prob.add_design_variables() super_prob.add_objective() + super_prob.model.set_input_defaults('mission:design:range', val=4000) super_prob.setup_wrapper() + super_prob.set_val('mission:design:range', super_prob.get_design_range(phase_infos)) for i, prob in enumerate(super_prob.probs): - super_prob.set_val( - super_prob.group_prefix + - f"_{i}.aircraft:design:landing_to_takeoff_mass_ratio", 0.5) prob.set_initial_guesses(super_prob, super_prob.group_prefix+f"_{i}.") - print(super_prob.get_val(super_prob.group_prefix + - f"_{i}.aircraft:design:landing_to_takeoff_mass_ratio")) - print(super_prob.get_val(super_prob.group_prefix + - f"_{i}.mission:summary:range")) + # super_prob.final_setup() if makeN2: from createN2 import createN2 @@ -163,3 +167,4 @@ def run(self): print("Summary Gross Mass") print(super_prob.get_val(f'group_0.{Mission.Summary.GROSS_MASS}')) print(super_prob.get_val(f'group_1.{Mission.Summary.GROSS_MASS}')) + # super_prob.model.group_1.list_vars(units=True, print_arrays=True) From a2226426045852e9245d3b4c8046054478dc2f89 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Tue, 6 Aug 2024 14:14:26 -0400 Subject: [PATCH 036/113] merge --- aviary/interface/methods_for_level2.py | 12 +- multi_aviary_copymodel.py | 558 ++----------------------- 2 files changed, 48 insertions(+), 522 deletions(-) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index 3f859fcdd..03c3622d4 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -367,14 +367,14 @@ def load_inputs( ['actual_takeoff_mass'], units='lbm') if 'target_range' in self.post_mission_info: - aviary_inputs.set_val(Mission.Design.RANGE, wrapped_convert_units( + aviary_inputs.set_val(Mission.Summary.RANGE, wrapped_convert_units( phase_info['post_mission']['target_range'], 'NM'), units='NM') self.require_range_residual = True else: self.require_range_residual = False self.target_range = aviary_inputs.get_val( - Mission.Design.RANGE, units='NM') + Mission.Summary.RANGE, units='NM') return aviary_inputs @@ -1446,7 +1446,7 @@ def link_phases(self): connected=true_unless_mpi) self.model.connect(f'traj.{self.regular_phases[-1]}.timeseries.distance', - Mission.Summary.RANGE, + "actual_range", src_indices=[-1], flat_src_indices=True) elif self.mission_method is SOLVED_2DOF: @@ -2472,7 +2472,7 @@ def _add_objectives(self): "val": self.target_range, "units": "NM"}, ), promotes_inputs=[ - ("actual_range", Mission.Summary.RANGE), + "actual_range", ("ascent_duration", Mission.Takeoff.ASCENT_DURATION), ], promotes_outputs=[("reg_objective", Mission.Objectives.RANGE)], @@ -2487,8 +2487,8 @@ def _add_objectives(self): range_resid={"val": 30, "units": "NM"}, ), promotes_inputs=[ - ("actual_range", Mission.Summary.RANGE), - ("target_range", Mission.Design.RANGE), + "actual_range", + ("target_range", Mission.Summary.RANGE), ], promotes_outputs=[ ("range_resid", Mission.Constraints.RANGE_RESIDUAL)], diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index 67cb3cbce..bbc794908 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -11,6 +11,7 @@ import openmdao.api as om import dymos as dm import numpy as np +import matplotlib.pyplot as plt from c5_models.c5_ferry_phase_info import phase_info as c5_ferry_phase_info from c5_models.c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info from c5_models.c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info @@ -18,6 +19,8 @@ from easy_phase_info_max import phase_info as easy_max from aviary.variable_info.variables import Mission, Aircraft from aviary.variable_info.enums import ProblemType +from openmdao.api import CaseReader + # "comp?.a can be used to reference multiple comp1.a comp2.a etc" @@ -57,7 +60,7 @@ def __init__(self, planes, phase_infos, weights): self.model.add_subsystem( self.group_prefix + f'_{i}', prob.model, - promotes=[Mission.Design.GROSS_MASS]) + promotes=[Mission.Design.GROSS_MASS, Mission.Design.RANGE]) def add_design_variables(self): self.model.add_design_var('mission:design:gross_mass', lower=10., upper=900e3) @@ -96,7 +99,7 @@ def add_objective(self): # connecting each subcomponent's fuel burn to super problem's unique fuel variables self.model.connect( self.group_prefix+f"_{i}.{Mission.Objectives.FUEL}", f"fuel_{i}") - self.model.add_objective('compound', ref=1e4) + self.model.add_objective('compound', ref=1) def setup_wrapper(self): """Wrapper for om.Problem setup with warning ignoring and setting options""" @@ -119,7 +122,7 @@ def run(self): self.model.set_solver_print(0) # self.run_driver() - dm.run_problem(self, make_plots=True) + dm.run_problem(self, solution_record_file='res.db') if __name__ == '__main__': @@ -127,6 +130,7 @@ def run(self): planes = ['c5_models/c5_maxpayload.csv', 'c5_models/c5_intermediate.csv'] # phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] phase_infos = [easy_max, easy_inter] + phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] weights = [1, 1] super_prob = MultiMissionProblem(planes, phase_infos, weights) super_prob.add_driver() @@ -149,14 +153,45 @@ def run(self): super_prob.run() outputs = {Mission.Summary.FUEL_BURNED: [], - Aircraft.Design.EMPTY_MASS: []} + Aircraft.Design.EMPTY_MASS: [], + Mission.Summary.GROSS_MASS: []} print("\n\n=========================\n") for key in outputs.keys(): - val1 = super_prob.get_val(f'group_0.{key}')[0] - val2 = super_prob.get_val(f'group_1.{key}')[0] + val1 = super_prob.get_val(f'group_0.{key}', units='lbm')[0] + val2 = super_prob.get_val(f'group_1.{key}', units='lbm')[0] print(f"Variable: {key}") - print(f"Values: {val1}, {val2}") + print(f"Values: {val1}, {val2} (lbm)") + + comps = ['vertical_tail', 'horizontal_tail', 'wing', 'fuselage'] + print("\nmass comparisons") + for comp in comps: + v1 = super_prob.get_val(f'group_0.aircraft:{comp}:mass') + v2 = super_prob.get_val(f'group_1.aircraft:{comp}:mass') + print(f'{comp}: {v1} vs. {v2}') + + sol = CaseReader('res.db').get_case('final') + # super_prob.model.list_vars() + # for i in range(2): + var = 'throttle' + t = np.concatenate([sol.get_val('group_0.traj.climb_1.t'), + sol.get_val('group_0.traj.climb_2.t'), + sol.get_val('group_0.traj.descent_1.t')]) + alt = np.concatenate([sol.get_val(f'group_0.traj.climb_1.timeseries.{var}'), + sol.get_val(f'group_0.traj.climb_2.timeseries.{var}'), + sol.get_val(f'group_0.traj.descent_1.timeseries.{var}')]) + t2 = np.concatenate([sol.get_val('group_1.traj.climb_1.t'), + sol.get_val('group_1.traj.climb_2.t'), + sol.get_val('group_1.traj.descent_1.t')]) + alt2 = np.concatenate([sol.get_val(f'group_1.traj.climb_1.timeseries.{var}'), + sol.get_val(f'group_1.traj.climb_2.timeseries.{var}'), + sol.get_val(f'group_1.traj.descent_1.timeseries.{var}')]) + plt.plot(t, alt, 'r*') + plt.plot(t2, alt2, 'b*') + plt.title(f"Time vs {var}") + plt.legend(['group_0', 'group_1']) + plt.grid() + plt.show() """ Variable: mission:summary:fuel_burned @@ -164,512 +199,3 @@ def run(self): Variable: aircraft:design:empty_mass Values: 336859.7179064408, 337047.85745526763 """ - -# def initvals(self): -# """attempting to copy over aviary code for setting initial values and changing references""" -# for i, prob in enumerate(self.probs): -# setvalprob.set_val(parent_prefix+self.group_prefix + -# f'_{i}.aircraft:design:landing_to_takeoff_mass_ratio', 0.5) -# # Grab the trajectory object from the model -# traj = prob.model.traj - -# # Determine which phases to loop over, fetching them from the trajectory -# phase_items = traj._phases.items() - -# # Loop over each phase and set initial guesses for the state and control variables -# for idx, (phase_name, phase) in enumerate(phase_items): -# # If not, fetch the initial guesses specific to the phase -# # check if guesses exist for this phase -# if "initial_guesses" in prob.phase_info[phase_name]: -# guesses = prob.phase_info[phase_name]['initial_guesses'] -# else: -# guesses = {} - -# # ||||||||||||| _add_subsystem_guesses -# # Get all subsystems associated with the phase -# all_subsystems = prob._get_all_subsystems( -# prob.phase_info[phase_name]['external_subsystems']) - -# # Loop over each subsystem -# for subsystem in all_subsystems: -# # Fetch the initial guesses for the subsystem -# initial_guesses = subsystem.get_initial_guesses() - -# # Loop over each guess -# for key, val in initial_guesses.items(): -# # Identify the type of the guess (state or control) -# type = val.pop('type') -# if 'state' in type: -# path_string = 'states' -# elif 'control' in type: -# path_string = 'controls' - -# # Process the guess variable (handles array interpolation) -# val['val'] = prob._process_guess_var(val['val'], key, phase) - -# # Set the initial guess in the problem -# setvalprob.set_val(parent_prefix+ -# self.group_prefix + -# f'_{i}.traj.{phase_name}.{path_string}:{key}', **val) - -# # Set initial guesses for states and controls for each phase - -# # |||||||||||||||||||||| _add_guesses -# # If using the GASP model, set initial guesses for the rotation mass and flight duration -# if prob.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): -# control_keys = ["mach", "altitude"] -# state_keys = ["mass", Dynamic.Mission.DISTANCE] -# prob_keys = ["tau_gear", "tau_flaps"] - -# # for the simple mission method, use the provided initial and final mach and altitude values from phase_info -# if prob.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF): -# initial_altitude = wrapped_convert_units( -# prob.phase_info[phase_name]['user_options'] -# ['initial_altitude'], -# 'ft') -# final_altitude = wrapped_convert_units( -# prob.phase_info[phase_name]['user_options']['final_altitude'], 'ft') -# initial_mach = prob.phase_info[phase_name]['user_options'][ -# 'initial_mach'] -# final_mach = prob.phase_info[phase_name]['user_options'][ -# 'final_mach'] - -# guesses["mach"] = ([initial_mach[0], final_mach[0]], "unitless") -# guesses["altitude"] = ([initial_altitude, final_altitude], 'ft') - -# if prob.mission_method is HEIGHT_ENERGY: -# # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds -# if 'time' not in guesses: -# initial_bounds = wrapped_convert_units( -# prob.phase_info[phase_name]['user_options']['initial_bounds'], 's') -# duration_bounds = wrapped_convert_units( -# prob.phase_info[phase_name]['user_options']['duration_bounds'], 's') -# guesses["time"] = ([np.mean(initial_bounds[0]), np.mean( -# duration_bounds[0])], 's') - -# # if time not in initial guesses, set it to the average of the initial_bounds and the duration_bounds -# if 'time' not in guesses: -# initial_bounds = prob.phase_info[phase_name]['user_options'][ -# 'initial_bounds'] -# duration_bounds = prob.phase_info[phase_name]['user_options'][ -# 'duration_bounds'] -# # Add a check for the initial and duration bounds, raise an error if they are not consistent -# if initial_bounds[1] != duration_bounds[1]: -# raise ValueError( -# f"Initial and duration bounds for {phase_name} are not consistent.") -# guesses["time"] = ([np.mean(initial_bounds[0]), np.mean( -# duration_bounds[0])], initial_bounds[1]) - -# for guess_key, guess_data in guesses.items(): -# val, units = guess_data - -# # Set initial guess for time variables -# if 'time' == guess_key and prob.mission_method is not SOLVED_2DOF: -# setvalprob.set_val(parent_prefix+ -# self.group_prefix + f'_{i}.traj.{phase_name}.t_initial', -# val[0], -# units=units) -# setvalprob.set_val(parent_prefix+ -# self.group_prefix + f'_{i}.traj.{phase_name}.t_duration', -# val[1], -# units=units) - -# else: -# # Set initial guess for control variables -# if guess_key in control_keys: -# try: -# setvalprob.set_val(parent_prefix+self.group_prefix + -# f'_{i}.traj.{phase_name}.controls:{guess_key}', -# prob._process_guess_var( -# val, guess_key, phase), -# units=units) -# except KeyError: -# try: -# setvalprob.set_val(parent_prefix+ -# self.group_prefix + -# f'_{i}.traj.{phase_name}.polynomial_controls:{guess_key}', -# prob._process_guess_var(val, guess_key, phase), -# units=units) -# except KeyError: -# setvalprob.set_val(parent_prefix+ -# self.group_prefix + -# f'_{i}.traj.{phase_name}.bspline_controls:{guess_key}', -# prob._process_guess_var(val, guess_key, phase), -# units=units) - -# if guess_key in control_keys: -# pass -# # Set initial guess for state variables -# elif guess_key in state_keys: -# setvalprob.set_val(parent_prefix+self.group_prefix + -# f'_{i}.traj.{phase_name}.states:{guess_key}', -# prob._process_guess_var( -# val, guess_key, phase), -# units=units) -# elif guess_key in prob_keys: -# setvalprob.set_val(parent_prefix+ -# self.group_prefix+f'_{i}.'+guess_key, val, units=units) -# elif ":" in guess_key: -# setvalprob.set_val(parent_prefix+ -# self.group_prefix + f'_{i}.traj.{phase_name}.{guess_key}', -# prob._process_guess_var(val, guess_key, phase), -# units=units) -# else: -# # raise error if the guess key is not recognized -# raise ValueError( -# f"Initial guess key {guess_key} in {phase_name} is not recognized.") - -# # We need some special logic for these following variables because GASP computes -# # initial guesses using some knowledge of the mission duration and other variables -# # that are only available after calling `create_vehicle`. Thus these initial guess -# # values are not included in the `phase_info` object. - -# base_phase = phase_name -# if 'mass' not in guesses: -# mass_guess = prob.aviary_inputs.get_val( -# Mission.Design.GROSS_MASS, units='lbm') -# # Set the mass guess as the initial value for the mass state variable -# setvalprob.set_val(parent_prefix+self.group_prefix+f'_{i}.traj.{phase_name}.states:mass', -# mass_guess, units='lbm') - -# # if 'time' not in guesses: -# # # Determine initial time and duration guesses depending on the phase name -# # if 'desc1' == base_phase: -# # t_initial = flight_duration*.9 -# # t_duration = flight_duration*.04 -# # elif 'desc2' in base_phase: -# # t_initial = flight_duration*.94 -# # t_duration = 5000 -# # # Set the time guesses as the initial values for the time-related trajectory variables -# # setvalprob.set_val(parent_prefix+f"traj.{phase_name}.t_initial", -# # t_initial, units='s') -# # setvalprob.set_val(parent_prefix+f"traj.{phase_name}.t_duration", -# # t_duration, units='s') - - -# ========================================================================= old code -# super_prob = om.Problem() -# num_missions = len(weights) -# probs = [] -# prefix = "problem_" - -# makeN2 = False -# if len(sys.argv) > 1: -# if "n2" in sys.argv: -# makeN2 = True - -# # define individual aviary problems -# for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): -# prob = av.AviaryProblem() -# prob.load_inputs(plane, phase_info) -# prob.check_and_preprocess_inputs() -# prob.add_pre_mission_systems() -# traj = prob.add_phases() # save dymos traj to add to super problem as a subsystem -# prob.add_post_mission_systems() -# prob.link_phases() # this is half working / connect statements from outside of traj to inside are failing -# prob.problem_type = ProblemType.ALTERNATE # adds summary gross mass as design var -# prob.add_design_variables() -# probs.append(prob) - -# group = om.Group() # this group will contain all the promoted aviary vars -# group.add_subsystem("pre", prob.pre_mission) -# group.add_subsystem("traj", traj) -# group.add_subsystem("post", prob.post_mission) - -# # setting defaults for these variables to suppress errors -# longlst = [ -# 'mission:summary:gross_mass', 'aircraft:wing:sweep', -# 'aircraft:wing:thickness_to_chord', 'aircraft:wing:area', -# 'aircraft:wing:taper_ratio', 'mission:design:gross_mass'] -# for var in longlst: -# group.set_input_defaults( -# var, val=MetaData[var]['default_value'], -# units=MetaData[var]['units']) - -# # add group and promote design gross mass (common input amongst multiple missions) -# # in this way it represents the MTOW -# super_prob.model.add_subsystem(prefix+f'{i}', group, promotes=[ -# 'mission:design:gross_mass']) - -# # add design gross mass as a design var -# super_prob.model.add_design_var( -# 'mission:design:gross_mass', lower=100e3, upper=1000e3) - -# for i in range(num_missions): -# # connecting each subcomponent's fuel burn to super problem's unique fuel variables -# super_prob.model.connect( -# prefix+f"{i}.mission:summary:fuel_burned", f"fuel_{i}") - -# # create constraint to force each mission's summary gross mass to not -# # exceed the common mission design gross mass (aka MTOW) -# super_prob.model.add_subsystem(f'MTOW_constraint{i}', om.ExecComp( -# 'mtow_resid = design_gross_mass - summary_gross_mass'), -# promotes=[('summary_gross_mass', prefix+f'{i}.mission:summary:gross_mass'), -# ('design_gross_mass', 'mission:design:gross_mass')]) - -# super_prob.model.add_constraint(f'MTOW_constraint{i}.mtow_resid', lower=0.) - -# # creating variable strings that will represent fuel burn from each mission -# fuel_burned_vars = [f"fuel_{i}" for i in range(num_missions)] -# weighted_str = "+".join([f"{fuel}*{weight}" -# for fuel, weight in zip(fuel_burned_vars, weights)]) -# # weighted_str looks like: fuel_0 * weight[0] + fuel_1 * weight[1] - -# # adding compound execComp to super problem -# super_prob.model.add_subsystem('compound_fuel_burn_objective', om.ExecComp( -# "compound = "+weighted_str), promotes=["compound", *fuel_burned_vars]) - -# super_prob.driver = om.ScipyOptimizeDriver() -# super_prob.driver.options['optimizer'] = 'SLSQP' -# super_prob.model.add_objective('compound') # output from execcomp goes here - -# with warnings.catch_warnings(): -# warnings.simplefilter("ignore", om.OpenMDAOWarning) -# warnings.simplefilter("ignore", om.PromotionWarning) -# super_prob.setup() - -# if makeN2: -# om.n2(super_prob, outfile="multi_mission_importTraj_N2.html") # create N2 diagram - -# # cannot use this b/c initial guesses (i.e. setval func) has to be called on super prob level -# # for prob in probs: -# # # prob.setup() -# # prob.set_initial_guesses() - -# # dm.run_problem(super_prob) - - -""" -Ferry mission phase info: -Times (min): 0, 50, 812, 843 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 7001 nmi -Notes: 32k in 30 mins too fast for aviary, climb to low alt then slow rise through cruise - -Intermediate mission phase info: -Times (min): 0, 50, 560, 590 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 4839 nmi - -Max Payload mission phase info: -Times (min): 0, 50, 260, 290 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 2272 nmi - -Hard to find multiple payload/range values for FwFm (737), so use C-5 instead -Based on: - https://en.wikipedia.org/wiki/Lockheed_C-5_Galaxy#Specifications_(C-5M), - https://www.af.mil/About-Us/Fact-Sheets/Display/Article/1529718/c-5-abc-galaxy-and-c-5m-super-galaxy/ - -MTOW: 840,000 lb -Max Payload: 281,000 lb -Max Fuel: 341,446 lb -Empty Weight: 380,000 lb -> leaves 460,000 lb for fuel+payload (max fuel + max payload = 622,446 lb) - -Payload/range: - 281,000 lb payload -> 2,150 nmi range (AF.mil) [max payload case] - 120,000 lb payload -> 4,800 nmi range (AF.mil) [intermediate case] - 0 lb payload -> 7,000 nmi range (AF.mil) [ferry case] - -Flight characteristics: - Cruise at M0.77 at 33k ft - Max rate of climb: 2100 ft/min -""" - - -""" -input disconnected error: -WARNING: The following inputs are not connected: - group_0.aircraft:air_conditioning:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.AC.aircraft:air_conditioning:mass_scaler) - group_0.aircraft:anti_icing:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.anti_icing.aircraft:anti_icing:mass_scaler) - group_0.aircraft:apu:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.apu.aircraft:apu:mass_scaler) - group_0.aircraft:avionics:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.avionics.aircraft:avionics:mass_scaler) - group_0.aircraft:canard:area (group_0.pre_mission.core_subsystems.core_geometry.canard.aircraft:canard:area) - group_0.aircraft:canard:area (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:canard:area) - group_0.aircraft:canard:area (group_0.pre_mission.core_subsystems.core_mass.canard.aircraft:canard:area) - group_0.aircraft:canard:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:canard:aspect_ratio) - group_0.aircraft:canard:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.canard.aircraft:canard:mass_scaler) - group_0.aircraft:canard:taper_ratio (group_0.pre_mission.core_subsystems.core_mass.canard.aircraft:canard:taper_ratio) - group_0.aircraft:canard:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.canard.aircraft:canard:thickness_to_chord) - group_0.aircraft:canard:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:canard:thickness_to_chord) - group_0.aircraft:canard:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.canard.aircraft:canard:wetted_area_scaler) - group_0.aircraft:crew_and_payload:cargo_container_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.cargo_containers.aircraft:crew_and_payload:cargo_container_mass_scaler) - group_0.aircraft:crew_and_payload:cargo_mass (group_0.pre_mission.core_subsystems.core_mass.cargo_containers.aircraft:crew_and_payload:cargo_mass) - group_0.aircraft:crew_and_payload:cargo_mass (group_0.pre_mission.core_subsystems.core_mass.total_mass.zero_fuel_mass.aircraft:crew_and_payload:cargo_mass) - group_0.aircraft:crew_and_payload:flight_crew_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.flight_crew.aircraft:crew_and_payload:flight_crew_mass_scaler) - group_0.aircraft:crew_and_payload:misc_cargo (group_0.pre_mission.core_subsystems.core_mass.cargo.aircraft:crew_and_payload:misc_cargo) - group_0.aircraft:crew_and_payload:non_flight_crew_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.nonflight_crew.aircraft:crew_and_payload:non_flight_crew_mass_scaler) - group_0.aircraft:crew_and_payload:passenger_service_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.pass_service.aircraft:crew_and_payload:passenger_service_mass_scaler) - group_0.aircraft:crew_and_payload:wing_cargo (group_0.pre_mission.core_subsystems.core_mass.cargo.aircraft:crew_and_payload:wing_cargo) - group_0.aircraft:design:base_area (group_0.traj.param_comp.parameters:aircraft:design:base_area) - group_0.aircraft:design:empty_mass_margin_scaler (group_0.pre_mission.core_subsystems.core_mass.total_mass.empty_mass_margin.aircraft:design:empty_mass_margin_scaler) - group_0.aircraft:design:external_subsystems_mass (group_0.pre_mission.core_subsystems.core_mass.total_mass.system_equip_mass.aircraft:design:external_subsystems_mass) - group_0.aircraft:design:lift_dependent_drag_coeff_factor (group_0.traj.param_comp.parameters:aircraft:design:lift_dependent_drag_coeff_factor) - group_0.aircraft:design:reserve_fuel_additional (group_0.post_mission.reserve_fuel.reserve_fuel_additional) - group_0.aircraft:design:subsonic_drag_coeff_factor (group_0.traj.param_comp.parameters:aircraft:design:subsonic_drag_coeff_factor) - group_0.aircraft:design:supersonic_drag_coeff_factor (group_0.traj.param_comp.parameters:aircraft:design:supersonic_drag_coeff_factor) - group_0.aircraft:design:zero_lift_drag_coeff_factor (group_0.traj.param_comp.parameters:aircraft:design:zero_lift_drag_coeff_factor) - group_0.aircraft:electrical:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.electrical.aircraft:electrical:mass_scaler) - group_0.aircraft:engine:mass (group_0.pre_mission.core_subsystems.core_mass.wing_group.engine_pod_mass.aircraft:engine:mass) - group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_propulsion.CF6.aircraft:engine:scaled_sls_thrust) - group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_propulsion.propulsion_sum.aircraft:engine:scaled_sls_thrust) - group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_subsystems.core_mass.engine_mass.aircraft:engine:scaled_sls_thrust) - group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_subsystems.core_mass.nacelle.aircraft:engine:scaled_sls_thrust) - group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_subsystems.core_mass.thrust_rev.aircraft:engine:scaled_sls_thrust) - group_0.aircraft:engine:scaled_sls_thrust (group_0.pre_mission.core_subsystems.core_mass.wing_group.engine_pod_mass.aircraft:engine:scaled_sls_thrust) - group_0.aircraft:engine:thrust_reversers_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.thrust_rev.aircraft:engine:thrust_reversers_mass_scaler) - group_0.aircraft:engine:wing_locations (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:engine:wing_locations) - group_0.aircraft:engine:wing_locations (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:engine:wing_locations) - group_0.aircraft:fins:area (group_0.pre_mission.core_subsystems.core_mass.fin.aircraft:fins:area) - group_0.aircraft:fins:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.fin.aircraft:fins:mass_scaler) - group_0.aircraft:fins:taper_ratio (group_0.pre_mission.core_subsystems.core_mass.fin.aircraft:fins:taper_ratio) - group_0.aircraft:fuel:auxiliary_fuel_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.total_fuel_capacity.aircraft:fuel:auxiliary_fuel_capacity) - group_0.aircraft:fuel:capacity_factor (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:capacity_factor) - group_0.aircraft:fuel:density_ratio (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:density_ratio) - group_0.aircraft:fuel:density_ratio (group_0.pre_mission.core_subsystems.core_mass.unusable_fuel.aircraft:fuel:density_ratio) - group_0.aircraft:fuel:fuel_margin (group_0.post_mission.fuel_calc.fuel_margin) - group_0.aircraft:fuel:fuel_system_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.fuel_system.aircraft:fuel:fuel_system_mass_scaler) - group_0.aircraft:fuel:fuselage_fuel_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.auxiliary_fuel_capacity.aircraft:fuel:fuselage_fuel_capacity) - group_0.aircraft:fuel:fuselage_fuel_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.total_fuel_capacity.aircraft:fuel:fuselage_fuel_capacity) - group_0.aircraft:fuel:total_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.auxiliary_fuel_capacity.aircraft:fuel:total_capacity) - group_0.aircraft:fuel:total_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.fuselage_fuel_capacity.aircraft:fuel:total_capacity) - group_0.aircraft:fuel:total_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_system.aircraft:fuel:total_capacity) - group_0.aircraft:fuel:total_capacity (group_0.pre_mission.core_subsystems.core_mass.unusable_fuel.aircraft:fuel:total_capacity) - group_0.aircraft:fuel:unusable_fuel_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.unusable_fuel.aircraft:fuel:unusable_fuel_mass_scaler) - group_0.aircraft:fuel:wing_ref_capacity (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:wing_ref_capacity) - group_0.aircraft:fuel:wing_ref_capacity_area (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:wing_ref_capacity_area) - group_0.aircraft:fuel:wing_ref_capacity_term_A (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:wing_ref_capacity_term_A) - group_0.aircraft:fuel:wing_ref_capacity_term_B (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:fuel:wing_ref_capacity_term_B) - group_0.aircraft:furnishings:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.furnishings.aircraft:furnishings:mass_scaler) - group_0.aircraft:fuselage:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:fuselage:laminar_flow_lower) - group_0.aircraft:fuselage:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:fuselage:laminar_flow_upper) - group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:fuselage:length) - group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:fuselage:length) - group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_geometry.fuselage_prelim.aircraft:fuselage:length) - group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_mass.electrical.aircraft:fuselage:length) - group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_mass.fuselage.aircraft:fuselage:length) - group_0.aircraft:fuselage:length (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:fuselage:length) - group_0.aircraft:fuselage:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.fuselage.aircraft:fuselage:mass_scaler) - group_0.aircraft:fuselage:max_height (group_0.pre_mission.core_subsystems.core_geometry.fuselage_prelim.aircraft:fuselage:max_height) - group_0.aircraft:fuselage:max_height (group_0.pre_mission.core_subsystems.core_mass.AC.aircraft:fuselage:max_height) - group_0.aircraft:fuselage:max_height (group_0.pre_mission.core_subsystems.core_mass.furnishings.aircraft:fuselage:max_height) - group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_geometry.fuselage_prelim.aircraft:fuselage:max_width) - group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:fuselage:max_width) - group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_mass.anti_icing.aircraft:fuselage:max_width) - group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_mass.electrical.aircraft:fuselage:max_width) - group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_mass.furnishings.aircraft:fuselage:max_width) - group_0.aircraft:fuselage:max_width (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:fuselage:max_width) - group_0.aircraft:fuselage:passenger_compartment_length (group_0.pre_mission.core_subsystems.core_mass.furnishings.aircraft:fuselage:passenger_compartment_length) - group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.AC.aircraft:fuselage:planform_area) - group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.apu.aircraft:fuselage:planform_area) - group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.avionics.aircraft:fuselage:planform_area) - group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.hydraulics.aircraft:fuselage:planform_area) - group_0.aircraft:fuselage:planform_area (group_0.pre_mission.core_subsystems.core_mass.instruments.aircraft:fuselage:planform_area) - group_0.aircraft:fuselage:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:fuselage:wetted_area_scaler) - group_0.aircraft:horizontal_tail:area (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:horizontal_tail:area) - group_0.aircraft:horizontal_tail:area (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:horizontal_tail:area) - group_0.aircraft:horizontal_tail:area (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:horizontal_tail:area) - group_0.aircraft:horizontal_tail:area (group_0.pre_mission.core_subsystems.core_mass.htail.aircraft:horizontal_tail:area) - group_0.aircraft:horizontal_tail:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:horizontal_tail:aspect_ratio) - group_0.aircraft:horizontal_tail:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:horizontal_tail:aspect_ratio) - group_0.aircraft:horizontal_tail:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:horizontal_tail:laminar_flow_lower) - group_0.aircraft:horizontal_tail:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:horizontal_tail:laminar_flow_upper) - group_0.aircraft:horizontal_tail:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.htail.aircraft:horizontal_tail:mass_scaler) - group_0.aircraft:horizontal_tail:taper_ratio (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:horizontal_tail:taper_ratio) - group_0.aircraft:horizontal_tail:taper_ratio (group_0.pre_mission.core_subsystems.core_mass.htail.aircraft:horizontal_tail:taper_ratio) - group_0.aircraft:horizontal_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:horizontal_tail:thickness_to_chord) - group_0.aircraft:horizontal_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:horizontal_tail:thickness_to_chord) - group_0.aircraft:horizontal_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:horizontal_tail:thickness_to_chord) - group_0.aircraft:horizontal_tail:vertical_tail_fraction (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:horizontal_tail:vertical_tail_fraction) - group_0.aircraft:horizontal_tail:vertical_tail_fraction (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:horizontal_tail:vertical_tail_fraction) - group_0.aircraft:horizontal_tail:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:horizontal_tail:wetted_area_scaler) - group_0.aircraft:hydraulics:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.hydraulics.aircraft:hydraulics:mass_scaler) - group_0.aircraft:hydraulics:system_pressure (group_0.pre_mission.core_subsystems.core_mass.hydraulics.aircraft:hydraulics:system_pressure) - group_0.aircraft:instruments:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.instruments.aircraft:instruments:mass_scaler) - group_0.aircraft:landing_gear:main_gear_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.landing_group.landing_gear.aircraft:landing_gear:main_gear_mass_scaler) - group_0.aircraft:landing_gear:nose_gear_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.landing_group.landing_gear.aircraft:landing_gear:nose_gear_mass_scaler) - group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:nacelle:avg_diameter) - group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_geometry.nacelles.aircraft:nacelle:avg_diameter) - group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_mass.anti_icing.aircraft:nacelle:avg_diameter) - group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:nacelle:avg_diameter) - group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_mass.nacelle.aircraft:nacelle:avg_diameter) - group_0.aircraft:nacelle:avg_diameter (group_0.pre_mission.core_subsystems.core_mass.starter.aircraft:nacelle:avg_diameter) - group_0.aircraft:nacelle:avg_length (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:nacelle:avg_length) - group_0.aircraft:nacelle:avg_length (group_0.pre_mission.core_subsystems.core_geometry.nacelles.aircraft:nacelle:avg_length) - group_0.aircraft:nacelle:avg_length (group_0.pre_mission.core_subsystems.core_mass.nacelle.aircraft:nacelle:avg_length) - group_0.aircraft:nacelle:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:nacelle:laminar_flow_lower) - group_0.aircraft:nacelle:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:nacelle:laminar_flow_upper) - group_0.aircraft:nacelle:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.nacelle.aircraft:nacelle:mass_scaler) - group_0.aircraft:nacelle:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.nacelles.aircraft:nacelle:wetted_area_scaler) - group_0.aircraft:paint:mass_per_unit_area (group_0.pre_mission.core_subsystems.core_mass.paint.aircraft:paint:mass_per_unit_area) - group_0.aircraft:propulsion:engine_oil_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.engine_oil.aircraft:propulsion:engine_oil_mass_scaler) - group_0.aircraft:propulsion:misc_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.misc_engine.aircraft:propulsion:misc_mass_scaler) - group_0.aircraft:vertical_tail:area (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:vertical_tail:area) - group_0.aircraft:vertical_tail:area (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:vertical_tail:area) - group_0.aircraft:vertical_tail:area (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:vertical_tail:area) - group_0.aircraft:vertical_tail:area (group_0.pre_mission.core_subsystems.core_mass.vert_tail.aircraft:vertical_tail:area) - group_0.aircraft:vertical_tail:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:vertical_tail:aspect_ratio) - group_0.aircraft:vertical_tail:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:vertical_tail:aspect_ratio) - group_0.aircraft:vertical_tail:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:vertical_tail:laminar_flow_lower) - group_0.aircraft:vertical_tail:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:vertical_tail:laminar_flow_upper) - group_0.aircraft:vertical_tail:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.vert_tail.aircraft:vertical_tail:mass_scaler) - group_0.aircraft:vertical_tail:taper_ratio (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:vertical_tail:taper_ratio) - group_0.aircraft:vertical_tail:taper_ratio (group_0.pre_mission.core_subsystems.core_mass.vert_tail.aircraft:vertical_tail:taper_ratio) - group_0.aircraft:vertical_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:vertical_tail:thickness_to_chord) - group_0.aircraft:vertical_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:vertical_tail:thickness_to_chord) - group_0.aircraft:vertical_tail:thickness_to_chord (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:vertical_tail:thickness_to_chord) - group_0.aircraft:vertical_tail:wetted_area_scaler (group_0.pre_mission.core_subsystems.core_geometry.tail.aircraft:vertical_tail:wetted_area_scaler) - group_0.aircraft:wing:aeroelastic_tailoring_factor (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:aeroelastic_tailoring_factor) - group_0.aircraft:wing:aeroelastic_tailoring_factor (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:aeroelastic_tailoring_factor) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.wing.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_geometry.wing_prelim.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.hydraulics.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.surf_ctrl.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.unusable_fuel.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_misc.aircraft:wing:area) - group_0.aircraft:wing:area (group_0.traj.param_comp.parameters:aircraft:wing:area) - group_0.aircraft:wing:aspect_ratio (group_0.pre_mission.core_subsystems.core_aerodynamics.design.aircraft:wing:aspect_ratio) - group_0.aircraft:wing:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:wing:aspect_ratio) - group_0.aircraft:wing:aspect_ratio (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:wing:aspect_ratio) - group_0.aircraft:wing:aspect_ratio (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:aspect_ratio) - group_0.aircraft:wing:aspect_ratio (group_0.traj.param_comp.parameters:aircraft:wing:aspect_ratio) - group_0.aircraft:wing:aspect_ratio_reference (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:aspect_ratio_reference) - group_0.aircraft:wing:bending_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:bending_mass_scaler) - group_0.aircraft:wing:bwb_aft_body_mass (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_total.aircraft:wing:bwb_aft_body_mass) - group_0.aircraft:wing:chord_per_semispan (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:chord_per_semispan) - group_0.aircraft:wing:composite_fraction (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:composite_fraction) - group_0.aircraft:wing:composite_fraction (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_misc.aircraft:wing:composite_fraction) - group_0.aircraft:wing:composite_fraction (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_shear_control.aircraft:wing:composite_fraction) - group_0.aircraft:wing:control_surface_area (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_shear_control.aircraft:wing:control_surface_area) - group_0.aircraft:wing:control_surface_area_ratio (group_0.pre_mission.core_subsystems.core_mass.surf_ctrl.aircraft:wing:control_surface_area_ratio) - group_0.aircraft:wing:dihedral (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:wing:dihedral) - group_0.aircraft:wing:glove_and_bat (group_0.pre_mission.core_subsystems.core_geometry.characteristic_lengths.aircraft:wing:glove_and_bat) - group_0.aircraft:wing:glove_and_bat (group_0.pre_mission.core_subsystems.core_geometry.fuselage.aircraft:wing:glove_and_bat) - group_0.aircraft:wing:glove_and_bat (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:wing:glove_and_bat) - group_0.aircraft:wing:glove_and_bat (group_0.pre_mission.core_subsystems.core_geometry.wing_prelim.aircraft:wing:glove_and_bat) - group_0.aircraft:wing:incidence (group_0.traj.param_comp.parameters:aircraft:wing:incidence) - group_0.aircraft:wing:laminar_flow_lower (group_0.traj.param_comp.parameters:aircraft:wing:laminar_flow_lower) - group_0.aircraft:wing:laminar_flow_upper (group_0.traj.param_comp.parameters:aircraft:wing:laminar_flow_upper) - group_0.aircraft:wing:load_fraction (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:load_fraction) - group_0.aircraft:wing:load_path_sweep_dist (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending_factor.aircraft:wing:load_path_sweep_dist) - group_0.aircraft:wing:mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_total.aircraft:wing:mass_scaler) - group_0.aircraft:wing:max_camber_at_70_semispan (group_0.pre_mission.core_subsystems.core_aerodynamics.design.aircraft:wing:max_camber_at_70_semispan) - group_0.aircraft:wing:max_camber_at_70_semispan (group_0.traj.param_comp.parameters:aircraft:wing:max_camber_at_70_semispan) - group_0.aircraft:wing:misc_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:misc_mass_scaler) - group_0.aircraft:wing:misc_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_misc.aircraft:wing:misc_mass_scaler) - group_0.aircraft:wing:shear_control_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:shear_control_mass_scaler) - group_0.aircraft:wing:shear_control_mass_scaler (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_shear_control.aircraft:wing:shear_control_mass_scaler) - group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_geometry.prelim.aircraft:wing:span) - group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_geometry.wing_prelim.aircraft:wing:span) - group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_mass.anti_icing.aircraft:wing:span) - group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_mass.fuel_capacity_group.wing_fuel_capacity.aircraft:wing:span) - group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_mass.landing_group.main_landing_gear_length.aircraft:wing:span) - group_0.aircraft:wing:span (group_0.pre_mission.core_subsystems.core_mass.wing_group.wing_bending.aircraft:wing:span) -""" From e52792274adbf4a828eb11f8b06ccbea83df6181 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Tue, 6 Aug 2024 14:17:25 -0400 Subject: [PATCH 037/113] tried to apply fix for actual_range connection for 2DOF collocation --- aviary/interface/methods_for_level2.py | 4 ++-- 1 file changed, 2 insertions(+), 2 deletions(-) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index 0a056f1ad..afb81ecf3 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -1568,14 +1568,14 @@ def link_phases(self): Mission.Landing.TOUCHDOWN_MASS, src_indices=[-1]) connect_map = { - f"traj.{self.regular_phases[-1]}.timeseries.distance": Mission.Summary.RANGE, + f"traj.{self.regular_phases[-1]}.timeseries.distance": 'actual_range', } else: connect_map = { "taxi.mass": "traj.mass_initial", Mission.Takeoff.ROTATION_VELOCITY: "traj.SGMGroundroll_velocity_trigger", - "traj.distance_final": Mission.Summary.RANGE, + "traj.distance_final": 'actual_range', "traj.mass_final": Mission.Landing.TOUCHDOWN_MASS, } From 8ffc2fce6d82a99dc07e16ac5a8bceec10039e92 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Tue, 6 Aug 2024 14:27:26 -0400 Subject: [PATCH 038/113] successful optimization --- multi_aviary_copymodel.py | 18 ++---------------- 1 file changed, 2 insertions(+), 16 deletions(-) diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index 5e0568e5a..96dfb1595 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -68,16 +68,10 @@ def add_design_variables(self): def add_driver(self): self.driver = om.pyOptSparseDriver() - self.driver.options["optimizer"] = "SNOPT" + self.driver.options["optimizer"] = "SLSQP" # driver.declare_coloring(True) # do we need this anymore of we're specifying the below? # maybe we're getting matrixes that are too sparse, decrease tolerance to avoid missing corellatiton # set coloring at this value. 1e-45 didn't seem to make much difference - self.driver.declare_coloring(tol=1e-25, orders=None) - self.driver.opt_settings["Major iterations limit"] = 60 - self.driver.opt_settings["Major optimality tolerance"] = 1e-6 - self.driver.opt_settings["Major feasibility tolerance"] = 1e-6 - self.driver.opt_settings["iSumm"] = 6 - self.driver.opt_settings['Verify level'] = -1 # self.driver.options['maxiter'] = 1e3 # self.driver.declare_coloring() # self.model.linear_solver = om.DirectSolver() @@ -105,8 +99,7 @@ def add_objective(self): # connecting each subcomponent's fuel burn to super problem's unique fuel variables self.model.connect( self.group_prefix+f"_{i}.{Mission.Objectives.FUEL}", f"fuel_{i}") - self.model.add_objective('compound', ref=1) - self.model.add_objective('compound', ref=1) + self.model.add_objective('compound') def setup_wrapper(self): """Wrapper for om.Problem setup with warning ignoring and setting options""" @@ -174,13 +167,6 @@ def get_design_range(self, phase_infos): print(f"Variable: {key}") print(f"Values: {val1}, {val2} (lbm)") - comps = ['vertical_tail', 'horizontal_tail', 'wing', 'fuselage'] - print("\nmass comparisons") - for comp in comps: - v1 = super_prob.get_val(f'group_0.aircraft:{comp}:mass') - v2 = super_prob.get_val(f'group_1.aircraft:{comp}:mass') - print(f'{comp}: {v1} vs. {v2}') - sol = CaseReader('res.db').get_case('final') # super_prob.model.list_vars() # for i in range(2): From 369d4783803f3e7de9b3a9a7849bf58dc2ee58ad Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 7 Aug 2024 09:19:22 -0400 Subject: [PATCH 039/113] added plotting for multi mission --- multi_aviary_copymodel.py | 199 ++++++++++++++++++++++---------------- test_single_aviary.py | 12 +-- 2 files changed, 119 insertions(+), 92 deletions(-) diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index 96dfb1595..146eadafa 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -1,28 +1,24 @@ """ -Goal: use single aircraft description but optimize it for multiple missions simultaneously, -i.e. all missions are on the range-payload line instead of having excess performance -Aircraft csv: defines plane, but also defines payload (passengers, cargo) which can vary with mission - These will have to be specified in some alternate way such as a list correspond to mission # -Phase info: defines a particular mission, will have multiple phase infos +authors: Jatin Soni, Eliot Aretskin +Multi Mission Optimization Example using Aviary """ +from os.path import join import sys import warnings -import aviary.api as av -import openmdao.api as om import dymos as dm import numpy as np import matplotlib.pyplot as plt -from c5_models.c5_ferry_phase_info import phase_info as c5_ferry_phase_info -from c5_models.c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info -from c5_models.c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info -from easy_phase_info_inter import phase_info as easy_inter -from easy_phase_info_max import phase_info as easy_max -from aviary.variable_info.variables import Mission, Aircraft + +import aviary.api as av from aviary.variable_info.enums import ProblemType -from openmdao.api import CaseReader +from aviary.variable_info.variables import Mission, Aircraft +import openmdao.api as om +from openmdao.api import CaseReader -# "comp?.a can be used to reference multiple comp1.a comp2.a etc" +from c5_models.c5_ferry_phase_info import phase_info as c5_ferry_phase_info +from c5_models.c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info +from c5_models.c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info class MultiMissionProblem(om.Problem): @@ -42,9 +38,12 @@ def __init__(self, planes, phase_infos, weights): elif len(weights) > self.num_missions: raise Exception("Length of weights cannot exceed length of planes!") self.weights = weights + self.phase_infos = phase_infos self.group_prefix = 'group' self.probs = [] + self.fuel_vars = [] + self.phases = {} # define individual aviary problems for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): prob = av.AviaryProblem() @@ -54,51 +53,47 @@ def __init__(self, planes, phase_infos, weights): prob.add_phases() prob.add_post_mission_systems() prob.link_phases() + + # alternate prevents use of equality constraint b/w design and summary gross mass prob.problem_type = ProblemType.ALTERNATE - prob.add_design_variables() # should not work at super prob level + prob.add_design_variables() self.probs.append(prob) - + # phase names for each traj (can be used later to make plots/print outputs) + self.phases[f"{self.group_prefix}_{i}"] = list(prob.traj._phases.keys()) + + # design range and gross mass are promoted, these are Max Range/Max Takeoff Mass + # and must be the same for each aviary problem. Subsystems within aviary are sized + # using these - empty mass is same across all aviary problems. + # the fuel objective is also promoted since that's used in the compound objective + promoted_name = f"{self.group_prefix}_{i}_fuelobj" + self.fuel_vars.append(promoted_name) self.model.add_subsystem( self.group_prefix + f'_{i}', prob.model, - promotes=[Mission.Design.GROSS_MASS, Mission.Design.RANGE]) + promotes=[Mission.Design.GROSS_MASS, + Mission.Design.RANGE, + (Mission.Objectives.FUEL, promoted_name)]) def add_design_variables(self): self.model.add_design_var('mission:design:gross_mass', lower=10., upper=900e3) def add_driver(self): self.driver = om.pyOptSparseDriver() - self.driver.options["optimizer"] = "SLSQP" - # driver.declare_coloring(True) # do we need this anymore of we're specifying the below? - # maybe we're getting matrixes that are too sparse, decrease tolerance to avoid missing corellatiton - # set coloring at this value. 1e-45 didn't seem to make much difference - # self.driver.options['maxiter'] = 1e3 - # self.driver.declare_coloring() + self.driver.declare_coloring() + # linear solver causes nan entry error for landing to takeoff mass ratio param # self.model.linear_solver = om.DirectSolver() - """scipy SLSQP results - Iteration limit reached (Exit mode 9) - Current function value: -43.71865402878029 - Iterations: 200 - Function evaluations: 1018 - Gradient evaluations: 200 - Optimization FAILED. - Iteration limit reached""" def add_objective(self): + # weights are normalized - e.g. for given weights 3:1, the normalized + # weights are 0.75:0.25 weights = [float(weight/sum(self.weights)) for weight in self.weights] - fuel_burned_vars = [f"fuel_{i}" for i in range(self.num_missions)] - weighted_str = "+".join([f"{fuel}*{weight}" - for fuel, weight in zip(fuel_burned_vars, weights)]) + weighted_str = "+".join([f"{fuelobj}*{weight}" + for fuelobj, weight in zip(self.fuel_vars, weights)]) # weighted_str looks like: fuel_0 * weight[0] + fuel_1 * weight[1] # adding compound execComp to super problem self.model.add_subsystem('compound_fuel_burn_objective', om.ExecComp( - "compound = "+weighted_str), promotes=["compound", *fuel_burned_vars]) - - for i in range(self.num_missions): - # connecting each subcomponent's fuel burn to super problem's unique fuel variables - self.model.connect( - self.group_prefix+f"_{i}.{Mission.Objectives.FUEL}", f"fuel_{i}") + "compound = "+weighted_str), promotes=["compound"]) self.model.add_objective('compound') def setup_wrapper(self): @@ -117,82 +112,114 @@ def setup_wrapper(self): self.setup(check='all') def run(self): - # self.run_model() - # self.check_totals(method='fd', compact_print=True) self.model.set_solver_print(0) + dm.run_problem(self, make_plots=True) - # self.run_driver() - dm.run_problem(self, make_plots=True, solution_record_file='res.db') - - def get_design_range(self, phase_infos): + def get_design_range(self): + """Finds the longest mission and sets its range as the design range for all + Aviary problems. Used within Aviary for sizing subsystems.""" design_range = 0 - for phase_info in phase_infos: + for phase_info in self.phase_infos: get_range = phase_info['post_mission']['target_range'][0] # TBD add units if get_range > design_range: design_range = get_range return design_range -if __name__ == '__main__': - makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False - planes = ['c5_models/c5_maxpayload.csv', 'c5_models/c5_intermediate.csv'] - # phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] - phase_infos = [easy_max, easy_inter] +def C5_example(): + plane_dir = 'c5_models' + planes = ['c5_maxpayload.csv', 'c5_intermediate.csv'] + planes = [join(plane_dir, plane) for plane in planes] phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] weights = [1, 1] + super_prob = MultiMissionProblem(planes, phase_infos, weights) super_prob.add_driver() super_prob.add_design_variables() super_prob.add_objective() - super_prob.model.set_input_defaults('mission:design:range', val=4000) + # set input default to prevent error, value doesn't matter since set val is used later + super_prob.model.set_input_defaults(Mission.Design.RANGE, val=1.) super_prob.setup_wrapper() - super_prob.set_val('mission:design:range', super_prob.get_design_range(phase_infos)) + super_prob.set_val(Mission.Design.RANGE, super_prob.get_design_range()) + for i, prob in enumerate(super_prob.probs): prob.set_initial_guesses(super_prob, super_prob.group_prefix+f"_{i}.") - # super_prob.final_setup() if makeN2: from createN2 import createN2 createN2(__file__, super_prob) + super_prob.run() + return super_prob + + +def createTimeseriesPlots(super_prob, plotvars): + for plotidx, (var, unit) in enumerate(plotvars): + plt.subplot(int(np.ceil(len(plotvars)/2)), 2, plotidx+1) + for i in range(super_prob.num_missions): + time = np.array([]) + yvar = np.array([]) + for phase in super_prob.phases[f"{super_prob.group_prefix}_{i}"]: + rawt = super_prob.get_val( + f"{super_prob.group_prefix}_{i}.traj.{phase}.timeseries.time") + rawy = super_prob.get_val( + f"{super_prob.group_prefix}_{i}.traj.{phase}.timeseries.{var}", + units=unit) + time = np.hstack([time, np.ndarray.flatten(rawt)]) + yvar = np.hstack([yvar, np.ndarray.flatten(rawy)]) + plt.plot(time, yvar, 'o') + plt.xlabel("Time (s)") + plt.ylabel(f"{var.title()} ({unit})") + plt.grid() + plt.figlegend([f"Plane {i}" for i in range(super_prob.num_missions)]) + plt.show() + + +if __name__ == '__main__': + makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False - outputs = {Mission.Summary.FUEL_BURNED: [], - Aircraft.Design.EMPTY_MASS: [], + super_prob = C5_example() + plotvars = [('altitude', 'ft'), + ('mass', 'lbm'), + ('drag', 'lbf'), + ('distance', 'nmi'), + ('throttle', 'unitless')] + createTimeseriesPlots(super_prob, plotvars) + + outputs = {Aircraft.Design.EMPTY_MASS: [], + Mission.Summary.FUEL_BURNED: [], Mission.Summary.GROSS_MASS: []} print("\n\n=========================\n") for key in outputs.keys(): - val1 = super_prob.get_val(f'group_0.{key}', units='lbm')[0] - val2 = super_prob.get_val(f'group_1.{key}', units='lbm')[0] print(f"Variable: {key}") - print(f"Values: {val1}, {val2} (lbm)") - - sol = CaseReader('res.db').get_case('final') - # super_prob.model.list_vars() - # for i in range(2): - var = 'throttle' - t = np.concatenate([sol.get_val('group_0.traj.climb_1.t'), - sol.get_val('group_0.traj.climb_2.t'), - sol.get_val('group_0.traj.descent_1.t')]) - alt = np.concatenate([sol.get_val(f'group_0.traj.climb_1.timeseries.{var}'), - sol.get_val(f'group_0.traj.climb_2.timeseries.{var}'), - sol.get_val(f'group_0.traj.descent_1.timeseries.{var}')]) - t2 = np.concatenate([sol.get_val('group_1.traj.climb_1.t'), - sol.get_val('group_1.traj.climb_2.t'), - sol.get_val('group_1.traj.descent_1.t')]) - alt2 = np.concatenate([sol.get_val(f'group_1.traj.climb_1.timeseries.{var}'), - sol.get_val(f'group_1.traj.climb_2.timeseries.{var}'), - sol.get_val(f'group_1.traj.descent_1.timeseries.{var}')]) - plt.plot(t, alt, 'r*') - plt.plot(t2, alt2, 'b*') - plt.title(f"Time vs {var}") - plt.legend(['group_0', 'group_1']) - plt.grid() - plt.show() + for i in range(super_prob.num_missions): + val = super_prob.get_val(f'group_{i}.{key}', units='lbm')[0] + print(f"\tPlane {i}: {val} (lbm)") + """ +1:1 +Variable: mission:summary:fuel_burned +Values: 164988.61664962117, 306345.04737967893 (lbm) +Variable: aircraft:design:empty_mass +Values: 378204.91862045845, 378204.91862045845 (lbm) +Variable: mission:summary:gross_mass +Values: 598462.8871182877, 710244.3178483456 (lbm) + +1.5:1 +Variable: mission:summary:fuel_burned +Values: 164988.61476287164, 306345.04738991836 (lbm) +Variable: aircraft:design:empty_mass +Values: 378204.91862045845, 378204.91862045845 (lbm) +Variable: mission:summary:gross_mass +Values: 598462.8852315382, 710244.3178585849 (lbm) + +2:1 Variable: mission:summary:fuel_burned -Values: 13730.910584707046, 15740.545749454643 +Values: 164988.61651039496, 306345.04738988867 (lbm) Variable: aircraft:design:empty_mass -Values: 336859.7179064408, 337047.85745526763 +Values: 378204.91862045845, 378204.91862045845 (lbm) +Variable: mission:summary:gross_mass +Values: 598462.8869790616, 710244.3178585552 (lbm) """ diff --git a/test_single_aviary.py b/test_single_aviary.py index 10acfeeac..e130dc092 100644 --- a/test_single_aviary.py +++ b/test_single_aviary.py @@ -1,8 +1,8 @@ import aviary.api as av -from easy_phase_info_max import phase_info as max_phase_info -from easy_phase_info_inter import phase_info as inter_phase_info -# from c5_models.c5_maxpayload_phase_info import phase_info as max_phase_info -# from c5_models.c5_intermediate_phase_info import phase_info as inter_phase_info +# from easy_phase_info_max import phase_info as max_phase_info +# from easy_phase_info_inter import phase_info as inter_phase_info +from c5_models.c5_maxpayload_phase_info import phase_info as max_phase_info +from c5_models.c5_intermediate_phase_info import phase_info as inter_phase_info from aviary.variable_info.variables import Mission, Aircraft @@ -43,7 +43,7 @@ """ Current output: Variable: mission:summary:fuel_burned -Values: [140116.12301917037, 276762.7974282048] +Values: [164988.61692553537, 306345.04738212295] Variable: aircraft:design:empty_mass -Values: [302105.1606792437, 315604.5402712884] +Values: [339001.4003946201, 355540.377187145] """ From 3c094f9d67cd52d7ab4ecb78d0d513ce649cff04 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 7 Aug 2024 10:14:17 -0400 Subject: [PATCH 040/113] updated plot functions to be a multi mission method --- multi_aviary_copymodel.py | 130 ++++++++++++++++++++++++-------------- 1 file changed, 84 insertions(+), 46 deletions(-) diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index 146eadafa..37aa5bbe2 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -2,20 +2,18 @@ authors: Jatin Soni, Eliot Aretskin Multi Mission Optimization Example using Aviary """ -from os.path import join import sys import warnings import dymos as dm import numpy as np +from os.path import join import matplotlib.pyplot as plt +import openmdao.api as om import aviary.api as av from aviary.variable_info.enums import ProblemType from aviary.variable_info.variables import Mission, Aircraft -import openmdao.api as om -from openmdao.api import CaseReader - from c5_models.c5_ferry_phase_info import phase_info as c5_ferry_phase_info from c5_models.c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info from c5_models.c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info @@ -125,13 +123,78 @@ def get_design_range(self): design_range = get_range return design_range + def create_timeseries_plots(self, plotvars=[], show=True): + """Creates timeseries plots for any variables within timeseries. Specify variables + and units by setting plotvars = [('altitude','ft')]. Any number of vars can be added.""" + plt.figure() + for plotidx, (var, unit) in enumerate(plotvars): + plt.subplot(int(np.ceil(len(plotvars)/2)), 2, plotidx+1) + for i in range(self.num_missions): + time = np.array([]) + yvar = np.array([]) + # this loop concatenates data from all phases + for phase in self.phases[f"{self.group_prefix}_{i}"]: + rawt = self.get_val( + f"{self.group_prefix}_{i}.traj.{phase}.timeseries.time", + units='s') + rawy = self.get_val( + f"{self.group_prefix}_{i}.traj.{phase}.timeseries.{var}", + units=unit) + time = np.hstack([time, np.ndarray.flatten(rawt)]) + yvar = np.hstack([yvar, np.ndarray.flatten(rawy)]) + plt.plot(time, yvar, 'o') + plt.xlabel("Time (s)") + plt.ylabel(f"{var.title()} ({unit})") + plt.grid() + plt.figlegend([f"Plane {i}" for i in range(self.num_missions)]) + if show: + plt.show() + + def create_payload_range_plot(self, show=True): + """Creates payload range diagram for the super problem. Appends a point for max payload + and 0 range. """ + payloads = [] + ranges = [] + for i in range(self.num_missions): + ref = f"{self.group_prefix}_{i}" + payloads.append( + self.get_val( + f"{ref}.{Aircraft.CrewPayload.CARGO_MASS}", units='lbm')) + lastphase = self.phases[ref][-1] + ranges.append( + self.get_val( + f"{ref}.traj.{lastphase}.timeseries.distance", + units='nmi', indices=-1)[0]) + payloads, ranges = zip(*sorted(zip(payloads, ranges))) + payloads, ranges = list(payloads), list(ranges) + payloads.append(payloads[-1]) + ranges.append(0) + plt.figure() + plt.plot(ranges, payloads) + plt.xlabel("Range (nmi)") + plt.ylabel("Payload (lbm)") + plt.grid() + if show: + plt.show() + + def print_vars(self, vars=[]): + """Specify vars with name and unit in a tuple, e.g. vars = [ (Mission.Summary.FUEL_BURNED, 'lbm') ]""" + + print("\n\n=========================\n") + for var, unit in vars: + print(f"Variable: {var}") + for i in range(self.num_missions): + val = self.get_val(f'group_{i}.{var}', units=unit)[0] + print(f"\tPlane {i}: {val} ({unit})") + -def C5_example(): +def C5_example(makeN2=False): plane_dir = 'c5_models' - planes = ['c5_maxpayload.csv', 'c5_intermediate.csv'] + planes = ['c5_maxpayload.csv', 'c5_intermediate.csv', 'c5_ferry.csv'] planes = [join(plane_dir, plane) for plane in planes] - phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] - weights = [1, 1] + phase_infos = [c5_maxpayload_phase_info, + c5_intermediate_phase_info, c5_ferry_phase_info] + weights = [1, 1, 1] super_prob = MultiMissionProblem(planes, phase_infos, weights) super_prob.add_driver() @@ -150,53 +213,28 @@ def C5_example(): createN2(__file__, super_prob) super_prob.run() - return super_prob - - -def createTimeseriesPlots(super_prob, plotvars): - for plotidx, (var, unit) in enumerate(plotvars): - plt.subplot(int(np.ceil(len(plotvars)/2)), 2, plotidx+1) - for i in range(super_prob.num_missions): - time = np.array([]) - yvar = np.array([]) - for phase in super_prob.phases[f"{super_prob.group_prefix}_{i}"]: - rawt = super_prob.get_val( - f"{super_prob.group_prefix}_{i}.traj.{phase}.timeseries.time") - rawy = super_prob.get_val( - f"{super_prob.group_prefix}_{i}.traj.{phase}.timeseries.{var}", - units=unit) - time = np.hstack([time, np.ndarray.flatten(rawt)]) - yvar = np.hstack([yvar, np.ndarray.flatten(rawy)]) - plt.plot(time, yvar, 'o') - plt.xlabel("Time (s)") - plt.ylabel(f"{var.title()} ({unit})") - plt.grid() - plt.figlegend([f"Plane {i}" for i in range(super_prob.num_missions)]) - plt.show() - - -if __name__ == '__main__': - makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False + printoutputs = [(Aircraft.Design.EMPTY_MASS, 'lbm'), + (Mission.Summary.FUEL_BURNED, 'lbm'), + (Mission.Summary.GROSS_MASS, 'lbm')] + super_prob.print_vars(vars=printoutputs) - super_prob = C5_example() plotvars = [('altitude', 'ft'), ('mass', 'lbm'), ('drag', 'lbf'), ('distance', 'nmi'), ('throttle', 'unitless')] - createTimeseriesPlots(super_prob, plotvars) + super_prob.create_timeseries_plots(plotvars=plotvars, show=False) - outputs = {Aircraft.Design.EMPTY_MASS: [], - Mission.Summary.FUEL_BURNED: [], - Mission.Summary.GROSS_MASS: []} + super_prob.create_payload_range_plot(show=False) + plt.show() + + return super_prob - print("\n\n=========================\n") - for key in outputs.keys(): - print(f"Variable: {key}") - for i in range(super_prob.num_missions): - val = super_prob.get_val(f'group_{i}.{key}', units='lbm')[0] - print(f"\tPlane {i}: {val} (lbm)") +if __name__ == '__main__': + makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False + + super_prob = C5_example(makeN2=makeN2) """ 1:1 From 7be24760c9ffad7c39e281b6de5ca9f6095b7642 Mon Sep 17 00:00:00 2001 From: Jatin Soni Date: Wed, 7 Aug 2024 15:38:27 -0400 Subject: [PATCH 041/113] updated output printing, added easy option to optimize all altitudes/machs --- multi_aviary_copymodel.py | 143 ++++++++++++++++++++++++++++++++------ 1 file changed, 121 insertions(+), 22 deletions(-) diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index 37aa5bbe2..dc687aab0 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -67,12 +67,18 @@ def __init__(self, planes, phase_infos, weights): self.fuel_vars.append(promoted_name) self.model.add_subsystem( self.group_prefix + f'_{i}', prob.model, - promotes=[Mission.Design.GROSS_MASS, - Mission.Design.RANGE, - (Mission.Objectives.FUEL, promoted_name)]) + promotes_inputs=[Mission.Design.GROSS_MASS, + Mission.Design.RANGE, + Aircraft.Wing.SPAN, + Aircraft.Wing.AREA], + promotes_outputs=[(Mission.Objectives.FUEL, promoted_name)]) def add_design_variables(self): - self.model.add_design_var('mission:design:gross_mass', lower=10., upper=900e3) + self.model.add_design_var(Mission.Design.GROSS_MASS, + lower=10., upper=900e3, units='lbm') + self.model.add_design_var(Aircraft.Wing.SPAN, lower=100., upper=500., units='ft') + self.model.add_design_var(Aircraft.Wing.AREA, lower=10., + upper=1e6, units='ft**2') def add_driver(self): self.driver = om.pyOptSparseDriver() @@ -142,7 +148,7 @@ def create_timeseries_plots(self, plotvars=[], show=True): units=unit) time = np.hstack([time, np.ndarray.flatten(rawt)]) yvar = np.hstack([yvar, np.ndarray.flatten(rawy)]) - plt.plot(time, yvar, 'o') + plt.plot(time, yvar, linewidth=self.num_missions-i) plt.xlabel("Time (s)") plt.ylabel(f"{var.title()} ({unit})") plt.grid() @@ -181,11 +187,19 @@ def print_vars(self, vars=[]): """Specify vars with name and unit in a tuple, e.g. vars = [ (Mission.Summary.FUEL_BURNED, 'lbm') ]""" print("\n\n=========================\n") + print(f"{'':40}", end=': ') + for i in range(self.num_missions): + name = f"Mission {i}" + print(f"{name:^30}", end='| ') + print() for var, unit in vars: - print(f"Variable: {var}") + varname = f"Variable: {var.replace(':','.').upper()}" + print(f"{varname:40}", end=": ") for i in range(self.num_missions): val = self.get_val(f'group_{i}.{var}', units=unit)[0] - print(f"\tPlane {i}: {val} ({unit})") + printstatement = f"{val} ({unit})" + print(f"{printstatement:^30}", end="| ") + print() def C5_example(makeN2=False): @@ -194,6 +208,13 @@ def C5_example(makeN2=False): planes = [join(plane_dir, plane) for plane in planes] phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info, c5_ferry_phase_info] + optalt, optmach = False, False + for phaseinfo in phase_infos: + for key in phaseinfo.keys(): + if "user_options" in phaseinfo[key].keys(): + phaseinfo[key]["user_options"]["optimize_mach"] = optmach + phaseinfo[key]["user_options"]["optimize_altitude"] = optalt + weights = [1, 1, 1] super_prob = MultiMissionProblem(planes, phase_infos, weights) @@ -215,14 +236,17 @@ def C5_example(makeN2=False): super_prob.run() printoutputs = [(Aircraft.Design.EMPTY_MASS, 'lbm'), (Mission.Summary.FUEL_BURNED, 'lbm'), - (Mission.Summary.GROSS_MASS, 'lbm')] + (Mission.Summary.GROSS_MASS, 'lbm'), + (Aircraft.Wing.SPAN, 'ft'), + (Aircraft.Wing.AREA, 'ft**2')] super_prob.print_vars(vars=printoutputs) plotvars = [('altitude', 'ft'), ('mass', 'lbm'), ('drag', 'lbf'), ('distance', 'nmi'), - ('throttle', 'unitless')] + ('throttle', 'unitless'), + ('mach', 'unitless')] super_prob.create_timeseries_plots(plotvars=plotvars, show=False) super_prob.create_payload_range_plot(show=False) @@ -237,27 +261,102 @@ def C5_example(makeN2=False): super_prob = C5_example(makeN2=makeN2) """ -1:1 -Variable: mission:summary:fuel_burned -Values: 164988.61664962117, 306345.04737967893 (lbm) +1:1:1 and 5:1:1 and 1:1:5 and 1:5:1 Variable: aircraft:design:empty_mass -Values: 378204.91862045845, 378204.91862045845 (lbm) + Plane 0: 377110.8519657982 (lbm), Plane 1: 377110.8519657982 (lbm), Plane 2: 377110.8519657982 (lbm), +Variable: mission:summary:fuel_burned + Plane 0: 167530.46091225138 (lbm), Plane 1: 308428.65141334233 (lbm), Plane 2: 412689.6603555365 (lbm), Variable: mission:summary:gross_mass -Values: 598462.8871182877, 710244.3178483456 (lbm) + Plane 0: 599904.1437916472 (lbm), Plane 1: 711227.3342927382 (lbm), Plane 2: 793323.6057604996 (lbm), +Variable: aircraft:wing:span + Plane 0: 235.7734017415966 (ft), Plane 1: 235.7734017415966 (ft), Plane 2: 235.7734017415966 (ft), +Variable: aircraft:wing:area + Plane 0: 6106.843788863166 (ft**2), Plane 1: 6106.843788863166 (ft**2), Plane 2: 6106.843788863166 (ft**2), + +1:1:5 -1.5:1 +""" + +""" +inter payload: 100k +Variable: aircraft:design:empty_mass + Plane 0: 374179.5394606042 (lbm) + Plane 1: 374179.5394606042 (lbm) + Plane 2: 374179.5394606042 (lbm) Variable: mission:summary:fuel_burned -Values: 164988.61476287164, 306345.04738991836 (lbm) + Plane 0: 165739.44323952997 (lbm) + Plane 1: 306588.0148270305 (lbm) + Plane 2: 411012.49583405076 (lbm) +Variable: mission:summary:gross_mass + Plane 0: 595188.3345483424 (lbm) + Plane 1: 702786.9061358428 (lbm) + Plane 2: 788721.6496684301 (lbm) + +inter payload: 140k Variable: aircraft:design:empty_mass -Values: 378204.91862045845, 378204.91862045845 (lbm) + Plane 0: 374179.53946059936 (lbm) + Plane 1: 374179.53946059936 (lbm) + Plane 2: 374179.53946059936 (lbm) +Variable: mission:summary:fuel_burned + Plane 0: 165739.44340813044 (lbm) + Plane 1: 306588.0148359792 (lbm) + Plane 2: 411012.4960230509 (lbm) Variable: mission:summary:gross_mass -Values: 598462.8852315382, 710244.3178585849 (lbm) + Plane 0: 595188.3347169379 (lbm) + Plane 1: 710136.9061447867 (lbm) + Plane 2: 788721.6498574257 (lbm) -2:1 +140k inter, 301k max +Variable: aircraft:design:empty_mass + Plane 0: 374179.5394605969 (lbm) + Plane 1: 374179.5394605969 (lbm) + Plane 2: 374179.5394605969 (lbm) Variable: mission:summary:fuel_burned -Values: 164988.61651039496, 306345.04738988867 (lbm) + Plane 0: 165739.44397328247 (lbm) + Plane 1: 306588.01484213956 (lbm) + Plane 2: 411012.4961383113 (lbm) +Variable: mission:summary:gross_mass + Plane 0: 598863.3352823037 (lbm) + Plane 1: 710136.9061509445 (lbm) + Plane 2: 788721.6499726834 (lbm) + +140k inter, 301k max, 10k ferry Variable: aircraft:design:empty_mass -Values: 378204.91862045845, 378204.91862045845 (lbm) + Plane 0: 374179.5394605957 (lbm) + Plane 1: 374179.5394605957 (lbm) + Plane 2: 374179.5394605957 (lbm) +Variable: mission:summary:fuel_burned + Plane 0: 165739.4440247023 (lbm) + Plane 1: 306588.01484336343 (lbm) + Plane 2: 411012.49619538186 (lbm) Variable: mission:summary:gross_mass -Values: 598462.8869790616, 710244.3178585552 (lbm) + Plane 0: 598863.3353337225 (lbm) + Plane 1: 710136.9061521672 (lbm) + Plane 2: 790586.3875041857 (lbm) +""" + +""" +optimize mach only: optimize both mach and alt: optimize neither mach or altitude +Variable: aircraft:design:empty_mass Variable: aircraft:design:empty_mass Variable: aircraft:design:empty_mass + Plane 0: 326047.42156711605 (lbm) Plane 0: 390475.71469928196 (lbm) Plane 0: 371320.23571631836 (lbm) + Plane 1: 326047.42156711605 (lbm) Plane 1: 390475.71469928196 (lbm) Plane 1: 371320.23571631836 (lbm) + Plane 2: 326047.42156711605 (lbm) Plane 2: 390475.71469928196 (lbm) Plane 2: 371320.23571631836 (lbm) +Variable: mission:summary:fuel_burned Variable: mission:summary:fuel_burned Variable: mission:summary:fuel_burned + Plane 0: 175717.28062873823 (lbm) Plane 0: 178314.99288207013 (lbm) Plane 0: 167946.2102766974 (lbm) + Plane 1: 306419.71885746776 (lbm) Plane 1: 325789.9474922766 (lbm) Plane 1: 309094.299337939 (lbm) + Plane 2: 394791.91474366543 (lbm) Plane 2: 429716.0286375711 (lbm) Plane 2: 413746.64501453174 (lbm) +Variable: mission:summary:gross_mass Variable: mission:summary:gross_mass Variable: mission:summary:gross_mass + Plane 0: 557034.0540440837 (lbm) Plane 0: 624060.059429561 (lbm) Plane 0: 594535.797841224 (lbm) + Plane 1: 658161.4922728132 (lbm) Plane 1: 741960.0140397676 (lbm) Plane 1: 706108.8869024655 (lbm) + Plane 2: 724368.9506845778 (lbm) Plane 2: 823721.3577106291 (lbm) Plane 2: 788596.4951046254 (lbm) +Variable: aircraft:wing:span Variable: aircraft:wing:span Variable: aircraft:wing:span + Plane 0: 54.707828078624665 (ft) Plane 0: 287.14946969690783 (ft) Plane 0: 211.8281919608065 (ft) + Plane 1: 54.707828078624665 (ft) Plane 1: 287.14946969690783 (ft) Plane 1: 211.8281919608065 (ft) + Plane 2: 54.707828078624665 (ft) Plane 2: 287.14946969690783 (ft) Plane 2: 211.8281919608065 (ft) +Variable: aircraft:wing:aspect_ratio Variable: aircraft:wing:aspect_ratio Variable: aircraft:wing:aspect_ratio + Plane 0: 6.263196240285538 (unitless) Plane 0: 6.931291416800268 (unitless) Plane 0: 7.576574965501183 (unitless) + Plane 1: 6.263196240285538 (unitless) Plane 1: 6.931291416800268 (unitless) Plane 1: 7.576574965501183 (unitless) + Plane 2: 6.263196240285538 (unitless) Plane 2: 6.931291416800268 (unitless) Plane 2: 7.576574965501183 (unitless) + + """ From 320e0a6fc4f1fb374c2665c13fc3a59bbd9a962b Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 8 Aug 2024 10:02:48 -0400 Subject: [PATCH 042/113] renamed a file, added a comment --- test_single_aviary.py => c5_runfile_single_aviary.py | 0 multi_aviary_copymodel.py | 2 ++ 2 files changed, 2 insertions(+) rename test_single_aviary.py => c5_runfile_single_aviary.py (100%) diff --git a/test_single_aviary.py b/c5_runfile_single_aviary.py similarity index 100% rename from test_single_aviary.py rename to c5_runfile_single_aviary.py diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index 6e3c45dbd..5ca9b0137 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -128,6 +128,8 @@ def run(self): dm.run_problem(self, make_plots=True) def get_design_range(self, phase_infos): + # Take the largest range from all the phase_infos and sets that as design_range + # this affects how large the avionics mass and landing gear mass design_range = 0 for phase_info in phase_infos: get_range = phase_info['post_mission']['target_range'][0] # TBD add units From d85b692c9e4e434685a90e19afac70fb00236c61 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Mon, 12 Aug 2024 11:35:18 -0400 Subject: [PATCH 043/113] added min and max range to get_design_range --- multi_aviary_copymodel.py | 22 ++++++++++++++-------- 1 file changed, 14 insertions(+), 8 deletions(-) diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index d6f75d0d5..47db49e54 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -121,17 +121,23 @@ def run(self): def get_design_range(self): """Finds the longest mission and sets its range as the design range for all - Aviary problems. Used within Aviary for sizing subsystems (avionics and landing gear).""" - design_range = 0 + Aviary problems. Used within Aviary for sizing subsystems (avionics and AC). + Landing gear decreases in size as range increases, + so that should be sized of minimum range mission!""" + design_range = [] for phase_info in self.phase_infos: - get_range = phase_info['post_mission']['target_range'][0] # TBD add units - if get_range > design_range: - design_range = get_range - return design_range + design_range.append(phase_info['post_mission'] + ['target_range'][0]) # TBD add units + design_range_min = np.min(design_range) + design_range_max = np.max(design_range) + return design_range_max, # design_range_min def create_timeseries_plots(self, plotvars=[], show=True): - """Creates timeseries plots for any variables within timeseries. Specify variables - and units by setting plotvars = [('altitude','ft')]. Any number of vars can be added.""" + """ + Temporary create plots manually because graphing won't work for dual-trajectories. + Creates timeseries plots for any variables within timeseries. Specify variables + and units by setting plotvars = [('altitude','ft')]. Any number of vars can be added. + """ plt.figure() for plotidx, (var, unit) in enumerate(plotvars): plt.subplot(int(np.ceil(len(plotvars)/2)), 2, plotidx+1) From 1f73bb1f21821bfd247d7e08e930f813c4592caf Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Mon, 12 Aug 2024 11:36:22 -0400 Subject: [PATCH 044/113] added some comments. Opt running fine --- multi_aviary_copymodel.py | 4 +++- 1 file changed, 3 insertions(+), 1 deletion(-) diff --git a/multi_aviary_copymodel.py b/multi_aviary_copymodel.py index 47db49e54..7e6d4b7c4 100644 --- a/multi_aviary_copymodel.py +++ b/multi_aviary_copymodel.py @@ -94,10 +94,12 @@ def add_objective(self): weighted_str = "+".join([f"{fuelobj}*{weight}" for fuelobj, weight in zip(self.fuel_vars, weights)]) # weighted_str looks like: fuel_0 * weight[0] + fuel_1 * weight[1] + # note that the fuel objective itself is the base aviary fuel objective + # which is also a function of climb time becuse climb is not very sensitive to fuel # adding compound execComp to super problem self.model.add_subsystem('compound_fuel_burn_objective', om.ExecComp( - "compound = "+weighted_str), promotes=["compound"]) + "compound = "+weighted_str, has_diag_partials=True), promotes=["compound"]) self.model.add_objective('compound') def setup_wrapper(self): From 2a508f6337863bb4992c6b8941fc397af574283a Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Fri, 16 Aug 2024 12:06:05 -0400 Subject: [PATCH 045/113] moved c5 example files --- .../multi_missions/c5_models/c5_ferry.csv | 167 ++++++++++++++++++ .../c5_models/c5_ferry_phase_info.py | 83 +++++++++ .../c5_models/c5_intermediate.csv | 167 ++++++++++++++++++ .../c5_models/c5_intermediate_phase_info.py | 83 +++++++++ .../c5_models/c5_maxpayload.csv | 167 ++++++++++++++++++ .../c5_models/c5_maxpayload_phase_info.py | 83 +++++++++ .../run_multimission_example.py | 6 +- 7 files changed, 755 insertions(+), 1 deletion(-) create mode 100644 aviary/examples/multi_missions/c5_models/c5_ferry.csv create mode 100644 aviary/examples/multi_missions/c5_models/c5_ferry_phase_info.py create mode 100644 aviary/examples/multi_missions/c5_models/c5_intermediate.csv create mode 100644 aviary/examples/multi_missions/c5_models/c5_intermediate_phase_info.py create mode 100644 aviary/examples/multi_missions/c5_models/c5_maxpayload.csv create mode 100644 aviary/examples/multi_missions/c5_models/c5_maxpayload_phase_info.py rename multi_aviary_copymodel.py => aviary/examples/multi_missions/run_multimission_example.py (98%) diff --git a/aviary/examples/multi_missions/c5_models/c5_ferry.csv b/aviary/examples/multi_missions/c5_models/c5_ferry.csv new file mode 100644 index 000000000..6540463d5 --- /dev/null +++ b/aviary/examples/multi_missions/c5_models/c5_ferry.csv @@ -0,0 +1,167 @@ +# author: Chris Psenica +#aircraft:air_conditioning:mass_scaler,1.0,unitless +#aircraft:anti_icing:mass_scaler,1.0,unitless +#aircraft:apu:mass_scaler,1.0,unitless +#aircraft:avionics:mass_scaler,1.0,unitless +#aircraft:canard:area,0.0,ft**2 +#aircraft:canard:aspect_ratio,0.0,unitless +#aircraft:canard:thickness_to_chord,0.0,unitless +aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm +#aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless +#aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:mass_per_passenger,180.0,lbm + +aircraft:crew_and_payload:cargo_mass,0,lbm +#aircraft:crew_and_payload:num_passengers,82,unitless + +#aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:num_flight_crew,7,unitless +#aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless +#aircraft:crew_and_payload:wing_cargo,0.0,lbm +#aircraft:design:base_area,0.0,ft**2 +#aircraft:design:empty_mass_margin_scaler,1.0,unitless +#aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless +#aircraft:design:touchdown_mass,498554,lbm +aircraft:design:reserve_fuel_additional,0,lbm +#aircraft:design:subsonic_drag_coeff_factor,1.0,unitless +#aircraft:design:supersonic_drag_coeff_factor,1.0,unitless +aircraft:design:use_alt_mass,False,unitless +#aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless +#aircraft:electrical:mass_scaler,1.0,unitless + +aircraft:engine:data_file,models/engines/CF6.deck,unitless + +aircraft:engine:additional_mass_fraction,0.,unitless +aircraft:engine:constant_fuel_consumption,0.,lbm/h + +aircraft:engine:flight_idle_thrust_fraction,0.0,unitless +aircraft:engine:flight_idle_max_fraction,1.0,unitless +aircraft:engine:flight_idle_min_fraction,0.08,unitless +#aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless +#aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless +aircraft:engine:generate_flight_idle,False,unitless +aircraft:engine:geopotential_alt,False,unitless +aircraft:engine:ignore_negative_thrust,False,unitless +aircraft:engine:interpolation_method,slinear,unitless +aircraft:engine:mass_scaler,1.0,unitless +aircraft:engine:mass,8176,lbm +aircraft:engine:reference_mass,8176,lbm +aircraft:engine:reference_sls_thrust,51250.,lbf +aircraft:engine:scale_mass,True,unitless +aircraft:engine:scale_performance,True,unitless +aircraft:engine:scaled_sls_thrust,51250,lbf +#aircraft:engine:subsonic_fuel_flow_scaler,1.0,unitless +#aircraft:engine:supersonic_fuel_flow_scaler,1.0,unitless +#aircraft:engine:thrust_reversers_mass_scaler,1.0,unitless +aircraft:engine:num_fuselage_engines,0,unitless +aircraft:engine:num_engines,4,unitless +aircraft:engine:num_wing_engines,4,unitless +aircraft:engine:wing_locations,[0.3561541339,0.555929667],unitless +#aircraft:fins:area,0.0,ft**2 +#aircraft:fins:mass_scaler,1.0,unitless +#aircraft:fins:mass,0.0,lbm +#aircraft:fins:num_fins,0,unitless +#aircraft:fins:taper_ratio,10.0,unitless +aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm +#aircraft:fuel:density_ratio,1.0,unitless +#aircraft:fuel:fuel_system_mass_scaler,1.0,unitless +aircraft:fuel:fuselage_fuel_capacity,0.0,lbm +aircraft:fuel:num_tanks,12,unitless +aircraft:fuel:total_capacity,341446,lbm +#aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless +#aircraft:furnishings:mass_scaler,1.0,unitless +aircraft:fuselage:length,230.58,ft +#aircraft:fuselage:mass_scaler,1.0,unitless +aircraft:fuselage:max_height,26.83,ft +aircraft:fuselage:max_width,23.9,ft +aircraft:fuselage:military_cargo_floor,True,unitless +aircraft:fuselage:num_fuselages,1,unitless +aircraft:fuselage:passenger_compartment_length,143.75,ft +aircraft:fuselage:planform_area,4462.78,ft**2 +#aircraft:fuselage:wetted_area_scaler,1.0,unitless +aircraft:horizontal_tail:area,965.8,ft**2 +aircraft:horizontal_tail:aspect_ratio,4.2,unitless +#aircraft:horizontal_tail:mass_scaler,1.0,unitless +aircraft:horizontal_tail:taper_ratio,0.43,unitless +aircraft:horizontal_tail:thickness_to_chord,0.16,unitless +aircraft:horizontal_tail:vertical_tail_fraction,1.0,unitless +#aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless +#aircraft:hydraulics:mass_scaler,1.0,unitless +#aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 +#aircraft:instruments:mass_scaler,1.0,unitless +#aircraft:landing_gear:carrier_based,False,unitless +#aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless +#aircraft:landing_gear:main_gear_oleo_length,45,inch +#aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless +#aircraft:landing_gear:nose_gear_oleo_length,45,inch +aircraft:nacelle:avg_diameter,9.15,ft +aircraft:nacelle:avg_length,20.56,ft +#aircraft:nacelle:mass_scaler,1.0,unitless +#aircraft:nacelle:wetted_area_scaler,1.0,unitless +#aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 +#aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless +#aircraft:propulsion:misc_mass_scaler,1.0,unitless +aircraft:vertical_tail:area,537.9,ft**2 +aircraft:vertical_tail:aspect_ratio,0.958,unitless +#aircraft:vertical_tail:mass_scaler,1.0,unitless +aircraft:vertical_tail:num_tails,1,unitless +aircraft:vertical_tail:taper_ratio,0.846,unitless +aircraft:vertical_tail:thickness_to_chord,0.157,unitless +#aircraft:vertical_tail:wetted_area_scaler,1.0,unitless +aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless +aircraft:wing:airfoil_technology,1.0,unitless +aircraft:wing:area,6200,ft**2 +aircraft:wing:aspect_ratio,7.75,unitless +#aircraft:wing:bending_mass_scaler,1.0,unitless +#aircraft:wing:composite_fraction,0.1,unitless +aircraft:wing:control_surface_area,2323.7,ft**2 +aircraft:wing:control_surface_area_ratio,0.37479,unitless +aircraft:wing:load_distribution_control,2.0,unitless +aircraft:wing:load_fraction,1.0,unitless +#aircraft:wing:mass_scaler,1.0,unitless +aircraft:wing:max_camber_at_70_semispan,0.0,unitless +#aircraft:wing:misc_mass_scaler,1.0,unitless +#aircraft:wing:shear_control_mass_scaler,1.0,unitless +aircraft:wing:span_efficiency_reduction,False,unitless +aircraft:wing:span,222.75,ft +#aircraft:wing:strut_bracing_factor,0.0,unitless +#aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless +aircraft:wing:sweep,20.0,deg +aircraft:wing:taper_ratio,0.419,unitless +aircraft:wing:thickness_to_chord,0.1284,unitless +aircraft:wing:ultimate_load_factor,3.75,unitless +aircraft:wing:var_sweep_mass_penalty,0.0,unitless +#aircraft:wing:wetted_area_scaler,1.0,unitless +aircraft:wing:num_integration_stations,50,unitless +aircraft:wing:thickness_to_chord_dist,0.1239,0.108,0.013,unitless +aircraft:wing:load_path_sweep_dist,0.0,0.0,deg +aircraft:wing:input_station_dist,0.0,0.3298,0.884,unitless +aircraft:wing:chord_per_semispan,0.362,0.2667,0.0456,unitless +aircraft:wing:glove_and_bat,0.0,ft**2 +aircraft:wing:detailed_wing,False,unitless + + +mission:constraints:max_mach,0.77,unitless +mission:design:cruise_altitude,34000,ft +mission:design:gross_mass,840000,lbm +mission:design:range,7000.0,NM +mission:design:thrust_takeoff_per_eng,51250,lbf +mission:landing:lift_coefficient_max,3.0,unitless +mission:design:mach,0.77,unitless +#mission:summary:fuel_flow_scaler,1.0,unitless +mission:takeoff:fuel_simple,6.32,lbm +mission:takeoff:lift_coefficient_max,3.62,unitless +mission:takeoff:lift_over_drag,19.5,unitless +settings:equations_of_motion,height_energy +settings:mass_method,FLOPS + + +### missions definition +# mission_name: payload +# times: 0, 50, 280, 300 +# altitudes: 0, 30000, 30000, 0 +# machs: 0.30, 0.77, 0.77, 0.30 +# optimize_altitudes: F,F,F +# optimize_machs: F,F,F +# takeoff: F +# landing: F diff --git a/aviary/examples/multi_missions/c5_models/c5_ferry_phase_info.py b/aviary/examples/multi_missions/c5_models/c5_ferry_phase_info.py new file mode 100644 index 000000000..6a472ed2f --- /dev/null +++ b/aviary/examples/multi_missions/c5_models/c5_ferry_phase_info.py @@ -0,0 +1,83 @@ +phase_info = { + "pre_mission": {"include_takeoff": False, "optimize_mass": True}, + "climb_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.3, "unitless"), + "final_mach": (0.77, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (0.0, "ft"), + "final_altitude": (29500.0, "ft"), + "altitude_bounds": ((0.0, 30000.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": True, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((0.0, 0.0), "min"), + "duration_bounds": ((25.0, 75.0), "min"), + }, + "initial_guesses": {"time": ([0.0, 50.0], "min")}, + }, + "climb_2": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.77, "unitless"), + "final_mach": (0.77, "unitless"), + "mach_bounds": ((0.75, 0.79), "unitless"), + "initial_altitude": (29500.0, "ft"), + "final_altitude": (32000.0, "ft"), + "altitude_bounds": ((29000.0, 32500.0), "ft"), + "throttle_enforcement": "boundary_constraint", + "fix_initial": False, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((25.0, 75.0), "min"), + "duration_bounds": ((381.0, 1143.0), "min"), + }, + "initial_guesses": {"time": ([50.0, 762.0], "min")}, + }, + "descent_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.77, "unitless"), + "final_mach": (0.3, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (32000.0, "ft"), + "final_altitude": (0.0, "ft"), + "altitude_bounds": ((0.0, 32500.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": False, + "constrain_final": True, + "fix_duration": False, + "initial_bounds": ((406.0, 1218.0), "min"), + "duration_bounds": ((15.5, 46.5), "min"), + }, + "initial_guesses": {"time": ([812.0, 31.0], "min")}, + }, + "post_mission": { + "include_landing": False, + "constrain_range": True, + "target_range": (7001.59, "nmi"), + }, +} diff --git a/aviary/examples/multi_missions/c5_models/c5_intermediate.csv b/aviary/examples/multi_missions/c5_models/c5_intermediate.csv new file mode 100644 index 000000000..bb4565239 --- /dev/null +++ b/aviary/examples/multi_missions/c5_models/c5_intermediate.csv @@ -0,0 +1,167 @@ +# author: Chris Psenica +#aircraft:air_conditioning:mass_scaler,1.0,unitless +#aircraft:anti_icing:mass_scaler,1.0,unitless +#aircraft:apu:mass_scaler,1.0,unitless +#aircraft:avionics:mass_scaler,1.0,unitless +#aircraft:canard:area,0.0,ft**2 +#aircraft:canard:aspect_ratio,0.0,unitless +#aircraft:canard:thickness_to_chord,0.0,unitless +aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm +#aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless +#aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:mass_per_passenger,180.0,lbm + +aircraft:crew_and_payload:cargo_mass,120000.0,lbm +#aircraft:crew_and_payload:num_passengers,82,unitless + +#aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:num_flight_crew,7,unitless +#aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless +#aircraft:crew_and_payload:wing_cargo,0.0,lbm +#aircraft:design:base_area,0.0,ft**2 +#aircraft:design:empty_mass_margin_scaler,1.0,unitless +#aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless +#aircraft:design:touchdown_mass,498554,lbm +aircraft:design:reserve_fuel_additional,0,lbm +#aircraft:design:subsonic_drag_coeff_factor,1.0,unitless +#aircraft:design:supersonic_drag_coeff_factor,1.0,unitless +aircraft:design:use_alt_mass,False,unitless +#aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless +#aircraft:electrical:mass_scaler,1.0,unitless + +aircraft:engine:data_file,models/engines/CF6.deck,unitless + +aircraft:engine:additional_mass_fraction,0.,unitless +aircraft:engine:constant_fuel_consumption,0.,lbm/h + +aircraft:engine:flight_idle_thrust_fraction,0.0,unitless +aircraft:engine:flight_idle_max_fraction,1.0,unitless +aircraft:engine:flight_idle_min_fraction,0.08,unitless +#aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless +#aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless +aircraft:engine:generate_flight_idle,False,unitless +aircraft:engine:geopotential_alt,False,unitless +aircraft:engine:ignore_negative_thrust,False,unitless +aircraft:engine:interpolation_method,slinear,unitless +aircraft:engine:mass_scaler,1.0,unitless +aircraft:engine:mass,8176,lbm +aircraft:engine:reference_mass,8176,lbm +aircraft:engine:reference_sls_thrust,51250.,lbf +aircraft:engine:scale_mass,True,unitless +aircraft:engine:scale_performance,True,unitless +aircraft:engine:scaled_sls_thrust,51250,lbf +#aircraft:engine:subsonic_fuel_flow_scaler,1.0,unitless +#aircraft:engine:supersonic_fuel_flow_scaler,1.0,unitless +#aircraft:engine:thrust_reversers_mass_scaler,1.0,unitless +aircraft:engine:num_fuselage_engines,0,unitless +aircraft:engine:num_engines,4,unitless +aircraft:engine:num_wing_engines,4,unitless +aircraft:engine:wing_locations,[0.3561541339,0.555929667],unitless +#aircraft:fins:area,0.0,ft**2 +#aircraft:fins:mass_scaler,1.0,unitless +#aircraft:fins:mass,0.0,lbm +#aircraft:fins:num_fins,0,unitless +#aircraft:fins:taper_ratio,10.0,unitless +aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm +#aircraft:fuel:density_ratio,1.0,unitless +#aircraft:fuel:fuel_system_mass_scaler,1.0,unitless +aircraft:fuel:fuselage_fuel_capacity,0.0,lbm +aircraft:fuel:num_tanks,12,unitless +aircraft:fuel:total_capacity,341446,lbm +#aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless +#aircraft:furnishings:mass_scaler,1.0,unitless +aircraft:fuselage:length,230.58,ft +#aircraft:fuselage:mass_scaler,1.0,unitless +aircraft:fuselage:max_height,26.83,ft +aircraft:fuselage:max_width,23.9,ft +aircraft:fuselage:military_cargo_floor,True,unitless +aircraft:fuselage:num_fuselages,1,unitless +aircraft:fuselage:passenger_compartment_length,143.75,ft +aircraft:fuselage:planform_area,4462.78,ft**2 +#aircraft:fuselage:wetted_area_scaler,1.0,unitless +aircraft:horizontal_tail:area,965.8,ft**2 +aircraft:horizontal_tail:aspect_ratio,4.2,unitless +#aircraft:horizontal_tail:mass_scaler,1.0,unitless +aircraft:horizontal_tail:taper_ratio,0.43,unitless +aircraft:horizontal_tail:thickness_to_chord,0.16,unitless +aircraft:horizontal_tail:vertical_tail_fraction,1.0,unitless +#aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless +#aircraft:hydraulics:mass_scaler,1.0,unitless +#aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 +#aircraft:instruments:mass_scaler,1.0,unitless +#aircraft:landing_gear:carrier_based,False,unitless +#aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless +#aircraft:landing_gear:main_gear_oleo_length,45,inch +#aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless +#aircraft:landing_gear:nose_gear_oleo_length,45,inch +aircraft:nacelle:avg_diameter,9.15,ft +aircraft:nacelle:avg_length,20.56,ft +#aircraft:nacelle:mass_scaler,1.0,unitless +#aircraft:nacelle:wetted_area_scaler,1.0,unitless +#aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 +#aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless +#aircraft:propulsion:misc_mass_scaler,1.0,unitless +aircraft:vertical_tail:area,537.9,ft**2 +aircraft:vertical_tail:aspect_ratio,0.958,unitless +#aircraft:vertical_tail:mass_scaler,1.0,unitless +aircraft:vertical_tail:num_tails,1,unitless +aircraft:vertical_tail:taper_ratio,0.846,unitless +aircraft:vertical_tail:thickness_to_chord,0.157,unitless +#aircraft:vertical_tail:wetted_area_scaler,1.0,unitless +aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless +aircraft:wing:airfoil_technology,1.0,unitless +aircraft:wing:area,6200,ft**2 +aircraft:wing:aspect_ratio,7.75,unitless +#aircraft:wing:bending_mass_scaler,1.0,unitless +#aircraft:wing:composite_fraction,0.1,unitless +aircraft:wing:control_surface_area,2323.7,ft**2 +aircraft:wing:control_surface_area_ratio,0.37479,unitless +aircraft:wing:load_distribution_control,2.0,unitless +aircraft:wing:load_fraction,1.0,unitless +#aircraft:wing:mass_scaler,1.0,unitless +aircraft:wing:max_camber_at_70_semispan,0.0,unitless +#aircraft:wing:misc_mass_scaler,1.0,unitless +#aircraft:wing:shear_control_mass_scaler,1.0,unitless +aircraft:wing:span_efficiency_reduction,False,unitless +aircraft:wing:span,222.75,ft +#aircraft:wing:strut_bracing_factor,0.0,unitless +#aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless +aircraft:wing:sweep,20.0,deg +aircraft:wing:taper_ratio,0.419,unitless +aircraft:wing:thickness_to_chord,0.1284,unitless +aircraft:wing:ultimate_load_factor,3.75,unitless +aircraft:wing:var_sweep_mass_penalty,0.0,unitless +#aircraft:wing:wetted_area_scaler,1.0,unitless +aircraft:wing:num_integration_stations,50,unitless +aircraft:wing:thickness_to_chord_dist,0.1239,0.108,0.013,unitless +aircraft:wing:load_path_sweep_dist,0.0,0.0,deg +aircraft:wing:input_station_dist,0.0,0.3298,0.884,unitless +aircraft:wing:chord_per_semispan,0.362,0.2667,0.0456,unitless +aircraft:wing:glove_and_bat,0.0,ft**2 +aircraft:wing:detailed_wing,False,unitless + + +mission:constraints:max_mach,0.77,unitless +mission:design:cruise_altitude,34000,ft +mission:design:gross_mass,840000,lbm +mission:design:range,4800.0,NM +mission:design:thrust_takeoff_per_eng,51250,lbf +mission:landing:lift_coefficient_max,3.0,unitless +mission:design:mach,0.77,unitless +#mission:summary:fuel_flow_scaler,1.0,unitless +mission:takeoff:fuel_simple,6.32,lbm +mission:takeoff:lift_coefficient_max,3.62,unitless +mission:takeoff:lift_over_drag,19.5,unitless +settings:equations_of_motion,height_energy +settings:mass_method,FLOPS + + +### missions definition +# mission_name: payload +# times: 0, 50, 280, 300 +# altitudes: 0, 30000, 30000, 0 +# machs: 0.30, 0.77, 0.77, 0.30 +# optimize_altitudes: F,F,F +# optimize_machs: F,F,F +# takeoff: F +# landing: F diff --git a/aviary/examples/multi_missions/c5_models/c5_intermediate_phase_info.py b/aviary/examples/multi_missions/c5_models/c5_intermediate_phase_info.py new file mode 100644 index 000000000..88f121ca1 --- /dev/null +++ b/aviary/examples/multi_missions/c5_models/c5_intermediate_phase_info.py @@ -0,0 +1,83 @@ +phase_info = { + "pre_mission": {"include_takeoff": False, "optimize_mass": True}, + "climb_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.3, "unitless"), + "final_mach": (0.73, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (0.0, "ft"), + "final_altitude": (29500.0, "ft"), + "altitude_bounds": ((0.0, 30000.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": True, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((0.0, 0.0), "min"), + "duration_bounds": ((25.0, 75.0), "min"), + }, + "initial_guesses": {"time": ([0.0, 50.0], "min")}, + }, + "climb_2": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.73, "unitless"), + "final_mach": (0.73, "unitless"), + "mach_bounds": ((0.72, 0.74), "unitless"), + "initial_altitude": (29500.0, "ft"), + "final_altitude": (32000.0, "ft"), + "altitude_bounds": ((29000.0, 32500.0), "ft"), + "throttle_enforcement": "boundary_constraint", + "fix_initial": False, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((25.0, 75.0), "min"), + "duration_bounds": ((255.0, 765.0), "min"), + }, + "initial_guesses": {"time": ([50.0, 510.0], "min")}, + }, + "descent_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.73, "unitless"), + "final_mach": (0.3, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (32000.0, "ft"), + "final_altitude": (0.0, "ft"), + "altitude_bounds": ((0.0, 32500.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": False, + "constrain_final": True, + "fix_duration": False, + "initial_bounds": ((280.0, 840.0), "min"), + "duration_bounds": ((15.0, 45.0), "min"), + }, + "initial_guesses": {"time": ([560.0, 30.0], "min")}, + }, + "post_mission": { + "include_landing": False, + "constrain_range": True, + "target_range": (4839.41, "nmi"), + }, +} diff --git a/aviary/examples/multi_missions/c5_models/c5_maxpayload.csv b/aviary/examples/multi_missions/c5_models/c5_maxpayload.csv new file mode 100644 index 000000000..07a6fb381 --- /dev/null +++ b/aviary/examples/multi_missions/c5_models/c5_maxpayload.csv @@ -0,0 +1,167 @@ +# author: Chris Psenica +#aircraft:air_conditioning:mass_scaler,1.0,unitless +#aircraft:anti_icing:mass_scaler,1.0,unitless +#aircraft:apu:mass_scaler,1.0,unitless +#aircraft:avionics:mass_scaler,1.0,unitless +#aircraft:canard:area,0.0,ft**2 +#aircraft:canard:aspect_ratio,0.0,unitless +#aircraft:canard:thickness_to_chord,0.0,unitless +aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm +#aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless +#aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:mass_per_passenger,180.0,lbm + +aircraft:crew_and_payload:cargo_mass,281000.0,lbm +#aircraft:crew_and_payload:num_passengers,82,unitless + +#aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:num_flight_crew,7,unitless +#aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless +#aircraft:crew_and_payload:wing_cargo,0.0,lbm +#aircraft:design:base_area,0.0,ft**2 +#aircraft:design:empty_mass_margin_scaler,1.0,unitless +#aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless +#aircraft:design:touchdown_mass,498554,lbm +aircraft:design:reserve_fuel_additional,0,lbm +#aircraft:design:subsonic_drag_coeff_factor,1.0,unitless +#aircraft:design:supersonic_drag_coeff_factor,1.0,unitless +aircraft:design:use_alt_mass,False,unitless +#aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless +#aircraft:electrical:mass_scaler,1.0,unitless + +aircraft:engine:data_file,models/engines/CF6.deck,unitless + +aircraft:engine:additional_mass_fraction,0.,unitless +aircraft:engine:constant_fuel_consumption,0.,lbm/h + +aircraft:engine:flight_idle_thrust_fraction,0.0,unitless +aircraft:engine:flight_idle_max_fraction,1.0,unitless +aircraft:engine:flight_idle_min_fraction,0.08,unitless +#aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless +#aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless +aircraft:engine:generate_flight_idle,False,unitless +aircraft:engine:geopotential_alt,False,unitless +aircraft:engine:ignore_negative_thrust,False,unitless +aircraft:engine:interpolation_method,slinear,unitless +aircraft:engine:mass_scaler,1.0,unitless +aircraft:engine:mass,8176,lbm +aircraft:engine:reference_mass,8176,lbm +aircraft:engine:reference_sls_thrust,51250.,lbf +aircraft:engine:scale_mass,True,unitless +aircraft:engine:scale_performance,True,unitless +aircraft:engine:scaled_sls_thrust,51250,lbf +#aircraft:engine:subsonic_fuel_flow_scaler,1.0,unitless +#aircraft:engine:supersonic_fuel_flow_scaler,1.0,unitless +#aircraft:engine:thrust_reversers_mass_scaler,1.0,unitless +aircraft:engine:num_fuselage_engines,0,unitless +aircraft:engine:num_engines,4,unitless +aircraft:engine:num_wing_engines,4,unitless +aircraft:engine:wing_locations,[0.3561541339,0.555929667],unitless +#aircraft:fins:area,0.0,ft**2 +#aircraft:fins:mass_scaler,1.0,unitless +#aircraft:fins:mass,0.0,lbm +#aircraft:fins:num_fins,0,unitless +#aircraft:fins:taper_ratio,10.0,unitless +aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm +#aircraft:fuel:density_ratio,1.0,unitless +#aircraft:fuel:fuel_system_mass_scaler,1.0,unitless +aircraft:fuel:fuselage_fuel_capacity,0.0,lbm +aircraft:fuel:num_tanks,12,unitless +aircraft:fuel:total_capacity,341446,lbm +#aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless +#aircraft:furnishings:mass_scaler,1.0,unitless +aircraft:fuselage:length,230.58,ft +#aircraft:fuselage:mass_scaler,1.0,unitless +aircraft:fuselage:max_height,26.83,ft +aircraft:fuselage:max_width,23.9,ft +aircraft:fuselage:military_cargo_floor,True,unitless +aircraft:fuselage:num_fuselages,1,unitless +aircraft:fuselage:passenger_compartment_length,143.75,ft +aircraft:fuselage:planform_area,4462.78,ft**2 +#aircraft:fuselage:wetted_area_scaler,1.0,unitless +aircraft:horizontal_tail:area,965.8,ft**2 +aircraft:horizontal_tail:aspect_ratio,4.2,unitless +#aircraft:horizontal_tail:mass_scaler,1.0,unitless +aircraft:horizontal_tail:taper_ratio,0.43,unitless +aircraft:horizontal_tail:thickness_to_chord,0.16,unitless +aircraft:horizontal_tail:vertical_tail_fraction,1.0,unitless +#aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless +#aircraft:hydraulics:mass_scaler,1.0,unitless +#aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 +#aircraft:instruments:mass_scaler,1.0,unitless +#aircraft:landing_gear:carrier_based,False,unitless +#aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless +#aircraft:landing_gear:main_gear_oleo_length,45,inch +#aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless +#aircraft:landing_gear:nose_gear_oleo_length,45,inch +aircraft:nacelle:avg_diameter,9.15,ft +aircraft:nacelle:avg_length,20.56,ft +#aircraft:nacelle:mass_scaler,1.0,unitless +#aircraft:nacelle:wetted_area_scaler,1.0,unitless +#aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 +#aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless +#aircraft:propulsion:misc_mass_scaler,1.0,unitless +aircraft:vertical_tail:area,537.9,ft**2 +aircraft:vertical_tail:aspect_ratio,0.958,unitless +#aircraft:vertical_tail:mass_scaler,1.0,unitless +aircraft:vertical_tail:num_tails,1,unitless +aircraft:vertical_tail:taper_ratio,0.846,unitless +aircraft:vertical_tail:thickness_to_chord,0.157,unitless +#aircraft:vertical_tail:wetted_area_scaler,1.0,unitless +aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless +aircraft:wing:airfoil_technology,1.0,unitless +aircraft:wing:area,6200,ft**2 +aircraft:wing:aspect_ratio,7.75,unitless +#aircraft:wing:bending_mass_scaler,1.0,unitless +#aircraft:wing:composite_fraction,0.1,unitless +aircraft:wing:control_surface_area,2323.7,ft**2 +aircraft:wing:control_surface_area_ratio,0.37479,unitless +aircraft:wing:load_distribution_control,2.0,unitless +aircraft:wing:load_fraction,1.0,unitless +#aircraft:wing:mass_scaler,1.0,unitless +aircraft:wing:max_camber_at_70_semispan,0.0,unitless +#aircraft:wing:misc_mass_scaler,1.0,unitless +#aircraft:wing:shear_control_mass_scaler,1.0,unitless +aircraft:wing:span_efficiency_reduction,False,unitless +aircraft:wing:span,222.75,ft +#aircraft:wing:strut_bracing_factor,0.0,unitless +#aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless +aircraft:wing:sweep,20.0,deg +aircraft:wing:taper_ratio,0.419,unitless +aircraft:wing:thickness_to_chord,0.1284,unitless +aircraft:wing:ultimate_load_factor,3.75,unitless +aircraft:wing:var_sweep_mass_penalty,0.0,unitless +#aircraft:wing:wetted_area_scaler,1.0,unitless +aircraft:wing:num_integration_stations,50,unitless +aircraft:wing:thickness_to_chord_dist,0.1239,0.108,0.013,unitless +aircraft:wing:load_path_sweep_dist,0.0,0.0,deg +aircraft:wing:input_station_dist,0.0,0.3298,0.884,unitless +aircraft:wing:chord_per_semispan,0.362,0.2667,0.0456,unitless +aircraft:wing:glove_and_bat,0.0,ft**2 +aircraft:wing:detailed_wing,False,unitless + + +mission:constraints:max_mach,0.77,unitless +mission:design:cruise_altitude,34000,ft +mission:design:gross_mass,840000,lbm +mission:design:range,2150.0,NM +mission:design:thrust_takeoff_per_eng,51250,lbf +mission:landing:lift_coefficient_max,3.0,unitless +mission:design:mach,0.77,unitless +#mission:summary:fuel_flow_scaler,1.0,unitless +mission:takeoff:fuel_simple,6.32,lbm +mission:takeoff:lift_coefficient_max,3.62,unitless +mission:takeoff:lift_over_drag,19.5,unitless +settings:equations_of_motion,height_energy +settings:mass_method,FLOPS + + +### missions definition +# mission_name: payload +# times: 0, 50, 280, 300 +# altitudes: 0, 30000, 30000, 0 +# machs: 0.30, 0.77, 0.77, 0.30 +# optimize_altitudes: F,F,F +# optimize_machs: F,F,F +# takeoff: F +# landing: F diff --git a/aviary/examples/multi_missions/c5_models/c5_maxpayload_phase_info.py b/aviary/examples/multi_missions/c5_models/c5_maxpayload_phase_info.py new file mode 100644 index 000000000..a52acec96 --- /dev/null +++ b/aviary/examples/multi_missions/c5_models/c5_maxpayload_phase_info.py @@ -0,0 +1,83 @@ +phase_info = { + "pre_mission": {"include_takeoff": False, "optimize_mass": True}, + "climb_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.3, "unitless"), + "final_mach": (0.77, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (0.0, "ft"), + "final_altitude": (29500.0, "ft"), + "altitude_bounds": ((0.0, 30000.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": True, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((0.0, 0.0), "min"), + "duration_bounds": ((25.0, 75.0), "min"), + }, + "initial_guesses": {"time": ([0.0, 50.0], "min")}, + }, + "climb_2": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.77, "unitless"), + "final_mach": (0.77, "unitless"), + "mach_bounds": ((0.75, 0.79), "unitless"), + "initial_altitude": (29500.0, "ft"), + "final_altitude": (32000.0, "ft"), + "altitude_bounds": ((29000.0, 32500.0), "ft"), + "throttle_enforcement": "boundary_constraint", + "fix_initial": False, + "constrain_final": False, + "fix_duration": False, + "initial_bounds": ((25.0, 75.0), "min"), + "duration_bounds": ((105.0, 315.0), "min"), + }, + "initial_guesses": {"time": ([50.0, 210.0], "min")}, + }, + "descent_1": { + "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, + "user_options": { + "optimize_mach": False, + "optimize_altitude": False, + "polynomial_control_order": 1, + "use_polynomial_control": True, + "num_segments": 3, + "order": 3, + "solve_for_distance": False, + "initial_mach": (0.77, "unitless"), + "final_mach": (0.3, "unitless"), + "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), + "initial_altitude": (32000.0, "ft"), + "final_altitude": (0.0, "ft"), + "altitude_bounds": ((0.0, 32500.0), "ft"), + "throttle_enforcement": "path_constraint", + "fix_initial": False, + "constrain_final": True, + "fix_duration": False, + "initial_bounds": ((130.0, 390.0), "min"), + "duration_bounds": ((15.0, 45.0), "min"), + }, + "initial_guesses": {"time": ([260.0, 30.0], "min")}, + }, + "post_mission": { + "include_landing": False, + "constrain_range": True, + "target_range": (2272.47, "nmi"), + }, +} diff --git a/multi_aviary_copymodel.py b/aviary/examples/multi_missions/run_multimission_example.py similarity index 98% rename from multi_aviary_copymodel.py rename to aviary/examples/multi_missions/run_multimission_example.py index 7e6d4b7c4..87d4d6864 100644 --- a/multi_aviary_copymodel.py +++ b/aviary/examples/multi_missions/run_multimission_example.py @@ -246,7 +246,11 @@ def C5_example(makeN2=False): (Mission.Summary.FUEL_BURNED, 'lbm'), (Mission.Summary.GROSS_MASS, 'lbm'), (Aircraft.Wing.SPAN, 'ft'), - (Aircraft.Wing.AREA, 'ft**2')] + (Aircraft.Wing.AREA, 'ft**2'), + (Aircraft.LandingGear.MAIN_GEAR_MASS, 'lbm'), + (Aircraft.LandingGear.NOSE_GEAR_MASS, 'lbm'), + (Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, 'unitless'), + (Mission.Summary.CRUISE_MACH, 'unitless')] super_prob.print_vars(vars=printoutputs) plotvars = [('altitude', 'ft'), From 8a299a6f04560e9e5574d5978cf7072b280e53ee Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Mon, 26 Aug 2024 17:13:52 -0400 Subject: [PATCH 046/113] working example where user must specify TOUCHDOWN_MASS or LANDING_TO_TAKEOFF_MASS_RATIO and Mission.Design.RANGE must be set to be the same for all problems --- .../multi_missions/c5_models/c5_ferry.csv | 1 + .../run_multimission_example.py | 37 +++++++++++++++---- 2 files changed, 30 insertions(+), 8 deletions(-) diff --git a/aviary/examples/multi_missions/c5_models/c5_ferry.csv b/aviary/examples/multi_missions/c5_models/c5_ferry.csv index 6540463d5..336372d19 100644 --- a/aviary/examples/multi_missions/c5_models/c5_ferry.csv +++ b/aviary/examples/multi_missions/c5_models/c5_ferry.csv @@ -20,6 +20,7 @@ aircraft:crew_and_payload:num_flight_crew,7,unitless #aircraft:crew_and_payload:wing_cargo,0.0,lbm #aircraft:design:base_area,0.0,ft**2 #aircraft:design:empty_mass_margin_scaler,1.0,unitless +aircraft:design:landing_to_takeoff_mass_ration,0.91, unitless #aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless #aircraft:design:touchdown_mass,498554,lbm aircraft:design:reserve_fuel_additional,0,lbm diff --git a/aviary/examples/multi_missions/run_multimission_example.py b/aviary/examples/multi_missions/run_multimission_example.py index 87d4d6864..1857eff8c 100644 --- a/aviary/examples/multi_missions/run_multimission_example.py +++ b/aviary/examples/multi_missions/run_multimission_example.py @@ -19,6 +19,10 @@ from c5_models.c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info +# Usage: +# For the landing gear mass (MAIN_GEAR_MASS & NOSE_GEAR_MASS) to be designed consistently +# between missions, the Aircraft.Design.TOUCHDOWN_MASS must be set to the same value for all missions. + class MultiMissionProblem(om.Problem): def __init__(self, planes, phase_infos, weights): super().__init__() @@ -102,9 +106,17 @@ def add_objective(self): "compound = "+weighted_str, has_diag_partials=True), promotes=["compound"]) self.model.add_objective('compound') - def setup_wrapper(self): + def setup_wrapper(self,LANDING_TO_TAKEOFF_MASS_RATIO=[None,'unitless'], TOUCHDOWN_MASS=[None,'lbm']): """Wrapper for om.Problem setup with warning ignoring and setting options""" for prob in self.probs: + if LANDING_TO_TAKEOFF_MASS_RATIO[0] is not None: + prob.aviary_inputs.set_val(Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, LANDING_TO_TAKEOFF_MASS_RATIO[0], units=LANDING_TO_TAKEOFF_MASS_RATIO[1]) + elif TOUCHDOWN_MASS[0] is not None: + prob.aviary_inputs.set_val(Aircraft.Design.TOUCHDOWN_MASS, TOUCHDOWN_MASS[0], units=TOUCHDOWN_MASS[1]) + else: + print('User must specify LANDING_TO_TAKEOFF_MASS_RATIO or TOUCHDOWN_MASS in MultiMissionProblem.setup_wrapper().') + exit() + prob.model.options['aviary_options'] = prob.aviary_inputs prob.model.options['aviary_metadata'] = prob.meta_data prob.model.options['phase_info'] = prob.phase_info @@ -123,16 +135,14 @@ def run(self): def get_design_range(self): """Finds the longest mission and sets its range as the design range for all - Aviary problems. Used within Aviary for sizing subsystems (avionics and AC). - Landing gear decreases in size as range increases, - so that should be sized of minimum range mission!""" + Aviary problems. Used within Aviary for sizing subsystems (avionics and AC).""" design_range = [] for phase_info in self.phase_infos: design_range.append(phase_info['post_mission'] ['target_range'][0]) # TBD add units design_range_min = np.min(design_range) design_range_max = np.max(design_range) - return design_range_max, # design_range_min + return design_range_max, design_range_min # design_range_min def create_timeseries_plots(self, plotvars=[], show=True): """ @@ -231,18 +241,28 @@ def C5_example(makeN2=False): super_prob.add_objective() # set input default to prevent error, value doesn't matter since set val is used later super_prob.model.set_input_defaults(Mission.Design.RANGE, val=1.) - super_prob.setup_wrapper() - super_prob.set_val(Mission.Design.RANGE, super_prob.get_design_range()) + # Setqup aviary problem and user must specify LANDING_TO_TAKEOFF_MASS_RATIO or TOUCHDOWN_MASS + super_prob.setup_wrapper(LANDING_TO_TAKEOFF_MASS_RATIO = [0.91,'unitless']) + #super_prob.setup_wrapper(TOUCHDOWN_MASS = [700000,'lbm']) + + # All the design ranges must be the same to make sure Air Conditioning and Avionics are designed the same for all missions, + super_prob.set_val(Mission.Design.RANGE, super_prob.get_design_range()[0]) for i, prob in enumerate(super_prob.probs): prob.set_initial_guesses(super_prob, super_prob.group_prefix+f"_{i}.") + + + # this does not work: + # super_prob.set_val("group_0."+Aircraft.Design.TOUCHDOWN_MASS, 498554, units='lbm') + if makeN2: from createN2 import createN2 createN2(__file__, super_prob) super_prob.run() printoutputs = [(Aircraft.Design.EMPTY_MASS, 'lbm'), + (Mission.Design.GROSS_MASS, 'lbm'), (Mission.Summary.FUEL_BURNED, 'lbm'), (Mission.Summary.GROSS_MASS, 'lbm'), (Aircraft.Wing.SPAN, 'ft'), @@ -250,7 +270,8 @@ def C5_example(makeN2=False): (Aircraft.LandingGear.MAIN_GEAR_MASS, 'lbm'), (Aircraft.LandingGear.NOSE_GEAR_MASS, 'lbm'), (Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, 'unitless'), - (Mission.Summary.CRUISE_MACH, 'unitless')] + (Mission.Summary.CRUISE_MACH, 'unitless'), + (Aircraft.Design.TOUCHDOWN_MASS, 'lbm')] super_prob.print_vars(vars=printoutputs) plotvars = [('altitude', 'ft'), From d8d28d226849856bfab5a0bd6306f677dc6a97e8 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Wed, 4 Sep 2024 13:58:29 -0400 Subject: [PATCH 047/113] small changes to takeoff_to_landing mass ratios input handling --- .../multi_missions/run_multimission_example.py | 11 +++-------- 1 file changed, 3 insertions(+), 8 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example.py b/aviary/examples/multi_missions/run_multimission_example.py index 1857eff8c..fc311b8aa 100644 --- a/aviary/examples/multi_missions/run_multimission_example.py +++ b/aviary/examples/multi_missions/run_multimission_example.py @@ -110,9 +110,9 @@ def setup_wrapper(self,LANDING_TO_TAKEOFF_MASS_RATIO=[None,'unitless'], TOUCHDOW """Wrapper for om.Problem setup with warning ignoring and setting options""" for prob in self.probs: if LANDING_TO_TAKEOFF_MASS_RATIO[0] is not None: - prob.aviary_inputs.set_val(Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, LANDING_TO_TAKEOFF_MASS_RATIO[0], units=LANDING_TO_TAKEOFF_MASS_RATIO[1]) - elif TOUCHDOWN_MASS[0] is not None: prob.aviary_inputs.set_val(Aircraft.Design.TOUCHDOWN_MASS, TOUCHDOWN_MASS[0], units=TOUCHDOWN_MASS[1]) + elif TOUCHDOWN_MASS[0] is not None: + prob.aviary_inputs.set_val(Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, LANDING_TO_TAKEOFF_MASS_RATIO[0], units=LANDING_TO_TAKEOFF_MASS_RATIO[1]) else: print('User must specify LANDING_TO_TAKEOFF_MASS_RATIO or TOUCHDOWN_MASS in MultiMissionProblem.setup_wrapper().') exit() @@ -233,7 +233,7 @@ def C5_example(makeN2=False): phaseinfo[key]["user_options"]["optimize_mach"] = optmach phaseinfo[key]["user_options"]["optimize_altitude"] = optalt - weights = [1, 1, 1] + weights = [1, 1, 1] super_prob = MultiMissionProblem(planes, phase_infos, weights) super_prob.add_driver() @@ -251,11 +251,6 @@ def C5_example(makeN2=False): for i, prob in enumerate(super_prob.probs): prob.set_initial_guesses(super_prob, super_prob.group_prefix+f"_{i}.") - - - # this does not work: - # super_prob.set_val("group_0."+Aircraft.Design.TOUCHDOWN_MASS, 498554, units='lbm') - if makeN2: from createN2 import createN2 createN2(__file__, super_prob) From 47de110e460d13e83839ed770928bfd07baad428 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 5 Sep 2024 12:17:02 -0400 Subject: [PATCH 048/113] created FwFm multi mission, added design vars for crew passengers, neithe model converging because of wing_detailed.py and skin_friction.py issues --- .../multi_missions/c5_models/c5_ferry.csv | 2 +- .../test_aircraft/aircraft_for_bench_FwFm.csv | 4 ++ .../mass/flops_based/furnishings.py | 28 ++++----- .../mass/flops_based/wing_detailed.py | 4 ++ aviary/variable_info/variable_meta_data.py | 62 ++++++++++++++++++- aviary/variable_info/variables.py | 5 ++ 6 files changed, 89 insertions(+), 16 deletions(-) diff --git a/aviary/examples/multi_missions/c5_models/c5_ferry.csv b/aviary/examples/multi_missions/c5_models/c5_ferry.csv index 336372d19..61893fe28 100644 --- a/aviary/examples/multi_missions/c5_models/c5_ferry.csv +++ b/aviary/examples/multi_missions/c5_models/c5_ferry.csv @@ -20,7 +20,7 @@ aircraft:crew_and_payload:num_flight_crew,7,unitless #aircraft:crew_and_payload:wing_cargo,0.0,lbm #aircraft:design:base_area,0.0,ft**2 #aircraft:design:empty_mass_margin_scaler,1.0,unitless -aircraft:design:landing_to_takeoff_mass_ration,0.91, unitless +aircraft:design:landing_to_takeoff_mass_ratio,0.91, unitless #aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless #aircraft:design:touchdown_mass,498554,lbm aircraft:design:reserve_fuel_additional,0,lbm diff --git a/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv b/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv index c2fa1d8a1..f4840cdd1 100644 --- a/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv +++ b/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv @@ -17,6 +17,10 @@ aircraft:crew_and_payload:num_flight_attendants,3,unitless aircraft:crew_and_payload:num_flight_crew,2,unitless aircraft:crew_and_payload:num_galley_crew,0,unitless aircraft:crew_and_payload:num_passengers,169,unitless +aircraft:crew_and_payload:design:num_passengers,169,unitless +aircraft:crew_and_payload:design:num_tourist_class,158,unitless +aircraft:crew_and_payload:design:num_business_class,0,unitless +aircraft:crew_and_payload:design:num_first_class,11,unitless aircraft:crew_and_payload:num_tourist_class,158,unitless aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless aircraft:crew_and_payload:wing_cargo,0.0,lbm diff --git a/aviary/subsystems/mass/flops_based/furnishings.py b/aviary/subsystems/mass/flops_based/furnishings.py index 62fd9f7bf..6146caffa 100644 --- a/aviary/subsystems/mass/flops_based/furnishings.py +++ b/aviary/subsystems/mass/flops_based/furnishings.py @@ -38,13 +38,13 @@ def compute( aviary_options: AviaryValues = self.options['aviary_options'] flight_crew_count = aviary_options.get_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW) - first_class_count = aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS) + first_class_count = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) business_class_count = aviary_options.get_val( - Aircraft.CrewPayload.NUM_BUSINESS_CLASS) + Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) tourist_class_count = aviary_options.get_val( - Aircraft.CrewPayload.NUM_TOURIST_CLASS) + Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS) fuse_count = aviary_options.get_val(Aircraft.Fuselage.NUM_FUSELAGES) @@ -67,13 +67,13 @@ def compute_partials(self, inputs, J): aviary_options: AviaryValues = self.options['aviary_options'] flight_crew_count = aviary_options.get_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW) - first_class_count = aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS) + first_class_count = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) business_class_count = aviary_options.get_val( - Aircraft.CrewPayload.NUM_BUSINESS_CLASS) + Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) tourist_class_count = aviary_options.get_val( - Aircraft.CrewPayload.NUM_TOURIST_CLASS) + Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS) fuse_count = aviary_options.get_val(Aircraft.Fuselage.NUM_FUSELAGES) @@ -135,13 +135,13 @@ def compute( aviary_options: AviaryValues = self.options['aviary_options'] flight_crew_count = aviary_options.get_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW) - first_class_count = aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS) + first_class_count = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) business_class_count = aviary_options.get_val( - Aircraft.CrewPayload.NUM_BUSINESS_CLASS) + Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) tourist_class_count = aviary_options.get_val( - Aircraft.CrewPayload.NUM_TOURIST_CLASS) + Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS) scaler = inputs[Aircraft.Furnishings.MASS_SCALER] fuse_max_width = inputs[Aircraft.Fuselage.MAX_WIDTH] @@ -173,13 +173,13 @@ def compute_partials(self, inputs, J): aviary_options: AviaryValues = self.options['aviary_options'] flight_crew_count = aviary_options.get_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW) - first_class_count = aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS) + first_class_count = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) business_class_count = aviary_options.get_val( - Aircraft.CrewPayload.NUM_BUSINESS_CLASS) + Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) tourist_class_count = aviary_options.get_val( - Aircraft.CrewPayload.NUM_TOURIST_CLASS) + Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS) scaler = inputs[Aircraft.Furnishings.MASS_SCALER] @@ -275,7 +275,7 @@ def compute( ): aviary_options: AviaryValues = self.options['aviary_options'] pax_count = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') scaler = inputs[Aircraft.Furnishings.MASS_SCALER] outputs[Aircraft.Furnishings.MASS_BASE] = \ @@ -284,7 +284,7 @@ def compute( def compute_partials(self, inputs, J, discrete_inputs=None): aviary_options: AviaryValues = self.options['aviary_options'] pax_count = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') J[ Aircraft.Furnishings.MASS_BASE, diff --git a/aviary/subsystems/mass/flops_based/wing_detailed.py b/aviary/subsystems/mass/flops_based/wing_detailed.py index 81ddc32fd..174e0944c 100644 --- a/aviary/subsystems/mass/flops_based/wing_detailed.py +++ b/aviary/subsystems/mass/flops_based/wing_detailed.py @@ -149,6 +149,7 @@ def compute(self, inputs, outputs): chord_int_stations[1:] * (2*load_intensity[1:] + load_intensity[:-1])) / 6 el = np.sum(del_load) + print('el', el) del_moment = dy**2 * ( chord_int_stations[:-1] * (load_intensity[:-1]+load_intensity[1:]) + @@ -172,6 +173,7 @@ def compute(self, inputs, outputs): bma = total_moment * csw / (chord_int_stations[:-1] * tc_int_stations[:-1]) pm = np.sum((bma[:-1] + bma[1:]) * dy[:-1] * 0.5) + print('pm',pm) # s = np.sum((chord_int_stations[:-1] + chord_int_stations[1:]) * dy * 0.5) @@ -185,6 +187,8 @@ def compute(self, inputs, outputs): bt = btb / (ar**(0.25*fstrt) * (1.0 + (0.5*faert - 0.16*fstrt) * sa**2 + 0.03*caya * (1.0-0.5*faert)*sa)) + print('BT', bt) + outputs[Aircraft.Wing.BENDING_FACTOR] = bt inertia_factor = np.zeros(num_engine_type, dtype=chord.dtype) diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index e17f17509..9273fb0db 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -618,6 +618,67 @@ # |___/ # ====================================================================================== +# TODO: Set initial defaults better +# from aviary.utils.aviary_values import AviaryValues + +add_meta_data( + Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": 'WTIN.NPB', # ['&DEFINE.WTIN.NPB', 'WTS.NPB'], + "LEAPS1": 'aircraft.inputs.L0_crew_and_payload.business_class_count' + }, + units='unitless', + desc='number of business class passengers that the aircraft is designed to accommodate', + types=int, + option=True, + default_value=0, #AviaryValues.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS), +) + +add_meta_data( + Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": 'WTIN.NPF', # ['&DEFINE.WTIN.NPF', 'WTS.NPF'], + "LEAPS1": 'aircraft.inputs.L0_crew_and_payload.first_class_count' + }, + units='unitless', + desc='number of first class passengers that the aircraft is designed to accommodate', + types=int, + option=True, + default_value=0, +) + +# TODO rename to economy? +add_meta_data( + Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": 'WTIN.NPT', # ['&DEFINE.WTIN.NPT', 'WTS.NPT'], + "LEAPS1": 'aircraft.inputs.L0_crew_and_payload.tourist_class_count' + }, + units='unitless', + desc='number of tourist class passengers that the aircraft is designed to accommodate', + types=int, + option=True, + default_value=0, +) + +add_meta_data( + Aircraft.CrewPayload.Design.NUM_PASSENGERS, + meta_data=_MetaData, + historical_name={"GASP": 'INGASP.PAX', + "FLOPS": None, # ['CSTDAT.NSV', '~WEIGHT.NPASS', '~WTSTAT.NPASS'], + "LEAPS1": 'aircraft.outputs.L0_crew_and_payload.passenger_count' + }, + units='unitless', + desc='total number of passengers that the aircraft is designed to accommodate', + option=True, + default_value=0, + types=int, +) + + add_meta_data( Aircraft.CrewPayload.BAGGAGE_MASS, meta_data=_MetaData, @@ -1017,7 +1078,6 @@ # __/ | # |___/ # ========================================= - add_meta_data( Aircraft.Design.BASE_AREA, meta_data=_MetaData, diff --git a/aviary/variable_info/variables.py b/aviary/variable_info/variables.py index d2d31cfc6..61e72a935 100644 --- a/aviary/variable_info/variables.py +++ b/aviary/variable_info/variables.py @@ -129,6 +129,11 @@ class CrewPayload: TOTAL_PAYLOAD_MASS = 'aircraft:crew_and_payload:total_payload_mass' WATER_MASS_PER_OCCUPANT = 'aircraft:crew_and_payload:water_mass_per_occupant' WING_CARGO = 'aircraft:crew_and_payload:wing_cargo' + class Design: + NUM_BUSINESS_CLASS = 'aircraft:crew_and_payload:design:num_business_class' + NUM_FIRST_CLASS = 'aircraft:crew_and_payload:design:num_first_class' + NUM_TOURIST_CLASS = 'aircraft:crew_and_payload:design:num_tourist_class' + NUM_PASSENGERS = 'aircraft:crew_and_payload:design:num_passengers' class Design: # These variables are values that do not fall into a particular aircraft From e0044d21292938c90d02056ab4d14fcbb9125126 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 5 Sep 2024 13:35:52 -0400 Subject: [PATCH 049/113] no longer having nan errors on run_multimission_example.py, but dymos.phase.options error at end probably due to new dymos version --- .../examples/multi_missions/c5_models/c5_ferry.csv | 1 + .../multi_missions/c5_models/c5_intermediate.csv | 1 + .../multi_missions/c5_models/c5_maxpayload.csv | 1 + .../multi_missions/run_multimission_example.py | 14 ++------------ .../test_aircraft/aircraft_for_bench_FwFm.csv | 9 ++++++--- .../subsystems/mass/flops_based/wing_detailed.py | 3 --- aviary/variable_info/variable_meta_data.py | 2 +- 7 files changed, 12 insertions(+), 19 deletions(-) diff --git a/aviary/examples/multi_missions/c5_models/c5_ferry.csv b/aviary/examples/multi_missions/c5_models/c5_ferry.csv index 61893fe28..6f9e54275 100644 --- a/aviary/examples/multi_missions/c5_models/c5_ferry.csv +++ b/aviary/examples/multi_missions/c5_models/c5_ferry.csv @@ -13,6 +13,7 @@ aircraft:crew_and_payload:mass_per_passenger,180.0,lbm aircraft:crew_and_payload:cargo_mass,0,lbm #aircraft:crew_and_payload:num_passengers,82,unitless +#aircraft:crew_and_payload:design:num_passengers,82,unitless #aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless aircraft:crew_and_payload:num_flight_crew,7,unitless diff --git a/aviary/examples/multi_missions/c5_models/c5_intermediate.csv b/aviary/examples/multi_missions/c5_models/c5_intermediate.csv index bb4565239..cf7f415be 100644 --- a/aviary/examples/multi_missions/c5_models/c5_intermediate.csv +++ b/aviary/examples/multi_missions/c5_models/c5_intermediate.csv @@ -13,6 +13,7 @@ aircraft:crew_and_payload:mass_per_passenger,180.0,lbm aircraft:crew_and_payload:cargo_mass,120000.0,lbm #aircraft:crew_and_payload:num_passengers,82,unitless +#aircraft:crew_and_payload:design:num_passengers,82,unitless #aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless aircraft:crew_and_payload:num_flight_crew,7,unitless diff --git a/aviary/examples/multi_missions/c5_models/c5_maxpayload.csv b/aviary/examples/multi_missions/c5_models/c5_maxpayload.csv index 07a6fb381..f1f67b76d 100644 --- a/aviary/examples/multi_missions/c5_models/c5_maxpayload.csv +++ b/aviary/examples/multi_missions/c5_models/c5_maxpayload.csv @@ -13,6 +13,7 @@ aircraft:crew_and_payload:mass_per_passenger,180.0,lbm aircraft:crew_and_payload:cargo_mass,281000.0,lbm #aircraft:crew_and_payload:num_passengers,82,unitless +#aircraft:crew_and_payload:design:num_passengers,82,unitless #aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless aircraft:crew_and_payload:num_flight_crew,7,unitless diff --git a/aviary/examples/multi_missions/run_multimission_example.py b/aviary/examples/multi_missions/run_multimission_example.py index fc311b8aa..a289e63a4 100644 --- a/aviary/examples/multi_missions/run_multimission_example.py +++ b/aviary/examples/multi_missions/run_multimission_example.py @@ -106,17 +106,9 @@ def add_objective(self): "compound = "+weighted_str, has_diag_partials=True), promotes=["compound"]) self.model.add_objective('compound') - def setup_wrapper(self,LANDING_TO_TAKEOFF_MASS_RATIO=[None,'unitless'], TOUCHDOWN_MASS=[None,'lbm']): + def setup_wrapper(self): """Wrapper for om.Problem setup with warning ignoring and setting options""" for prob in self.probs: - if LANDING_TO_TAKEOFF_MASS_RATIO[0] is not None: - prob.aviary_inputs.set_val(Aircraft.Design.TOUCHDOWN_MASS, TOUCHDOWN_MASS[0], units=TOUCHDOWN_MASS[1]) - elif TOUCHDOWN_MASS[0] is not None: - prob.aviary_inputs.set_val(Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, LANDING_TO_TAKEOFF_MASS_RATIO[0], units=LANDING_TO_TAKEOFF_MASS_RATIO[1]) - else: - print('User must specify LANDING_TO_TAKEOFF_MASS_RATIO or TOUCHDOWN_MASS in MultiMissionProblem.setup_wrapper().') - exit() - prob.model.options['aviary_options'] = prob.aviary_inputs prob.model.options['aviary_metadata'] = prob.meta_data prob.model.options['phase_info'] = prob.phase_info @@ -241,9 +233,7 @@ def C5_example(makeN2=False): super_prob.add_objective() # set input default to prevent error, value doesn't matter since set val is used later super_prob.model.set_input_defaults(Mission.Design.RANGE, val=1.) - # Setqup aviary problem and user must specify LANDING_TO_TAKEOFF_MASS_RATIO or TOUCHDOWN_MASS - super_prob.setup_wrapper(LANDING_TO_TAKEOFF_MASS_RATIO = [0.91,'unitless']) - #super_prob.setup_wrapper(TOUCHDOWN_MASS = [700000,'lbm']) + super_prob.setup_wrapper() # All the design ranges must be the same to make sure Air Conditioning and Avionics are designed the same for all missions, super_prob.set_val(Mission.Design.RANGE, super_prob.get_design_range()[0]) diff --git a/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv b/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv index f4840cdd1..55ee2cac3 100644 --- a/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv +++ b/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv @@ -11,17 +11,20 @@ aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless aircraft:crew_and_payload:mass_per_passenger,180.0,lbm aircraft:crew_and_payload:misc_cargo,0.0,lbm aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:num_business_class,0,unitless -aircraft:crew_and_payload:num_first_class,11,unitless + aircraft:crew_and_payload:num_flight_attendants,3,unitless aircraft:crew_and_payload:num_flight_crew,2,unitless aircraft:crew_and_payload:num_galley_crew,0,unitless -aircraft:crew_and_payload:num_passengers,169,unitless + aircraft:crew_and_payload:design:num_passengers,169,unitless aircraft:crew_and_payload:design:num_tourist_class,158,unitless aircraft:crew_and_payload:design:num_business_class,0,unitless aircraft:crew_and_payload:design:num_first_class,11,unitless +aircraft:crew_and_payload:num_passengers,169,unitless aircraft:crew_and_payload:num_tourist_class,158,unitless +aircraft:crew_and_payload:num_business_class,0,unitless +aircraft:crew_and_payload:num_first_class,11,unitless + aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless aircraft:crew_and_payload:wing_cargo,0.0,lbm aircraft:design:base_area,0.0,ft**2 diff --git a/aviary/subsystems/mass/flops_based/wing_detailed.py b/aviary/subsystems/mass/flops_based/wing_detailed.py index 174e0944c..906e33b23 100644 --- a/aviary/subsystems/mass/flops_based/wing_detailed.py +++ b/aviary/subsystems/mass/flops_based/wing_detailed.py @@ -149,7 +149,6 @@ def compute(self, inputs, outputs): chord_int_stations[1:] * (2*load_intensity[1:] + load_intensity[:-1])) / 6 el = np.sum(del_load) - print('el', el) del_moment = dy**2 * ( chord_int_stations[:-1] * (load_intensity[:-1]+load_intensity[1:]) + @@ -173,7 +172,6 @@ def compute(self, inputs, outputs): bma = total_moment * csw / (chord_int_stations[:-1] * tc_int_stations[:-1]) pm = np.sum((bma[:-1] + bma[1:]) * dy[:-1] * 0.5) - print('pm',pm) # s = np.sum((chord_int_stations[:-1] + chord_int_stations[1:]) * dy * 0.5) @@ -187,7 +185,6 @@ def compute(self, inputs, outputs): bt = btb / (ar**(0.25*fstrt) * (1.0 + (0.5*faert - 0.16*fstrt) * sa**2 + 0.03*caya * (1.0-0.5*faert)*sa)) - print('BT', bt) outputs[Aircraft.Wing.BENDING_FACTOR] = bt diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index 9273fb0db..f4d7b8126 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -1332,7 +1332,7 @@ }, units='unitless', desc='ratio of maximum landing mass to maximum takeoff mass', - default_value=None, + default_value=0.9, ) add_meta_data( From d8bfcab4fc80141f4270e94e2ae379f3be473b14 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 5 Sep 2024 13:38:06 -0400 Subject: [PATCH 050/113] FwFm example running, but dymos error at end --- .../run_multimission_example_FwFm.py | 284 ++++++++++++++++++ .../aircraft_for_bench_FwFm_deadhead.csv | 162 ++++++++++ 2 files changed, 446 insertions(+) create mode 100644 aviary/examples/multi_missions/run_multimission_example_FwFm.py create mode 100644 aviary/models/test_aircraft/aircraft_for_bench_FwFm_deadhead.csv diff --git a/aviary/examples/multi_missions/run_multimission_example_FwFm.py b/aviary/examples/multi_missions/run_multimission_example_FwFm.py new file mode 100644 index 000000000..5ed809d6e --- /dev/null +++ b/aviary/examples/multi_missions/run_multimission_example_FwFm.py @@ -0,0 +1,284 @@ +""" +authors: Jatin Soni, Eliot Aretskin +Multi Mission Optimization Example using Aviary + +For the deadhead mission: +aircraft:crew_and_payload:num_passengers,0,unitless +aircraft:crew_and_payload:num_tourist_class,0,unitless +aircraft:crew_and_payload:num_first_class,0,unitless + +""" +from aviary.api import SubsystemBuilderBase +from aviary.subsystems.mass.flops_based.furnishings import TransportFurnishingsGroupMass +import sys +import warnings +import dymos as dm +import numpy as np +from os.path import join +import matplotlib.pyplot as plt + +import openmdao.api as om +import aviary.api as av +from aviary.variable_info.enums import ProblemType +from aviary.variable_info.variables import Mission, Aircraft + +from aviary.examples.example_phase_info import phase_info + +# fly the same mission twice with two different passenger loads +phase_info_primary = phase_info +phase_info_deadhead = phase_info + + +class MultiMissionProblem(om.Problem): + def __init__(self, planes, phase_infos, weights): + super().__init__() + self.num_missions = len(planes) + # phase infos and planes length must match - this maybe unnecessary if + # different planes (payloads) fly same mission (say pax vs cargo) + # or if same payload flies 2 different missions (altitude/mach differences) + if self.num_missions != len(phase_infos): + raise Exception("Length of planes and phase_infos must be the same!") + + # if fewer weights than planes are provided, assign equal weights for all planes + if len(weights) < self.num_missions: + weights = [1]*self.num_missions + # if more weights than planes, raise exception + elif len(weights) > self.num_missions: + raise Exception("Length of weights cannot exceed length of planes!") + self.weights = weights + self.phase_infos = phase_infos + + self.group_prefix = 'group' + self.probs = [] + self.fuel_vars = [] + self.phases = {} + # define individual aviary problems + for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): + prob = av.AviaryProblem() + prob.load_inputs(plane, phase_info) + prob.check_and_preprocess_inputs() + prob.add_pre_mission_systems() + prob.add_phases() + prob.add_post_mission_systems() + prob.link_phases() + + # alternate prevents use of equality constraint b/w design and summary gross mass + prob.problem_type = ProblemType.ALTERNATE + prob.add_design_variables() + self.probs.append(prob) + # phase names for each traj (can be used later to make plots/print outputs) + self.phases[f"{self.group_prefix}_{i}"] = list(prob.traj._phases.keys()) + + # design range and gross mass are promoted, these are Max Range/Max Takeoff Mass + # and must be the same for each aviary problem. Subsystems within aviary are sized + # using these - empty mass is same across all aviary problems. + # the fuel objective is also promoted since that's used in the compound objective + promoted_name = f"{self.group_prefix}_{i}_fuelobj" + self.fuel_vars.append(promoted_name) + self.model.add_subsystem( + self.group_prefix + f'_{i}', prob.model, + promotes_inputs=[Mission.Design.GROSS_MASS, + Mission.Design.RANGE, + Aircraft.Wing.SPAN, + Aircraft.Wing.AREA], + promotes_outputs=[(Mission.Objectives.FUEL, promoted_name)]) + + def add_design_variables(self): + self.model.add_design_var(Mission.Design.GROSS_MASS, + lower=10., upper=900e3, units='lbm') + self.model.add_design_var(Aircraft.Wing.SPAN, lower=100., upper=500., units='ft') + self.model.add_design_var(Aircraft.Wing.AREA, lower=10., + upper=1e6, units='ft**2') + + def add_driver(self): + self.driver = om.pyOptSparseDriver() + self.driver.options["optimizer"] = "SLSQP" + self.driver.declare_coloring() + # linear solver causes nan entry error for landing to takeoff mass ratio param + # self.model.linear_solver = om.DirectSolver() + + def add_objective(self): + # weights are normalized - e.g. for given weights 3:1, the normalized + # weights are 0.75:0.25 + weights = [float(weight/sum(self.weights)) for weight in self.weights] + weighted_str = "+".join([f"{fuelobj}*{weight}" + for fuelobj, weight in zip(self.fuel_vars, weights)]) + # weighted_str looks like: fuel_0 * weight[0] + fuel_1 * weight[1] + # note that the fuel objective itself is the base aviary fuel objective + # which is also a function of climb time becuse climb is not very sensitive to fuel + + # adding compound execComp to super problem + self.model.add_subsystem('compound_fuel_burn_objective', om.ExecComp( + "compound = "+weighted_str, has_diag_partials=True), promotes=["compound"]) + self.model.add_objective('compound') + + def setup_wrapper(self): + """Wrapper for om.Problem setup with warning ignoring and setting options""" + for prob in self.probs: + prob.model.options['aviary_options'] = prob.aviary_inputs + prob.model.options['aviary_metadata'] = prob.meta_data + prob.model.options['phase_info'] = prob.phase_info + + # Aviary's problem setup wrapper uses these ignored warnings to suppress + # some warnings related to variable promotion. Replicating that here with + # setup for the super problem + with warnings.catch_warnings(): + warnings.simplefilter("ignore", om.OpenMDAOWarning) + warnings.simplefilter("ignore", om.PromotionWarning) + self.setup(check='all') + + def run(self): + self.model.set_solver_print(0) + dm.run_problem(self, make_plots=True) + + def get_design_range(self): + """Finds the longest mission and sets its range as the design range for all + Aviary problems. Used within Aviary for sizing subsystems (avionics and AC).""" + design_range = [] + for phase_info in self.phase_infos: + design_range.append(phase_info['post_mission'] + ['target_range'][0]) # TBD add units + design_range_min = np.min(design_range) + design_range_max = np.max(design_range) + return design_range_max, design_range_min # design_range_min + + def create_timeseries_plots(self, plotvars=[], show=True): + """ + Temporary create plots manually because graphing won't work for dual-trajectories. + Creates timeseries plots for any variables within timeseries. Specify variables + and units by setting plotvars = [('altitude','ft')]. Any number of vars can be added. + """ + plt.figure() + for plotidx, (var, unit) in enumerate(plotvars): + plt.subplot(int(np.ceil(len(plotvars)/2)), 2, plotidx+1) + for i in range(self.num_missions): + time = np.array([]) + yvar = np.array([]) + # this loop concatenates data from all phases + for phase in self.phases[f"{self.group_prefix}_{i}"]: + rawt = self.get_val( + f"{self.group_prefix}_{i}.traj.{phase}.timeseries.time", + units='s') + rawy = self.get_val( + f"{self.group_prefix}_{i}.traj.{phase}.timeseries.{var}", + units=unit) + time = np.hstack([time, np.ndarray.flatten(rawt)]) + yvar = np.hstack([yvar, np.ndarray.flatten(rawy)]) + plt.plot(time, yvar, linewidth=self.num_missions-i) + plt.xlabel("Time (s)") + plt.ylabel(f"{var.title()} ({unit})") + plt.grid() + plt.figlegend([f"Plane {i}" for i in range(self.num_missions)]) + if show: + plt.show() + + def create_payload_range_plot(self, show=True): + """Creates payload range diagram for the super problem. Appends a point for max payload + and 0 range. """ + payloads = [] + ranges = [] + for i in range(self.num_missions): + ref = f"{self.group_prefix}_{i}" + payloads.append( + self.get_val( + f"{ref}.{Aircraft.CrewPayload.CARGO_MASS}", units='lbm')) + lastphase = self.phases[ref][-1] + ranges.append( + self.get_val( + f"{ref}.traj.{lastphase}.timeseries.distance", + units='nmi', indices=-1)[0]) + payloads, ranges = zip(*sorted(zip(payloads, ranges))) + payloads, ranges = list(payloads), list(ranges) + payloads.append(payloads[-1]) + ranges.append(0) + plt.figure() + plt.plot(ranges, payloads) + plt.xlabel("Range (nmi)") + plt.ylabel("Payload (lbm)") + plt.grid() + if show: + plt.show() + + def print_vars(self, vars=[]): + """Specify vars with name and unit in a tuple, e.g. vars = [ (Mission.Summary.FUEL_BURNED, 'lbm') ]""" + + print("\n\n=========================\n") + print(f"{'':40}", end=': ') + for i in range(self.num_missions): + name = f"Mission {i}" + print(f"{name:^30}", end='| ') + print() + for var, unit in vars: + varname = f"Variable: {var.replace(':','.').upper()}" + print(f"{varname:40}", end=": ") + for i in range(self.num_missions): + val = self.get_val(f'group_{i}.{var}', units=unit)[0] + printstatement = f"{val} ({unit})" + print(f"{printstatement:^30}", end="| ") + print() + + +def FwFm_example(makeN2=False): + plane_dir = 'models/test_aircraft/' + planes = ['aircraft_for_bench_FwFm.csv', 'aircraft_for_bench_FwFm_deadhead.csv'] + planes = [join(plane_dir, plane) for plane in planes] + phase_infos = [phase_info_primary, + phase_info_deadhead] + optalt, optmach = False, False + for phaseinfo in phase_infos: + for key in phaseinfo.keys(): + if "user_options" in phaseinfo[key].keys(): + phaseinfo[key]["user_options"]["optimize_mach"] = optmach + phaseinfo[key]["user_options"]["optimize_altitude"] = optalt + + # how much each mission should be valued by the optimizer, larger numbers = more significance + weights = [1, 1] + + super_prob = MultiMissionProblem(planes, phase_infos, weights) + super_prob.add_driver() + super_prob.add_design_variables() + super_prob.add_objective() + # set input default to prevent error, value doesn't matter since set val is used later + super_prob.model.set_input_defaults(Mission.Design.RANGE, val=1.) + super_prob.setup_wrapper() + super_prob.set_val(Mission.Design.RANGE, super_prob.get_design_range()[0]) + + for i, prob in enumerate(super_prob.probs): + prob.set_initial_guesses(super_prob, super_prob.group_prefix+f"_{i}.") + + if makeN2: + from createN2 import createN2 + createN2(__file__, super_prob) + + super_prob.run() + printoutputs = [(Aircraft.Design.EMPTY_MASS, 'lbm'), + (Mission.Summary.FUEL_BURNED, 'lbm'), + (Mission.Summary.GROSS_MASS, 'lbm'), + (Aircraft.Wing.SPAN, 'ft'), + (Aircraft.Wing.AREA, 'ft**2'), + (Aircraft.LandingGear.MAIN_GEAR_MASS, 'lbm'), + (Aircraft.LandingGear.NOSE_GEAR_MASS, 'lbm'), + (Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, 'unitless'), + (Mission.Summary.CRUISE_MACH, 'unitless'), + (Aircraft.CrewPayload.NUM_PASSENGERS, 'unitless'), + (Aircraft.CrewPayload.Design.NUM_PASSENGERS, 'unitless')] + super_prob.print_vars(vars=printoutputs) + + plotvars = [('altitude', 'ft'), + ('mass', 'lbm'), + ('drag', 'lbf'), + ('distance', 'nmi'), + ('throttle', 'unitless'), + ('mach', 'unitless')] + super_prob.create_timeseries_plots(plotvars=plotvars, show=False) + + super_prob.create_payload_range_plot(show=False) + plt.show() + + return super_prob + + +if __name__ == '__main__': + makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False + + super_prob = FwFm_example(makeN2=makeN2) diff --git a/aviary/models/test_aircraft/aircraft_for_bench_FwFm_deadhead.csv b/aviary/models/test_aircraft/aircraft_for_bench_FwFm_deadhead.csv new file mode 100644 index 000000000..1e61f864a --- /dev/null +++ b/aviary/models/test_aircraft/aircraft_for_bench_FwFm_deadhead.csv @@ -0,0 +1,162 @@ +aircraft:air_conditioning:mass_scaler,1.0,unitless +aircraft:anti_icing:mass_scaler,1.0,unitless +aircraft:apu:mass_scaler,1.1,unitless +aircraft:avionics:mass_scaler,1.2,unitless +aircraft:canard:area,0.0,ft**2 +aircraft:canard:aspect_ratio,0.0,unitless +aircraft:canard:thickness_to_chord,0.0,unitless +aircraft:crew_and_payload:baggage_mass_per_passenger,45.0,lbm +aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless +aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:mass_per_passenger,180.0,lbm +aircraft:crew_and_payload:misc_cargo,0.0,lbm +aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless +aircraft:crew_and_payload:num_flight_attendants,3,unitless +aircraft:crew_and_payload:num_flight_crew,2,unitless +aircraft:crew_and_payload:num_galley_crew,0,unitless + +aircraft:crew_and_payload:design:num_passengers,169,unitless +aircraft:crew_and_payload:design:num_tourist_class,158,unitless +aircraft:crew_and_payload:design:num_business_class,0,unitless +aircraft:crew_and_payload:design:num_first_class,11,unitless +aircraft:crew_and_payload:num_passengers,0,unitless +aircraft:crew_and_payload:num_tourist_class,0,unitless +aircraft:crew_and_payload:num_business_class,0,unitless +aircraft:crew_and_payload:num_first_class,0,unitless + +aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless +aircraft:crew_and_payload:wing_cargo,0.0,lbm +aircraft:design:base_area,0.0,ft**2 +aircraft:design:empty_mass_margin_scaler,0.0,unitless +aircraft:design:lift_dependent_drag_coeff_factor,0.909839381134961,unitless +aircraft:design:touchdown_mass,152800.0,lbm +aircraft:design:reserve_fuel_additional,3000.,lbm +aircraft:design:subsonic_drag_coeff_factor,1.0,unitless +aircraft:design:supersonic_drag_coeff_factor,1.0,unitless +aircraft:design:use_alt_mass,False,unitless +aircraft:design:zero_lift_drag_coeff_factor,0.930890028006548,unitless +aircraft:electrical:mass_scaler,1.25,unitless +aircraft:engine:additional_mass_fraction,0.,unitless +aircraft:engine:constant_fuel_consumption,0.,lbm/h +aircraft:engine:data_file,models/engines/turbofan_28k.deck,unitless +aircraft:engine:flight_idle_thrust_fraction,0.0,unitless +aircraft:engine:flight_idle_max_fraction,1.0,unitless +aircraft:engine:flight_idle_min_fraction,0.08,unitless +aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless +aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless +aircraft:engine:generate_flight_idle,True,unitless +aircraft:engine:geopotential_alt,False,unitless +aircraft:engine:ignore_negative_thrust,False,unitless +aircraft:engine:interpolation_method,slinear,unitless +aircraft:engine:mass_scaler,1.15,unitless +aircraft:engine:mass,7400,lbm +aircraft:engine:num_engines,2,unitless +aircraft:engine:num_fuselage_engines,0,unitless +aircraft:engine:num_wing_engines,2,unitless +aircraft:engine:reference_mass,7400,lbm +aircraft:engine:reference_sls_thrust,28928.1,lbf +aircraft:engine:scale_mass,True,unitless +aircraft:engine:scale_performance,True,unitless +aircraft:engine:scaled_sls_thrust,28928.1,lbf +aircraft:engine:subsonic_fuel_flow_scaler,1.,unitless +aircraft:engine:supersonic_fuel_flow_scaler,1.,unitless +aircraft:engine:thrust_reversers_mass_scaler,0.0,unitless +aircraft:engine:wing_locations,[0.26869218],unitless +aircraft:fins:area,0.0,ft**2 +aircraft:fins:mass_scaler,1.0,unitless +aircraft:fins:mass,0.0,lbm +aircraft:fins:num_fins,0,unitless +aircraft:fins:taper_ratio,10.0,unitless +aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm +aircraft:fuel:density_ratio,1.0,unitless +aircraft:fuel:fuel_system_mass_scaler,1.0,unitless +aircraft:fuel:fuselage_fuel_capacity,0.0,lbm +aircraft:fuel:num_tanks,7,unitless +aircraft:fuel:total_capacity,45694.0,lbm +aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless +aircraft:furnishings:mass_scaler,1.1,unitless +aircraft:fuselage:length,128.0,ft +aircraft:fuselage:mass_scaler,1.05,unitless +aircraft:fuselage:max_height,13.17,ft +aircraft:fuselage:max_width,12.33,ft +aircraft:fuselage:military_cargo_floor,False,unitless +aircraft:fuselage:num_fuselages,1,unitless +aircraft:fuselage:passenger_compartment_length,85.5,ft +aircraft:fuselage:planform_area,1578.24,ft**2 +aircraft:fuselage:wetted_area_scaler,1.0,unitless +aircraft:fuselage:wetted_area,4158.62,ft**2 +aircraft:horizontal_tail:area,355.0,ft**2 +aircraft:horizontal_tail:aspect_ratio,6.0,unitless +aircraft:horizontal_tail:mass_scaler,1.2,unitless +aircraft:horizontal_tail:taper_ratio,0.22,unitless +aircraft:horizontal_tail:thickness_to_chord,0.125,unitless +aircraft:horizontal_tail:vertical_tail_fraction,0.0,unitless +aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless +aircraft:horizontal_tail:wetted_area,592.65,ft**2 +aircraft:hydraulics:mass_scaler,1.0,unitless +aircraft:hydraulics:system_pressure,3000,psi +aircraft:instruments:mass_scaler,1.25,unitless +aircraft:landing_gear:carrier_based,False,unitless +aircraft:landing_gear:main_gear_mass_scaler,1.1,unitless +aircraft:landing_gear:main_gear_oleo_length,102.0,inch +aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless +aircraft:landing_gear:nose_gear_oleo_length,67.0,inch +aircraft:nacelle:avg_diameter,7.94,ft +aircraft:nacelle:avg_length,12.3,ft +aircraft:nacelle:mass_scaler,1.0,unitless +aircraft:nacelle:wetted_area_scaler,1.0,unitless +aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 +aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless +aircraft:propulsion:misc_mass_scaler,1.0,unitless +aircraft:vertical_tail:area,284.0,ft**2 +aircraft:vertical_tail:aspect_ratio,1.75,unitless +aircraft:vertical_tail:mass_scaler,1.0,unitless +aircraft:vertical_tail:num_tails,1,unitless +aircraft:vertical_tail:taper_ratio,0.33,unitless +aircraft:vertical_tail:thickness_to_chord,0.1195,unitless +aircraft:vertical_tail:wetted_area_scaler,1.0,unitless +aircraft:vertical_tail:wetted_area,581.13,ft**2 +aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless +aircraft:wing:airfoil_technology,1.92669766647637,unitless +aircraft:wing:area,1370.0,ft**2 +aircraft:wing:aspect_ratio,11.22091,unitless +aircraft:wing:bending_mass_scaler,1.0,unitless +aircraft:wing:chord_per_semispan,0.31,0.23,0.084,unitless +aircraft:wing:composite_fraction,0.2,unitless +aircraft:wing:control_surface_area,137,ft**2 +aircraft:wing:control_surface_area_ratio,0.1,unitless +aircraft:wing:glove_and_bat,134.0,ft**2 +aircraft:wing:input_station_dist,0.,0.2759,0.9367,unitless +aircraft:wing:load_distribution_control,2.0,unitless +aircraft:wing:load_fraction,1.0,unitless +aircraft:wing:load_path_sweep_dist,0.,22.,deg +aircraft:wing:mass_scaler,1.23,unitless +aircraft:wing:max_camber_at_70_semispan,0.0,unitless +aircraft:wing:misc_mass_scaler,1.0,unitless +aircraft:wing:num_integration_stations,50,unitless +aircraft:wing:shear_control_mass_scaler,1.0,unitless +aircraft:wing:span_efficiency_reduction,False,unitless +aircraft:wing:span,117.83,ft +aircraft:wing:strut_bracing_factor,0.0,unitless +aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless +aircraft:wing:sweep,25.0,deg +aircraft:wing:taper_ratio,0.278,unitless +aircraft:wing:thickness_to_chord_dist,0.145,0.115,0.104,unitless +aircraft:wing:thickness_to_chord,0.13,unitless +aircraft:wing:ultimate_load_factor,3.75,unitless +aircraft:wing:var_sweep_mass_penalty,0.0,unitless +aircraft:wing:wetted_area_scaler,1.0,unitless +aircraft:wing:wetted_area,2396.56,ft**2 +mission:constraints:max_mach,0.785,unitless +mission:design:cruise_altitude,35000,ft +mission:design:gross_mass,175400.0,lbm +mission:design:range,3500,NM +mission:design:thrust_takeoff_per_eng,28928.1,lbf +mission:landing:lift_coefficient_max,2.0,unitless +mission:summary:cruise_mach,0.785,unitless +mission:summary:fuel_flow_scaler,1.0,unitless +mission:takeoff:fuel_simple,577,lbm +mission:takeoff:lift_coefficient_max,3.0,unitless +mission:takeoff:lift_over_drag,17.354,unitless +settings:equations_of_motion,height_energy +settings:mass_method,FLOPS \ No newline at end of file From b6c99c1ee90fe3df456229c9446808dae4e54a2f Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 5 Sep 2024 13:45:57 -0400 Subject: [PATCH 051/113] removed comments --- .../run_multimission_example.py | 101 ------------------ 1 file changed, 101 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example.py b/aviary/examples/multi_missions/run_multimission_example.py index a289e63a4..d7e851f09 100644 --- a/aviary/examples/multi_missions/run_multimission_example.py +++ b/aviary/examples/multi_missions/run_multimission_example.py @@ -277,104 +277,3 @@ def C5_example(makeN2=False): makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False super_prob = C5_example(makeN2=makeN2) - -""" -1:1:1 and 5:1:1 and 1:1:5 and 1:5:1 -Variable: aircraft:design:empty_mass - Plane 0: 377110.8519657982 (lbm), Plane 1: 377110.8519657982 (lbm), Plane 2: 377110.8519657982 (lbm), -Variable: mission:summary:fuel_burned - Plane 0: 167530.46091225138 (lbm), Plane 1: 308428.65141334233 (lbm), Plane 2: 412689.6603555365 (lbm), -Variable: mission:summary:gross_mass - Plane 0: 599904.1437916472 (lbm), Plane 1: 711227.3342927382 (lbm), Plane 2: 793323.6057604996 (lbm), -Variable: aircraft:wing:span - Plane 0: 235.7734017415966 (ft), Plane 1: 235.7734017415966 (ft), Plane 2: 235.7734017415966 (ft), -Variable: aircraft:wing:area - Plane 0: 6106.843788863166 (ft**2), Plane 1: 6106.843788863166 (ft**2), Plane 2: 6106.843788863166 (ft**2), - -1:1:5 - -""" - -""" -inter payload: 100k -Variable: aircraft:design:empty_mass - Plane 0: 374179.5394606042 (lbm) - Plane 1: 374179.5394606042 (lbm) - Plane 2: 374179.5394606042 (lbm) -Variable: mission:summary:fuel_burned - Plane 0: 165739.44323952997 (lbm) - Plane 1: 306588.0148270305 (lbm) - Plane 2: 411012.49583405076 (lbm) -Variable: mission:summary:gross_mass - Plane 0: 595188.3345483424 (lbm) - Plane 1: 702786.9061358428 (lbm) - Plane 2: 788721.6496684301 (lbm) - -inter payload: 140k -Variable: aircraft:design:empty_mass - Plane 0: 374179.53946059936 (lbm) - Plane 1: 374179.53946059936 (lbm) - Plane 2: 374179.53946059936 (lbm) -Variable: mission:summary:fuel_burned - Plane 0: 165739.44340813044 (lbm) - Plane 1: 306588.0148359792 (lbm) - Plane 2: 411012.4960230509 (lbm) -Variable: mission:summary:gross_mass - Plane 0: 595188.3347169379 (lbm) - Plane 1: 710136.9061447867 (lbm) - Plane 2: 788721.6498574257 (lbm) - -140k inter, 301k max -Variable: aircraft:design:empty_mass - Plane 0: 374179.5394605969 (lbm) - Plane 1: 374179.5394605969 (lbm) - Plane 2: 374179.5394605969 (lbm) -Variable: mission:summary:fuel_burned - Plane 0: 165739.44397328247 (lbm) - Plane 1: 306588.01484213956 (lbm) - Plane 2: 411012.4961383113 (lbm) -Variable: mission:summary:gross_mass - Plane 0: 598863.3352823037 (lbm) - Plane 1: 710136.9061509445 (lbm) - Plane 2: 788721.6499726834 (lbm) - -140k inter, 301k max, 10k ferry -Variable: aircraft:design:empty_mass - Plane 0: 374179.5394605957 (lbm) - Plane 1: 374179.5394605957 (lbm) - Plane 2: 374179.5394605957 (lbm) -Variable: mission:summary:fuel_burned - Plane 0: 165739.4440247023 (lbm) - Plane 1: 306588.01484336343 (lbm) - Plane 2: 411012.49619538186 (lbm) -Variable: mission:summary:gross_mass - Plane 0: 598863.3353337225 (lbm) - Plane 1: 710136.9061521672 (lbm) - Plane 2: 790586.3875041857 (lbm) -""" - -""" -optimize mach only: optimize both mach and alt: optimize neither mach or altitude -Variable: aircraft:design:empty_mass Variable: aircraft:design:empty_mass Variable: aircraft:design:empty_mass - Plane 0: 326047.42156711605 (lbm) Plane 0: 390475.71469928196 (lbm) Plane 0: 371320.23571631836 (lbm) - Plane 1: 326047.42156711605 (lbm) Plane 1: 390475.71469928196 (lbm) Plane 1: 371320.23571631836 (lbm) - Plane 2: 326047.42156711605 (lbm) Plane 2: 390475.71469928196 (lbm) Plane 2: 371320.23571631836 (lbm) -Variable: mission:summary:fuel_burned Variable: mission:summary:fuel_burned Variable: mission:summary:fuel_burned - Plane 0: 175717.28062873823 (lbm) Plane 0: 178314.99288207013 (lbm) Plane 0: 167946.2102766974 (lbm) - Plane 1: 306419.71885746776 (lbm) Plane 1: 325789.9474922766 (lbm) Plane 1: 309094.299337939 (lbm) - Plane 2: 394791.91474366543 (lbm) Plane 2: 429716.0286375711 (lbm) Plane 2: 413746.64501453174 (lbm) -Variable: mission:summary:gross_mass Variable: mission:summary:gross_mass Variable: mission:summary:gross_mass - Plane 0: 557034.0540440837 (lbm) Plane 0: 624060.059429561 (lbm) Plane 0: 594535.797841224 (lbm) - Plane 1: 658161.4922728132 (lbm) Plane 1: 741960.0140397676 (lbm) Plane 1: 706108.8869024655 (lbm) - Plane 2: 724368.9506845778 (lbm) Plane 2: 823721.3577106291 (lbm) Plane 2: 788596.4951046254 (lbm) -Variable: aircraft:wing:span Variable: aircraft:wing:span Variable: aircraft:wing:span - Plane 0: 54.707828078624665 (ft) Plane 0: 287.14946969690783 (ft) Plane 0: 211.8281919608065 (ft) - Plane 1: 54.707828078624665 (ft) Plane 1: 287.14946969690783 (ft) Plane 1: 211.8281919608065 (ft) - Plane 2: 54.707828078624665 (ft) Plane 2: 287.14946969690783 (ft) Plane 2: 211.8281919608065 (ft) -Variable: aircraft:wing:aspect_ratio Variable: aircraft:wing:aspect_ratio Variable: aircraft:wing:aspect_ratio - Plane 0: 6.263196240285538 (unitless) Plane 0: 6.931291416800268 (unitless) Plane 0: 7.576574965501183 (unitless) - Plane 1: 6.263196240285538 (unitless) Plane 1: 6.931291416800268 (unitless) Plane 1: 7.576574965501183 (unitless) - Plane 2: 6.263196240285538 (unitless) Plane 2: 6.931291416800268 (unitless) Plane 2: 7.576574965501183 (unitless) - - -""" From 70b6c4b8cc5b979819d73ba7cc70ddd0a82518c4 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 5 Sep 2024 15:18:57 -0400 Subject: [PATCH 052/113] disabled make plots --- .../multi_missions/run_multimission_example_FwFm.py | 9 +++++---- 1 file changed, 5 insertions(+), 4 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example_FwFm.py b/aviary/examples/multi_missions/run_multimission_example_FwFm.py index 5ed809d6e..eb3c2e141 100644 --- a/aviary/examples/multi_missions/run_multimission_example_FwFm.py +++ b/aviary/examples/multi_missions/run_multimission_example_FwFm.py @@ -129,7 +129,7 @@ def setup_wrapper(self): def run(self): self.model.set_solver_print(0) - dm.run_problem(self, make_plots=True) + dm.run_problem(self, make_plots=False) def get_design_range(self): """Finds the longest mission and sets its range as the design range for all @@ -251,7 +251,9 @@ def FwFm_example(makeN2=False): createN2(__file__, super_prob) super_prob.run() - printoutputs = [(Aircraft.Design.EMPTY_MASS, 'lbm'), + printoutputs = [ + (Mission.Design.GROSS_MASS, 'lbm'), + (Aircraft.Design.EMPTY_MASS, 'lbm'), (Mission.Summary.FUEL_BURNED, 'lbm'), (Mission.Summary.GROSS_MASS, 'lbm'), (Aircraft.Wing.SPAN, 'ft'), @@ -260,8 +262,7 @@ def FwFm_example(makeN2=False): (Aircraft.LandingGear.NOSE_GEAR_MASS, 'lbm'), (Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, 'unitless'), (Mission.Summary.CRUISE_MACH, 'unitless'), - (Aircraft.CrewPayload.NUM_PASSENGERS, 'unitless'), - (Aircraft.CrewPayload.Design.NUM_PASSENGERS, 'unitless')] + (Aircraft.Furnishings.MASS, 'lbm'),] super_prob.print_vars(vars=printoutputs) plotvars = [('altitude', 'ft'), From 721d42780edfd8aa09b008e83a336ec52674619c Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 5 Sep 2024 15:31:54 -0400 Subject: [PATCH 053/113] added list_vars() to show all outputs from final case --- .../examples/multi_missions/run_multimission_example_FwFm.py | 3 +++ 1 file changed, 3 insertions(+) diff --git a/aviary/examples/multi_missions/run_multimission_example_FwFm.py b/aviary/examples/multi_missions/run_multimission_example_FwFm.py index eb3c2e141..d3b011bcc 100644 --- a/aviary/examples/multi_missions/run_multimission_example_FwFm.py +++ b/aviary/examples/multi_missions/run_multimission_example_FwFm.py @@ -283,3 +283,6 @@ def FwFm_example(makeN2=False): makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False super_prob = FwFm_example(makeN2=makeN2) + + super_prob.model.list_vars(val=True, units=True, print_arrays=True) + # https://openmdao.org/newdocs/versions/latest/features/debugging/listing_variables.html?highlight=list_driver_vars From 3b60925e38662bfffc7d623e330e21223a7c5684 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 5 Sep 2024 16:59:03 -0400 Subject: [PATCH 054/113] major changes to update Aircraft.CrewPayload.Design.NUM_PASSENGERS in supporting subsystems --- .../run_multimission_example_FwFm.py | 7 ++++--- .../geometry/gasp_based/fuselage.py | 2 +- .../mass/flops_based/air_conditioning.py | 8 +++---- aviary/subsystems/mass/flops_based/apu.py | 4 ++-- .../subsystems/mass/flops_based/electrical.py | 8 +++---- .../subsystems/mass/flops_based/engine_oil.py | 4 ++-- .../mass/flops_based/passenger_service.py | 4 ++-- .../gasp_based/equipment_and_useful_load.py | 4 ++-- aviary/utils/preprocessors.py | 21 ++++++++++++------- aviary/utils/process_input_decks.py | 2 +- 10 files changed, 35 insertions(+), 29 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example_FwFm.py b/aviary/examples/multi_missions/run_multimission_example_FwFm.py index d3b011bcc..650aed20c 100644 --- a/aviary/examples/multi_missions/run_multimission_example_FwFm.py +++ b/aviary/examples/multi_missions/run_multimission_example_FwFm.py @@ -262,7 +262,8 @@ def FwFm_example(makeN2=False): (Aircraft.LandingGear.NOSE_GEAR_MASS, 'lbm'), (Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, 'unitless'), (Mission.Summary.CRUISE_MACH, 'unitless'), - (Aircraft.Furnishings.MASS, 'lbm'),] + (Aircraft.Furnishings.MASS, 'lbm'), + (Aircraft.CrewPayload.PASSENGER_SERVICE_MASS, 'lbm')] super_prob.print_vars(vars=printoutputs) plotvars = [('altitude', 'ft'), @@ -283,6 +284,6 @@ def FwFm_example(makeN2=False): makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False super_prob = FwFm_example(makeN2=makeN2) - - super_prob.model.list_vars(val=True, units=True, print_arrays=True) + + super_prob.model.group_0.list_vars(val=True, units=True, print_arrays=False) # https://openmdao.org/newdocs/versions/latest/features/debugging/listing_variables.html?highlight=list_driver_vars diff --git a/aviary/subsystems/geometry/gasp_based/fuselage.py b/aviary/subsystems/geometry/gasp_based/fuselage.py index d9d80e0f9..2e33eed7e 100644 --- a/aviary/subsystems/geometry/gasp_based/fuselage.py +++ b/aviary/subsystems/geometry/gasp_based/fuselage.py @@ -57,7 +57,7 @@ def compute(self, inputs, outputs): num_aisle = aviary_options.get_val(Aircraft.Fuselage.NUM_AISLES) aisle_width = aviary_options.get_val(Aircraft.Fuselage.AISLE_WIDTH, units='inch') PAX = self.options['aviary_options'].get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') seat_pitch = aviary_options.get_val(Aircraft.Fuselage.SEAT_PITCH, units='inch') delta_diameter = inputs[Aircraft.Fuselage.DELTA_DIAMETER] diff --git a/aviary/subsystems/mass/flops_based/air_conditioning.py b/aviary/subsystems/mass/flops_based/air_conditioning.py index 98605525e..894ca14dd 100644 --- a/aviary/subsystems/mass/flops_based/air_conditioning.py +++ b/aviary/subsystems/mass/flops_based/air_conditioning.py @@ -37,7 +37,7 @@ def setup_partials(self): def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None): aviary_options: AviaryValues = self.options['aviary_options'] pax = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') scaler = inputs[Aircraft.AirConditioning.MASS_SCALER] avionics_wt = inputs[Aircraft.Avionics.MASS] * GRAV_ENGLISH_LBM @@ -52,7 +52,7 @@ def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None): def compute_partials(self, inputs, J): aviary_options: AviaryValues = self.options['aviary_options'] pax = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') scaler = inputs[Aircraft.AirConditioning.MASS_SCALER] avionics_wt = inputs[Aircraft.Avionics.MASS] * GRAV_ENGLISH_LBM @@ -101,7 +101,7 @@ def setup_partials(self): def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None): aviary_options: AviaryValues = self.options['aviary_options'] num_pax = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') scaler = inputs[Aircraft.AirConditioning.MASS_SCALER] @@ -111,7 +111,7 @@ def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None): def compute_partials(self, inputs, J): aviary_options: AviaryValues = self.options['aviary_options'] num_pax = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') J[Aircraft.AirConditioning.MASS, Aircraft.AirConditioning.MASS_SCALER] = \ 26.0 * num_pax / GRAV_ENGLISH_LBM diff --git a/aviary/subsystems/mass/flops_based/apu.py b/aviary/subsystems/mass/flops_based/apu.py index c4858be1f..3a8fec051 100644 --- a/aviary/subsystems/mass/flops_based/apu.py +++ b/aviary/subsystems/mass/flops_based/apu.py @@ -30,7 +30,7 @@ def setup_partials(self): def compute(self, inputs, outputs): aviary_options: AviaryValues = self.options['aviary_options'] pax = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') scaler = inputs[Aircraft.APU.MASS_SCALER] planform = inputs[Aircraft.Fuselage.PLANFORM_AREA] @@ -40,7 +40,7 @@ def compute(self, inputs, outputs): def compute_partials(self, inputs, J): aviary_options: AviaryValues = self.options['aviary_options'] pax = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') scaler = inputs[Aircraft.APU.MASS_SCALER] planform = inputs[Aircraft.Fuselage.PLANFORM_AREA] diff --git a/aviary/subsystems/mass/flops_based/electrical.py b/aviary/subsystems/mass/flops_based/electrical.py index d3b6e13ff..90f050cbc 100644 --- a/aviary/subsystems/mass/flops_based/electrical.py +++ b/aviary/subsystems/mass/flops_based/electrical.py @@ -33,7 +33,7 @@ def compute(self, inputs, outputs): options: AviaryValues = self.options['aviary_options'] nfuse = options.get_val(Aircraft.Fuselage.NUM_FUSELAGES) ncrew = options.get_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW) - npass = options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + npass = options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') length = inputs[Aircraft.Fuselage.LENGTH] width = inputs[Aircraft.Fuselage.MAX_WIDTH] num_eng = options.get_val(Aircraft.Propulsion.TOTAL_NUM_ENGINES) @@ -48,7 +48,7 @@ def compute_partials(self, inputs, J): options: AviaryValues = self.options['aviary_options'] nfuse = options.get_val(Aircraft.Fuselage.NUM_FUSELAGES) ncrew = options.get_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW) - npass = options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + npass = options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') length = inputs[Aircraft.Fuselage.LENGTH] width = inputs[Aircraft.Fuselage.MAX_WIDTH] num_eng = options.get_val(Aircraft.Propulsion.TOTAL_NUM_ENGINES) @@ -93,7 +93,7 @@ def setup_partials(self): def compute(self, inputs, outputs): aviary_options: AviaryValues = self.options['aviary_options'] npass = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') mass_scaler = inputs[Aircraft.Electrical.MASS_SCALER] outputs[Aircraft.Electrical.MASS] = 16.3 * \ @@ -102,7 +102,7 @@ def compute(self, inputs, outputs): def compute_partials(self, inputs, J): aviary_options: AviaryValues = self.options['aviary_options'] npass = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') J[Aircraft.Electrical.MASS, Aircraft.Electrical.MASS_SCALER] = \ 16.3 * npass / GRAV_ENGLISH_LBM diff --git a/aviary/subsystems/mass/flops_based/engine_oil.py b/aviary/subsystems/mass/flops_based/engine_oil.py index 79cfde263..d82cd8e63 100644 --- a/aviary/subsystems/mass/flops_based/engine_oil.py +++ b/aviary/subsystems/mass/flops_based/engine_oil.py @@ -87,7 +87,7 @@ def setup_partials(self): def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None): aviary_options: AviaryValues = self.options['aviary_options'] pax = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') scaler = inputs[Aircraft.Propulsion.ENGINE_OIL_MASS_SCALER] @@ -97,7 +97,7 @@ def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None): def compute_partials(self, inputs, J): aviary_options: AviaryValues = self.options['aviary_options'] pax = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') J[Aircraft.Propulsion.TOTAL_ENGINE_OIL_MASS, Aircraft.Propulsion.ENGINE_OIL_MASS_SCALER diff --git a/aviary/subsystems/mass/flops_based/passenger_service.py b/aviary/subsystems/mass/flops_based/passenger_service.py index 21c5a5ae2..e379855b3 100644 --- a/aviary/subsystems/mass/flops_based/passenger_service.py +++ b/aviary/subsystems/mass/flops_based/passenger_service.py @@ -132,7 +132,7 @@ def compute( ): aviary_options: AviaryValues = self.options['aviary_options'] passenger_count = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') passenger_service_mass_scaler = \ inputs[Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_SCALER] @@ -146,7 +146,7 @@ def compute( def compute_partials(self, inputs, J, discrete_inputs=None): aviary_options: AviaryValues = self.options['aviary_options'] passenger_count = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') J[ Aircraft.CrewPayload.PASSENGER_SERVICE_MASS, diff --git a/aviary/subsystems/mass/gasp_based/equipment_and_useful_load.py b/aviary/subsystems/mass/gasp_based/equipment_and_useful_load.py index 642bafc27..2749e2cb5 100644 --- a/aviary/subsystems/mass/gasp_based/equipment_and_useful_load.py +++ b/aviary/subsystems/mass/gasp_based/equipment_and_useful_load.py @@ -77,7 +77,7 @@ def setup(self): def compute(self, inputs, outputs): options: AviaryValues = self.options["aviary_options"] - PAX = options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + PAX = options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') smooth = options.get_val( Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, units='unitless') @@ -388,7 +388,7 @@ def compute(self, inputs, outputs): def compute_partials(self, inputs, partials): options = self.options['aviary_options'] - PAX = options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + PAX = options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') smooth = options.get_val( Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, units='unitless') gross_wt_initial = inputs[Mission.Design.GROSS_MASS] * GRAV_ENGLISH_LBM diff --git a/aviary/utils/preprocessors.py b/aviary/utils/preprocessors.py index 290145c39..fb5dd26ff 100644 --- a/aviary/utils/preprocessors.py +++ b/aviary/utils/preprocessors.py @@ -36,14 +36,19 @@ def preprocess_crewpayload(aviary_options: AviaryValues): """ if Aircraft.CrewPayload.NUM_PASSENGERS not in aviary_options: - passenger_count = 0 - for key in (Aircraft.CrewPayload.NUM_FIRST_CLASS, - Aircraft.CrewPayload.NUM_BUSINESS_CLASS, - Aircraft.CrewPayload.NUM_TOURIST_CLASS): - if key in aviary_options: - passenger_count += aviary_options.get_val(key) - if passenger_count == 0: - passenger_count = 1 + if Aircraft.CrewPayload.Design.NUM_PASSENGERS in aviary_options: + # Set the num_passengers to the designed number of passengers + passenger_count = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) + else: + # sum up the number of passengers + passenger_count = 0 + for key in (Aircraft.CrewPayload.NUM_FIRST_CLASS, + Aircraft.CrewPayload.NUM_BUSINESS_CLASS, + Aircraft.CrewPayload.NUM_TOURIST_CLASS): + if key in aviary_options: + passenger_count += aviary_options.get_val(key) + if passenger_count == 0: + passenger_count = 1 aviary_options.set_val( Aircraft.CrewPayload.NUM_PASSENGERS, passenger_count) diff --git a/aviary/utils/process_input_decks.py b/aviary/utils/process_input_decks.py index 2d9edcc68..a27e34f18 100644 --- a/aviary/utils/process_input_decks.py +++ b/aviary/utils/process_input_decks.py @@ -293,7 +293,7 @@ def initial_guessing(aircraft_values: AviaryValues, initial_guesses, engine_buil Updated aircraft values and initial guesses. """ problem_type = aircraft_values.get_val(Settings.PROBLEM_TYPE) - num_pax = aircraft_values.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) + num_pax = aircraft_values.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) reserve_val = aircraft_values.get_val( Aircraft.Design.RESERVE_FUEL_ADDITIONAL, units='lbm') reserve_frac = aircraft_values.get_val( From 31abe1e990c30a200f9a34962197e3f9dbf8b6a2 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Fri, 6 Sep 2024 10:38:50 -0400 Subject: [PATCH 055/113] added a few more printed outputs at end of mission --- .../run_multimission_example.py | 28 +++++++++++-------- .../run_multimission_example_FwFm.py | 26 +++++++++-------- .../mass/flops_based/passenger_service.py | 12 ++++---- 3 files changed, 36 insertions(+), 30 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example.py b/aviary/examples/multi_missions/run_multimission_example.py index d7e851f09..7942c0ffb 100644 --- a/aviary/examples/multi_missions/run_multimission_example.py +++ b/aviary/examples/multi_missions/run_multimission_example.py @@ -123,7 +123,7 @@ def setup_wrapper(self): def run(self): self.model.set_solver_print(0) - dm.run_problem(self, make_plots=True) + dm.run_problem(self, make_plots=False) def get_design_range(self): """Finds the longest mission and sets its range as the design range for all @@ -246,17 +246,21 @@ def C5_example(makeN2=False): createN2(__file__, super_prob) super_prob.run() - printoutputs = [(Aircraft.Design.EMPTY_MASS, 'lbm'), - (Mission.Design.GROSS_MASS, 'lbm'), - (Mission.Summary.FUEL_BURNED, 'lbm'), - (Mission.Summary.GROSS_MASS, 'lbm'), - (Aircraft.Wing.SPAN, 'ft'), - (Aircraft.Wing.AREA, 'ft**2'), - (Aircraft.LandingGear.MAIN_GEAR_MASS, 'lbm'), - (Aircraft.LandingGear.NOSE_GEAR_MASS, 'lbm'), - (Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, 'unitless'), - (Mission.Summary.CRUISE_MACH, 'unitless'), - (Aircraft.Design.TOUCHDOWN_MASS, 'lbm')] + printoutputs = [ + (Mission.Design.GROSS_MASS, 'lbm'), + (Aircraft.Design.EMPTY_MASS, 'lbm'), + (Mission.Summary.GROSS_MASS, 'lbm'), + (Mission.Summary.FUEL_BURNED, 'lbm'), + (Mission.Design.FUEL_MASS, 'lbm'), + (Mission.Summary.TOTAL_FUEL_MASS, 'lbm'), + (Aircraft.Wing.SPAN, 'ft'), + (Aircraft.Wing.AREA, 'ft**2'), + (Aircraft.LandingGear.MAIN_GEAR_MASS, 'lbm'), + (Aircraft.LandingGear.NOSE_GEAR_MASS, 'lbm'), + (Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, 'unitless'), + (Mission.Summary.CRUISE_MACH, 'unitless'), + (Aircraft.Furnishings.MASS, 'lbm'), + (Aircraft.CrewPayload.PASSENGER_SERVICE_MASS, 'lbm')] super_prob.print_vars(vars=printoutputs) plotvars = [('altitude', 'ft'), diff --git a/aviary/examples/multi_missions/run_multimission_example_FwFm.py b/aviary/examples/multi_missions/run_multimission_example_FwFm.py index 650aed20c..68ad4515c 100644 --- a/aviary/examples/multi_missions/run_multimission_example_FwFm.py +++ b/aviary/examples/multi_missions/run_multimission_example_FwFm.py @@ -232,7 +232,7 @@ def FwFm_example(makeN2=False): phaseinfo[key]["user_options"]["optimize_altitude"] = optalt # how much each mission should be valued by the optimizer, larger numbers = more significance - weights = [1, 1] + weights = [.9, 0.1] super_prob = MultiMissionProblem(planes, phase_infos, weights) super_prob.add_driver() @@ -254,16 +254,18 @@ def FwFm_example(makeN2=False): printoutputs = [ (Mission.Design.GROSS_MASS, 'lbm'), (Aircraft.Design.EMPTY_MASS, 'lbm'), - (Mission.Summary.FUEL_BURNED, 'lbm'), - (Mission.Summary.GROSS_MASS, 'lbm'), - (Aircraft.Wing.SPAN, 'ft'), - (Aircraft.Wing.AREA, 'ft**2'), - (Aircraft.LandingGear.MAIN_GEAR_MASS, 'lbm'), - (Aircraft.LandingGear.NOSE_GEAR_MASS, 'lbm'), - (Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, 'unitless'), - (Mission.Summary.CRUISE_MACH, 'unitless'), - (Aircraft.Furnishings.MASS, 'lbm'), - (Aircraft.CrewPayload.PASSENGER_SERVICE_MASS, 'lbm')] + (Mission.Summary.GROSS_MASS, 'lbm'), + (Mission.Summary.FUEL_BURNED, 'lbm'), + (Mission.Design.FUEL_MASS, 'lbm'), + (Mission.Summary.TOTAL_FUEL_MASS, 'lbm'), + (Aircraft.Wing.SPAN, 'ft'), + (Aircraft.Wing.AREA, 'ft**2'), + (Aircraft.LandingGear.MAIN_GEAR_MASS, 'lbm'), + (Aircraft.LandingGear.NOSE_GEAR_MASS, 'lbm'), + (Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, 'unitless'), + (Mission.Summary.CRUISE_MACH, 'unitless'), + (Aircraft.Furnishings.MASS, 'lbm'), + (Aircraft.CrewPayload.PASSENGER_SERVICE_MASS, 'lbm')] super_prob.print_vars(vars=printoutputs) plotvars = [('altitude', 'ft'), @@ -285,5 +287,5 @@ def FwFm_example(makeN2=False): super_prob = FwFm_example(makeN2=makeN2) - super_prob.model.group_0.list_vars(val=True, units=True, print_arrays=False) + # super_prob.model.group_1.list_vars(val=True, units=True, print_arrays=False) # https://openmdao.org/newdocs/versions/latest/features/debugging/listing_variables.html?highlight=list_driver_vars diff --git a/aviary/subsystems/mass/flops_based/passenger_service.py b/aviary/subsystems/mass/flops_based/passenger_service.py index e379855b3..0559c6276 100644 --- a/aviary/subsystems/mass/flops_based/passenger_service.py +++ b/aviary/subsystems/mass/flops_based/passenger_service.py @@ -46,13 +46,13 @@ def setup_partials(self): def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None): aviary_options: AviaryValues = self.options['aviary_options'] - first_class_count = aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS) + first_class_count = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) business_class_count = \ - aviary_options.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS) + aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) tourist_class_count = \ - aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS) + aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS) design_range = inputs[Mission.Design.RANGE] max_mach = aviary_options.get_val(Mission.Constraints.MAX_MACH) @@ -72,13 +72,13 @@ def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None): def compute_partials(self, inputs, J, discrete_inputs=None): aviary_options: AviaryValues = self.options['aviary_options'] - first_class_count = aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS) + first_class_count = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) business_class_count = \ - aviary_options.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS) + aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) tourist_class_count = \ - aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS) + aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS) design_range = inputs[Mission.Design.RANGE] max_mach = aviary_options.get_val(Mission.Constraints.MAX_MACH) From 7c86741a58c5b03508b9e65f26d7e8074e618720 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Fri, 6 Sep 2024 12:19:47 -0400 Subject: [PATCH 056/113] fixed phase_info assignments --- .../multi_missions/run_multimission_example_FwFm.py | 8 +++++--- 1 file changed, 5 insertions(+), 3 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example_FwFm.py b/aviary/examples/multi_missions/run_multimission_example_FwFm.py index 68ad4515c..dde79f6a5 100644 --- a/aviary/examples/multi_missions/run_multimission_example_FwFm.py +++ b/aviary/examples/multi_missions/run_multimission_example_FwFm.py @@ -23,11 +23,13 @@ from aviary.variable_info.variables import Mission, Aircraft from aviary.examples.example_phase_info import phase_info +import copy as copy # fly the same mission twice with two different passenger loads -phase_info_primary = phase_info -phase_info_deadhead = phase_info +phase_info_primary = copy.deepcopy(phase_info) +phase_info_deadhead = copy.deepcopy(phase_info) +#phase_info_deadhead['post_mission']['target_range'] = [1500, "nmi"] class MultiMissionProblem(om.Problem): def __init__(self, planes, phase_infos, weights): @@ -232,7 +234,7 @@ def FwFm_example(makeN2=False): phaseinfo[key]["user_options"]["optimize_altitude"] = optalt # how much each mission should be valued by the optimizer, larger numbers = more significance - weights = [.9, 0.1] + weights = [9, 1] super_prob = MultiMissionProblem(planes, phase_infos, weights) super_prob.add_driver() From d79f3d63b65b1c76a5dd47134bcf1b6ebc1857aa Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Wed, 11 Sep 2024 15:19:02 -0400 Subject: [PATCH 057/113] removed c5 and FwFm multi mission examples files, replaced with large_single_aisle example file --- .../run_multimission_example.py | 283 ------------------ ...ultimission_example_large_single_aisle.py} | 48 ++- c5_models/c5.csv | 167 ----------- c5_models/c5_ferry.csv | 167 ----------- c5_models/c5_ferry_phase_info.py | 83 ----- c5_models/c5_intermediate.csv | 167 ----------- c5_models/c5_intermediate_phase_info.py | 83 ----- c5_models/c5_maxpayload.csv | 167 ----------- c5_models/c5_maxpayload_phase_info.py | 83 ----- c5_runfile_single_aviary.py | 49 --- 10 files changed, 32 insertions(+), 1265 deletions(-) delete mode 100644 aviary/examples/multi_missions/run_multimission_example.py rename aviary/examples/multi_missions/{run_multimission_example_FwFm.py => run_multimission_example_large_single_aisle.py} (85%) delete mode 100644 c5_models/c5.csv delete mode 100644 c5_models/c5_ferry.csv delete mode 100644 c5_models/c5_ferry_phase_info.py delete mode 100644 c5_models/c5_intermediate.csv delete mode 100644 c5_models/c5_intermediate_phase_info.py delete mode 100644 c5_models/c5_maxpayload.csv delete mode 100644 c5_models/c5_maxpayload_phase_info.py delete mode 100644 c5_runfile_single_aviary.py diff --git a/aviary/examples/multi_missions/run_multimission_example.py b/aviary/examples/multi_missions/run_multimission_example.py deleted file mode 100644 index 7942c0ffb..000000000 --- a/aviary/examples/multi_missions/run_multimission_example.py +++ /dev/null @@ -1,283 +0,0 @@ -""" -authors: Jatin Soni, Eliot Aretskin -Multi Mission Optimization Example using Aviary -""" -import sys -import warnings -import dymos as dm -import numpy as np -from os.path import join -import matplotlib.pyplot as plt - -import openmdao.api as om -import aviary.api as av -from aviary.variable_info.enums import ProblemType -from aviary.variable_info.variables import Mission, Aircraft - -from c5_models.c5_ferry_phase_info import phase_info as c5_ferry_phase_info -from c5_models.c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info -from c5_models.c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info - - -# Usage: -# For the landing gear mass (MAIN_GEAR_MASS & NOSE_GEAR_MASS) to be designed consistently -# between missions, the Aircraft.Design.TOUCHDOWN_MASS must be set to the same value for all missions. - -class MultiMissionProblem(om.Problem): - def __init__(self, planes, phase_infos, weights): - super().__init__() - self.num_missions = len(planes) - # phase infos and planes length must match - this maybe unnecessary if - # different planes (payloads) fly same mission (say pax vs cargo) - # or if same payload flies 2 different missions (altitude/mach differences) - if self.num_missions != len(phase_infos): - raise Exception("Length of planes and phase_infos must be the same!") - - # if fewer weights than planes are provided, assign equal weights for all planes - if len(weights) < self.num_missions: - weights = [1]*self.num_missions - # if more weights than planes, raise exception - elif len(weights) > self.num_missions: - raise Exception("Length of weights cannot exceed length of planes!") - self.weights = weights - self.phase_infos = phase_infos - - self.group_prefix = 'group' - self.probs = [] - self.fuel_vars = [] - self.phases = {} - # define individual aviary problems - for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): - prob = av.AviaryProblem() - prob.load_inputs(plane, phase_info) - prob.check_and_preprocess_inputs() - prob.add_pre_mission_systems() - prob.add_phases() - prob.add_post_mission_systems() - prob.link_phases() - - # alternate prevents use of equality constraint b/w design and summary gross mass - prob.problem_type = ProblemType.ALTERNATE - prob.add_design_variables() - self.probs.append(prob) - # phase names for each traj (can be used later to make plots/print outputs) - self.phases[f"{self.group_prefix}_{i}"] = list(prob.traj._phases.keys()) - - # design range and gross mass are promoted, these are Max Range/Max Takeoff Mass - # and must be the same for each aviary problem. Subsystems within aviary are sized - # using these - empty mass is same across all aviary problems. - # the fuel objective is also promoted since that's used in the compound objective - promoted_name = f"{self.group_prefix}_{i}_fuelobj" - self.fuel_vars.append(promoted_name) - self.model.add_subsystem( - self.group_prefix + f'_{i}', prob.model, - promotes_inputs=[Mission.Design.GROSS_MASS, - Mission.Design.RANGE, - Aircraft.Wing.SPAN, - Aircraft.Wing.AREA], - promotes_outputs=[(Mission.Objectives.FUEL, promoted_name)]) - - def add_design_variables(self): - self.model.add_design_var(Mission.Design.GROSS_MASS, - lower=10., upper=900e3, units='lbm') - self.model.add_design_var(Aircraft.Wing.SPAN, lower=100., upper=500., units='ft') - self.model.add_design_var(Aircraft.Wing.AREA, lower=10., - upper=1e6, units='ft**2') - - def add_driver(self): - self.driver = om.pyOptSparseDriver() - self.driver.options["optimizer"] = "SLSQP" - self.driver.declare_coloring() - # linear solver causes nan entry error for landing to takeoff mass ratio param - # self.model.linear_solver = om.DirectSolver() - - def add_objective(self): - # weights are normalized - e.g. for given weights 3:1, the normalized - # weights are 0.75:0.25 - weights = [float(weight/sum(self.weights)) for weight in self.weights] - weighted_str = "+".join([f"{fuelobj}*{weight}" - for fuelobj, weight in zip(self.fuel_vars, weights)]) - # weighted_str looks like: fuel_0 * weight[0] + fuel_1 * weight[1] - # note that the fuel objective itself is the base aviary fuel objective - # which is also a function of climb time becuse climb is not very sensitive to fuel - - # adding compound execComp to super problem - self.model.add_subsystem('compound_fuel_burn_objective', om.ExecComp( - "compound = "+weighted_str, has_diag_partials=True), promotes=["compound"]) - self.model.add_objective('compound') - - def setup_wrapper(self): - """Wrapper for om.Problem setup with warning ignoring and setting options""" - for prob in self.probs: - prob.model.options['aviary_options'] = prob.aviary_inputs - prob.model.options['aviary_metadata'] = prob.meta_data - prob.model.options['phase_info'] = prob.phase_info - - # Aviary's problem setup wrapper uses these ignored warnings to suppress - # some warnings related to variable promotion. Replicating that here with - # setup for the super problem - with warnings.catch_warnings(): - warnings.simplefilter("ignore", om.OpenMDAOWarning) - warnings.simplefilter("ignore", om.PromotionWarning) - self.setup(check='all') - - def run(self): - self.model.set_solver_print(0) - dm.run_problem(self, make_plots=False) - - def get_design_range(self): - """Finds the longest mission and sets its range as the design range for all - Aviary problems. Used within Aviary for sizing subsystems (avionics and AC).""" - design_range = [] - for phase_info in self.phase_infos: - design_range.append(phase_info['post_mission'] - ['target_range'][0]) # TBD add units - design_range_min = np.min(design_range) - design_range_max = np.max(design_range) - return design_range_max, design_range_min # design_range_min - - def create_timeseries_plots(self, plotvars=[], show=True): - """ - Temporary create plots manually because graphing won't work for dual-trajectories. - Creates timeseries plots for any variables within timeseries. Specify variables - and units by setting plotvars = [('altitude','ft')]. Any number of vars can be added. - """ - plt.figure() - for plotidx, (var, unit) in enumerate(plotvars): - plt.subplot(int(np.ceil(len(plotvars)/2)), 2, plotidx+1) - for i in range(self.num_missions): - time = np.array([]) - yvar = np.array([]) - # this loop concatenates data from all phases - for phase in self.phases[f"{self.group_prefix}_{i}"]: - rawt = self.get_val( - f"{self.group_prefix}_{i}.traj.{phase}.timeseries.time", - units='s') - rawy = self.get_val( - f"{self.group_prefix}_{i}.traj.{phase}.timeseries.{var}", - units=unit) - time = np.hstack([time, np.ndarray.flatten(rawt)]) - yvar = np.hstack([yvar, np.ndarray.flatten(rawy)]) - plt.plot(time, yvar, linewidth=self.num_missions-i) - plt.xlabel("Time (s)") - plt.ylabel(f"{var.title()} ({unit})") - plt.grid() - plt.figlegend([f"Plane {i}" for i in range(self.num_missions)]) - if show: - plt.show() - - def create_payload_range_plot(self, show=True): - """Creates payload range diagram for the super problem. Appends a point for max payload - and 0 range. """ - payloads = [] - ranges = [] - for i in range(self.num_missions): - ref = f"{self.group_prefix}_{i}" - payloads.append( - self.get_val( - f"{ref}.{Aircraft.CrewPayload.CARGO_MASS}", units='lbm')) - lastphase = self.phases[ref][-1] - ranges.append( - self.get_val( - f"{ref}.traj.{lastphase}.timeseries.distance", - units='nmi', indices=-1)[0]) - payloads, ranges = zip(*sorted(zip(payloads, ranges))) - payloads, ranges = list(payloads), list(ranges) - payloads.append(payloads[-1]) - ranges.append(0) - plt.figure() - plt.plot(ranges, payloads) - plt.xlabel("Range (nmi)") - plt.ylabel("Payload (lbm)") - plt.grid() - if show: - plt.show() - - def print_vars(self, vars=[]): - """Specify vars with name and unit in a tuple, e.g. vars = [ (Mission.Summary.FUEL_BURNED, 'lbm') ]""" - - print("\n\n=========================\n") - print(f"{'':40}", end=': ') - for i in range(self.num_missions): - name = f"Mission {i}" - print(f"{name:^30}", end='| ') - print() - for var, unit in vars: - varname = f"Variable: {var.replace(':','.').upper()}" - print(f"{varname:40}", end=": ") - for i in range(self.num_missions): - val = self.get_val(f'group_{i}.{var}', units=unit)[0] - printstatement = f"{val} ({unit})" - print(f"{printstatement:^30}", end="| ") - print() - - -def C5_example(makeN2=False): - plane_dir = 'c5_models' - planes = ['c5_maxpayload.csv', 'c5_intermediate.csv', 'c5_ferry.csv'] - planes = [join(plane_dir, plane) for plane in planes] - phase_infos = [c5_maxpayload_phase_info, - c5_intermediate_phase_info, c5_ferry_phase_info] - optalt, optmach = False, False - for phaseinfo in phase_infos: - for key in phaseinfo.keys(): - if "user_options" in phaseinfo[key].keys(): - phaseinfo[key]["user_options"]["optimize_mach"] = optmach - phaseinfo[key]["user_options"]["optimize_altitude"] = optalt - - weights = [1, 1, 1] - - super_prob = MultiMissionProblem(planes, phase_infos, weights) - super_prob.add_driver() - super_prob.add_design_variables() - super_prob.add_objective() - # set input default to prevent error, value doesn't matter since set val is used later - super_prob.model.set_input_defaults(Mission.Design.RANGE, val=1.) - super_prob.setup_wrapper() - - # All the design ranges must be the same to make sure Air Conditioning and Avionics are designed the same for all missions, - super_prob.set_val(Mission.Design.RANGE, super_prob.get_design_range()[0]) - - for i, prob in enumerate(super_prob.probs): - prob.set_initial_guesses(super_prob, super_prob.group_prefix+f"_{i}.") - - if makeN2: - from createN2 import createN2 - createN2(__file__, super_prob) - - super_prob.run() - printoutputs = [ - (Mission.Design.GROSS_MASS, 'lbm'), - (Aircraft.Design.EMPTY_MASS, 'lbm'), - (Mission.Summary.GROSS_MASS, 'lbm'), - (Mission.Summary.FUEL_BURNED, 'lbm'), - (Mission.Design.FUEL_MASS, 'lbm'), - (Mission.Summary.TOTAL_FUEL_MASS, 'lbm'), - (Aircraft.Wing.SPAN, 'ft'), - (Aircraft.Wing.AREA, 'ft**2'), - (Aircraft.LandingGear.MAIN_GEAR_MASS, 'lbm'), - (Aircraft.LandingGear.NOSE_GEAR_MASS, 'lbm'), - (Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, 'unitless'), - (Mission.Summary.CRUISE_MACH, 'unitless'), - (Aircraft.Furnishings.MASS, 'lbm'), - (Aircraft.CrewPayload.PASSENGER_SERVICE_MASS, 'lbm')] - super_prob.print_vars(vars=printoutputs) - - plotvars = [('altitude', 'ft'), - ('mass', 'lbm'), - ('drag', 'lbf'), - ('distance', 'nmi'), - ('throttle', 'unitless'), - ('mach', 'unitless')] - super_prob.create_timeseries_plots(plotvars=plotvars, show=False) - - super_prob.create_payload_range_plot(show=False) - plt.show() - - return super_prob - - -if __name__ == '__main__': - makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False - - super_prob = C5_example(makeN2=makeN2) diff --git a/aviary/examples/multi_missions/run_multimission_example_FwFm.py b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py similarity index 85% rename from aviary/examples/multi_missions/run_multimission_example_FwFm.py rename to aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py index dde79f6a5..ef49b1c77 100644 --- a/aviary/examples/multi_missions/run_multimission_example_FwFm.py +++ b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py @@ -22,6 +22,7 @@ from aviary.variable_info.enums import ProblemType from aviary.variable_info.variables import Mission, Aircraft + from aviary.examples.example_phase_info import phase_info import copy as copy @@ -29,24 +30,40 @@ phase_info_primary = copy.deepcopy(phase_info) phase_info_deadhead = copy.deepcopy(phase_info) +# get large single aisle values +from aviary.validation_cases.validation_tests import get_flops_inputs +aviary_inputs_primary = get_flops_inputs('LargeSingleAisle2FLOPS') +aviary_inputs_primary.set_val('aircraft:crew_and_payload:design:num_passengers', 162, 'unitless') +aviary_inputs_primary.set_val('aircraft:crew_and_payload:design:num_tourist_class', 150, 'unitless') +aviary_inputs_primary.set_val('aircraft:crew_and_payload:design:num_business_class', 0, 'unitless') +aviary_inputs_primary.set_val('aircraft:crew_and_payload:design:num_first_class', 12, 'unitless') + + +aviary_inputs_deadhead = copy.deepcopy(aviary_inputs_primary) +aviary_inputs_deadhead.set_val('aircraft:crew_and_payload:num_passengers', 0, 'unitless') +aviary_inputs_deadhead.set_val('aircraft:crew_and_payload:num_tourist_class', 0, 'unitless') +aviary_inputs_deadhead.set_val('aircraft:crew_and_payload:num_business_class', 0, 'unitless') +aviary_inputs_deadhead.set_val('aircraft:crew_and_payload:num_first_class', 0, 'unitless') +aviary_inputs_deadhead.set_val(Aircraft.CrewPayload.MISC_CARGO, 0.0, 'lbm') + #phase_info_deadhead['post_mission']['target_range'] = [1500, "nmi"] class MultiMissionProblem(om.Problem): - def __init__(self, planes, phase_infos, weights): + def __init__(self, aviary_values, phase_infos, weights): super().__init__() - self.num_missions = len(planes) - # phase infos and planes length must match - this maybe unnecessary if - # different planes (payloads) fly same mission (say pax vs cargo) + self.num_missions = len(aviary_values) + # phase infos and aviary_values length must match - this maybe unnecessary if + # different aviary_values (payloads) fly same mission (say pax vs cargo) # or if same payload flies 2 different missions (altitude/mach differences) if self.num_missions != len(phase_infos): - raise Exception("Length of planes and phase_infos must be the same!") + raise Exception("Length of aviary_values and phase_infos must be the same!") - # if fewer weights than planes are provided, assign equal weights for all planes + # if fewer weights than aviary_values are provided, assign equal weights for all aviary_values if len(weights) < self.num_missions: weights = [1]*self.num_missions - # if more weights than planes, raise exception + # if more weights than aviary_values, raise exception elif len(weights) > self.num_missions: - raise Exception("Length of weights cannot exceed length of planes!") + raise Exception("Length of weights cannot exceed length of aviary_values!") self.weights = weights self.phase_infos = phase_infos @@ -55,9 +72,9 @@ def __init__(self, planes, phase_infos, weights): self.fuel_vars = [] self.phases = {} # define individual aviary problems - for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): + for i, (aviary_values, phase_info) in enumerate(zip(aviary_values, phase_infos)): prob = av.AviaryProblem() - prob.load_inputs(plane, phase_info) + prob.load_inputs(aviary_values, phase_info) prob.check_and_preprocess_inputs() prob.add_pre_mission_systems() prob.add_phases() @@ -220,10 +237,9 @@ def print_vars(self, vars=[]): print() -def FwFm_example(makeN2=False): - plane_dir = 'models/test_aircraft/' - planes = ['aircraft_for_bench_FwFm.csv', 'aircraft_for_bench_FwFm_deadhead.csv'] - planes = [join(plane_dir, plane) for plane in planes] +def large_single_aisle_example(makeN2=False): + aviary_values=[aviary_inputs_primary, + aviary_inputs_deadhead] phase_infos = [phase_info_primary, phase_info_deadhead] optalt, optmach = False, False @@ -236,7 +252,7 @@ def FwFm_example(makeN2=False): # how much each mission should be valued by the optimizer, larger numbers = more significance weights = [9, 1] - super_prob = MultiMissionProblem(planes, phase_infos, weights) + super_prob = MultiMissionProblem(aviary_values, phase_infos, weights) super_prob.add_driver() super_prob.add_design_variables() super_prob.add_objective() @@ -287,7 +303,7 @@ def FwFm_example(makeN2=False): if __name__ == '__main__': makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False - super_prob = FwFm_example(makeN2=makeN2) + super_prob = large_single_aisle_example(makeN2=makeN2) # super_prob.model.group_1.list_vars(val=True, units=True, print_arrays=False) # https://openmdao.org/newdocs/versions/latest/features/debugging/listing_variables.html?highlight=list_driver_vars diff --git a/c5_models/c5.csv b/c5_models/c5.csv deleted file mode 100644 index 186bb7e4f..000000000 --- a/c5_models/c5.csv +++ /dev/null @@ -1,167 +0,0 @@ -# author: Chris Psenica -#aircraft:air_conditioning:mass_scaler,1.0,unitless -#aircraft:anti_icing:mass_scaler,1.0,unitless -#aircraft:apu:mass_scaler,1.0,unitless -#aircraft:avionics:mass_scaler,1.0,unitless -#aircraft:canard:area,0.0,ft**2 -#aircraft:canard:aspect_ratio,0.0,unitless -#aircraft:canard:thickness_to_chord,0.0,unitless -aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm -#aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless -#aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:mass_per_passenger,180.0,lbm - -aircraft:crew_and_payload:cargo_mass,281000,lbm -#aircraft:crew_and_payload:num_passengers,82,unitless - -#aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:num_flight_crew,7,unitless -#aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless -#aircraft:crew_and_payload:wing_cargo,0.0,lbm -#aircraft:design:base_area,0.0,ft**2 -#aircraft:design:empty_mass_margin_scaler,1.0,unitless -#aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless -#aircraft:design:touchdown_mass,498554,lbm -aircraft:design:reserve_fuel_additional,0,lbm -#aircraft:design:subsonic_drag_coeff_factor,1.0,unitless -#aircraft:design:supersonic_drag_coeff_factor,1.0,unitless -aircraft:design:use_alt_mass,False,unitless -#aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless -#aircraft:electrical:mass_scaler,1.0,unitless - -aircraft:engine:data_file,models/engines/CF6.deck,unitless - -aircraft:engine:additional_mass_fraction,0.,unitless -aircraft:engine:constant_fuel_consumption,0.,lbm/h - -aircraft:engine:flight_idle_thrust_fraction,0.0,unitless -aircraft:engine:flight_idle_max_fraction,1.0,unitless -aircraft:engine:flight_idle_min_fraction,0.08,unitless -#aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless -#aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless -aircraft:engine:generate_flight_idle,False,unitless -aircraft:engine:geopotential_alt,False,unitless -aircraft:engine:ignore_negative_thrust,False,unitless -aircraft:engine:interpolation_method,slinear,unitless -aircraft:engine:mass_scaler,1.0,unitless -aircraft:engine:mass,8176,lbm -aircraft:engine:reference_mass,8176,lbm -aircraft:engine:reference_sls_thrust,51250.,lbf -aircraft:engine:scale_mass,True,unitless -aircraft:engine:scale_performance,True,unitless -aircraft:engine:scaled_sls_thrust,51250,lbf -#aircraft:engine:subsonic_fuel_flow_scaler,1.0,unitless -#aircraft:engine:supersonic_fuel_flow_scaler,1.0,unitless -#aircraft:engine:thrust_reversers_mass_scaler,1.0,unitless -aircraft:engine:num_fuselage_engines,0,unitless -aircraft:engine:num_engines,4,unitless -aircraft:engine:num_wing_engines,4,unitless -aircraft:engine:wing_locations,[0.3561541339,0.555929667],unitless -#aircraft:fins:area,0.0,ft**2 -#aircraft:fins:mass_scaler,1.0,unitless -#aircraft:fins:mass,0.0,lbm -#aircraft:fins:num_fins,0,unitless -#aircraft:fins:taper_ratio,10.0,unitless -aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm -#aircraft:fuel:density_ratio,1.0,unitless -#aircraft:fuel:fuel_system_mass_scaler,1.0,unitless -aircraft:fuel:fuselage_fuel_capacity,0.0,lbm -aircraft:fuel:num_tanks,12,unitless -aircraft:fuel:total_capacity,341446,lbm -#aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless -#aircraft:furnishings:mass_scaler,1.0,unitless -aircraft:fuselage:length,230.58,ft -#aircraft:fuselage:mass_scaler,1.0,unitless -aircraft:fuselage:max_height,26.83,ft -aircraft:fuselage:max_width,23.9,ft -aircraft:fuselage:military_cargo_floor,True,unitless -aircraft:fuselage:num_fuselages,1,unitless -aircraft:fuselage:passenger_compartment_length,143.75,ft -aircraft:fuselage:planform_area,4462.78,ft**2 -#aircraft:fuselage:wetted_area_scaler,1.0,unitless -aircraft:horizontal_tail:area,965.8,ft**2 -aircraft:horizontal_tail:aspect_ratio,4.2,unitless -#aircraft:horizontal_tail:mass_scaler,1.0,unitless -aircraft:horizontal_tail:taper_ratio,0.43,unitless -aircraft:horizontal_tail:thickness_to_chord,0.16,unitless -aircraft:horizontal_tail:vertical_tail_fraction,1.0,unitless -#aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless -#aircraft:hydraulics:mass_scaler,1.0,unitless -#aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 -#aircraft:instruments:mass_scaler,1.0,unitless -#aircraft:landing_gear:carrier_based,False,unitless -#aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless -#aircraft:landing_gear:main_gear_oleo_length,45,inch -#aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless -#aircraft:landing_gear:nose_gear_oleo_length,45,inch -aircraft:nacelle:avg_diameter,9.15,ft -aircraft:nacelle:avg_length,20.56,ft -#aircraft:nacelle:mass_scaler,1.0,unitless -#aircraft:nacelle:wetted_area_scaler,1.0,unitless -#aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 -#aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless -#aircraft:propulsion:misc_mass_scaler,1.0,unitless -aircraft:vertical_tail:area,537.9,ft**2 -aircraft:vertical_tail:aspect_ratio,0.958,unitless -#aircraft:vertical_tail:mass_scaler,1.0,unitless -aircraft:vertical_tail:num_tails,1,unitless -aircraft:vertical_tail:taper_ratio,0.846,unitless -aircraft:vertical_tail:thickness_to_chord,0.157,unitless -#aircraft:vertical_tail:wetted_area_scaler,1.0,unitless -aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless -aircraft:wing:airfoil_technology,1.0,unitless -aircraft:wing:area,6200,ft**2 -aircraft:wing:aspect_ratio,7.75,unitless -#aircraft:wing:bending_mass_scaler,1.0,unitless -#aircraft:wing:composite_fraction,0.1,unitless -aircraft:wing:control_surface_area,2323.7,ft**2 -aircraft:wing:control_surface_area_ratio,0.37479,unitless -aircraft:wing:load_distribution_control,2.0,unitless -aircraft:wing:load_fraction,1.0,unitless -#aircraft:wing:mass_scaler,1.0,unitless -aircraft:wing:max_camber_at_70_semispan,0.0,unitless -#aircraft:wing:misc_mass_scaler,1.0,unitless -#aircraft:wing:shear_control_mass_scaler,1.0,unitless -aircraft:wing:span_efficiency_reduction,False,unitless -aircraft:wing:span,222.75,ft -#aircraft:wing:strut_bracing_factor,0.0,unitless -#aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless -aircraft:wing:sweep,20.0,deg -aircraft:wing:taper_ratio,0.419,unitless -aircraft:wing:thickness_to_chord,0.1284,unitless -aircraft:wing:ultimate_load_factor,3.75,unitless -aircraft:wing:var_sweep_mass_penalty,0.0,unitless -#aircraft:wing:wetted_area_scaler,1.0,unitless -aircraft:wing:num_integration_stations,50,unitless -aircraft:wing:thickness_to_chord_dist,0.1239,0.108,0.013,unitless -aircraft:wing:load_path_sweep_dist,0.0,0.0,deg -aircraft:wing:input_station_dist,0.0,0.3298,0.884,unitless -aircraft:wing:chord_per_semispan,0.362,0.2667,0.0456,unitless -aircraft:wing:glove_and_bat,0.0,ft**2 -aircraft:wing:detailed_wing,False,unitless - - -mission:constraints:max_mach,0.77,unitless -mission:design:cruise_altitude,34000,ft -mission:design:gross_mass,840000,lbm -mission:design:range,7000,NM -mission:design:thrust_takeoff_per_eng,51250,lbf -mission:landing:lift_coefficient_max,3.0,unitless -mission:design:mach,0.77,unitless -#mission:summary:fuel_flow_scaler,1.0,unitless -mission:takeoff:fuel_simple,6.32,lbm -mission:takeoff:lift_coefficient_max,3.62,unitless -mission:takeoff:lift_over_drag,19.5,unitless -settings:equations_of_motion,height_energy -settings:mass_method,FLOPS - - -### missions definition -# mission_name: payload -# times: 0, 50, 280, 300 -# altitudes: 0, 30000, 30000, 0 -# machs: 0.30, 0.77, 0.77, 0.30 -# optimize_altitudes: F,F,F -# optimize_machs: F,F,F -# takeoff: F -# landing: F diff --git a/c5_models/c5_ferry.csv b/c5_models/c5_ferry.csv deleted file mode 100644 index 6540463d5..000000000 --- a/c5_models/c5_ferry.csv +++ /dev/null @@ -1,167 +0,0 @@ -# author: Chris Psenica -#aircraft:air_conditioning:mass_scaler,1.0,unitless -#aircraft:anti_icing:mass_scaler,1.0,unitless -#aircraft:apu:mass_scaler,1.0,unitless -#aircraft:avionics:mass_scaler,1.0,unitless -#aircraft:canard:area,0.0,ft**2 -#aircraft:canard:aspect_ratio,0.0,unitless -#aircraft:canard:thickness_to_chord,0.0,unitless -aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm -#aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless -#aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:mass_per_passenger,180.0,lbm - -aircraft:crew_and_payload:cargo_mass,0,lbm -#aircraft:crew_and_payload:num_passengers,82,unitless - -#aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:num_flight_crew,7,unitless -#aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless -#aircraft:crew_and_payload:wing_cargo,0.0,lbm -#aircraft:design:base_area,0.0,ft**2 -#aircraft:design:empty_mass_margin_scaler,1.0,unitless -#aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless -#aircraft:design:touchdown_mass,498554,lbm -aircraft:design:reserve_fuel_additional,0,lbm -#aircraft:design:subsonic_drag_coeff_factor,1.0,unitless -#aircraft:design:supersonic_drag_coeff_factor,1.0,unitless -aircraft:design:use_alt_mass,False,unitless -#aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless -#aircraft:electrical:mass_scaler,1.0,unitless - -aircraft:engine:data_file,models/engines/CF6.deck,unitless - -aircraft:engine:additional_mass_fraction,0.,unitless -aircraft:engine:constant_fuel_consumption,0.,lbm/h - -aircraft:engine:flight_idle_thrust_fraction,0.0,unitless -aircraft:engine:flight_idle_max_fraction,1.0,unitless -aircraft:engine:flight_idle_min_fraction,0.08,unitless -#aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless -#aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless -aircraft:engine:generate_flight_idle,False,unitless -aircraft:engine:geopotential_alt,False,unitless -aircraft:engine:ignore_negative_thrust,False,unitless -aircraft:engine:interpolation_method,slinear,unitless -aircraft:engine:mass_scaler,1.0,unitless -aircraft:engine:mass,8176,lbm -aircraft:engine:reference_mass,8176,lbm -aircraft:engine:reference_sls_thrust,51250.,lbf -aircraft:engine:scale_mass,True,unitless -aircraft:engine:scale_performance,True,unitless -aircraft:engine:scaled_sls_thrust,51250,lbf -#aircraft:engine:subsonic_fuel_flow_scaler,1.0,unitless -#aircraft:engine:supersonic_fuel_flow_scaler,1.0,unitless -#aircraft:engine:thrust_reversers_mass_scaler,1.0,unitless -aircraft:engine:num_fuselage_engines,0,unitless -aircraft:engine:num_engines,4,unitless -aircraft:engine:num_wing_engines,4,unitless -aircraft:engine:wing_locations,[0.3561541339,0.555929667],unitless -#aircraft:fins:area,0.0,ft**2 -#aircraft:fins:mass_scaler,1.0,unitless -#aircraft:fins:mass,0.0,lbm -#aircraft:fins:num_fins,0,unitless -#aircraft:fins:taper_ratio,10.0,unitless -aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm -#aircraft:fuel:density_ratio,1.0,unitless -#aircraft:fuel:fuel_system_mass_scaler,1.0,unitless -aircraft:fuel:fuselage_fuel_capacity,0.0,lbm -aircraft:fuel:num_tanks,12,unitless -aircraft:fuel:total_capacity,341446,lbm -#aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless -#aircraft:furnishings:mass_scaler,1.0,unitless -aircraft:fuselage:length,230.58,ft -#aircraft:fuselage:mass_scaler,1.0,unitless -aircraft:fuselage:max_height,26.83,ft -aircraft:fuselage:max_width,23.9,ft -aircraft:fuselage:military_cargo_floor,True,unitless -aircraft:fuselage:num_fuselages,1,unitless -aircraft:fuselage:passenger_compartment_length,143.75,ft -aircraft:fuselage:planform_area,4462.78,ft**2 -#aircraft:fuselage:wetted_area_scaler,1.0,unitless -aircraft:horizontal_tail:area,965.8,ft**2 -aircraft:horizontal_tail:aspect_ratio,4.2,unitless -#aircraft:horizontal_tail:mass_scaler,1.0,unitless -aircraft:horizontal_tail:taper_ratio,0.43,unitless -aircraft:horizontal_tail:thickness_to_chord,0.16,unitless -aircraft:horizontal_tail:vertical_tail_fraction,1.0,unitless -#aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless -#aircraft:hydraulics:mass_scaler,1.0,unitless -#aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 -#aircraft:instruments:mass_scaler,1.0,unitless -#aircraft:landing_gear:carrier_based,False,unitless -#aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless -#aircraft:landing_gear:main_gear_oleo_length,45,inch -#aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless -#aircraft:landing_gear:nose_gear_oleo_length,45,inch -aircraft:nacelle:avg_diameter,9.15,ft -aircraft:nacelle:avg_length,20.56,ft -#aircraft:nacelle:mass_scaler,1.0,unitless -#aircraft:nacelle:wetted_area_scaler,1.0,unitless -#aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 -#aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless -#aircraft:propulsion:misc_mass_scaler,1.0,unitless -aircraft:vertical_tail:area,537.9,ft**2 -aircraft:vertical_tail:aspect_ratio,0.958,unitless -#aircraft:vertical_tail:mass_scaler,1.0,unitless -aircraft:vertical_tail:num_tails,1,unitless -aircraft:vertical_tail:taper_ratio,0.846,unitless -aircraft:vertical_tail:thickness_to_chord,0.157,unitless -#aircraft:vertical_tail:wetted_area_scaler,1.0,unitless -aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless -aircraft:wing:airfoil_technology,1.0,unitless -aircraft:wing:area,6200,ft**2 -aircraft:wing:aspect_ratio,7.75,unitless -#aircraft:wing:bending_mass_scaler,1.0,unitless -#aircraft:wing:composite_fraction,0.1,unitless -aircraft:wing:control_surface_area,2323.7,ft**2 -aircraft:wing:control_surface_area_ratio,0.37479,unitless -aircraft:wing:load_distribution_control,2.0,unitless -aircraft:wing:load_fraction,1.0,unitless -#aircraft:wing:mass_scaler,1.0,unitless -aircraft:wing:max_camber_at_70_semispan,0.0,unitless -#aircraft:wing:misc_mass_scaler,1.0,unitless -#aircraft:wing:shear_control_mass_scaler,1.0,unitless -aircraft:wing:span_efficiency_reduction,False,unitless -aircraft:wing:span,222.75,ft -#aircraft:wing:strut_bracing_factor,0.0,unitless -#aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless -aircraft:wing:sweep,20.0,deg -aircraft:wing:taper_ratio,0.419,unitless -aircraft:wing:thickness_to_chord,0.1284,unitless -aircraft:wing:ultimate_load_factor,3.75,unitless -aircraft:wing:var_sweep_mass_penalty,0.0,unitless -#aircraft:wing:wetted_area_scaler,1.0,unitless -aircraft:wing:num_integration_stations,50,unitless -aircraft:wing:thickness_to_chord_dist,0.1239,0.108,0.013,unitless -aircraft:wing:load_path_sweep_dist,0.0,0.0,deg -aircraft:wing:input_station_dist,0.0,0.3298,0.884,unitless -aircraft:wing:chord_per_semispan,0.362,0.2667,0.0456,unitless -aircraft:wing:glove_and_bat,0.0,ft**2 -aircraft:wing:detailed_wing,False,unitless - - -mission:constraints:max_mach,0.77,unitless -mission:design:cruise_altitude,34000,ft -mission:design:gross_mass,840000,lbm -mission:design:range,7000.0,NM -mission:design:thrust_takeoff_per_eng,51250,lbf -mission:landing:lift_coefficient_max,3.0,unitless -mission:design:mach,0.77,unitless -#mission:summary:fuel_flow_scaler,1.0,unitless -mission:takeoff:fuel_simple,6.32,lbm -mission:takeoff:lift_coefficient_max,3.62,unitless -mission:takeoff:lift_over_drag,19.5,unitless -settings:equations_of_motion,height_energy -settings:mass_method,FLOPS - - -### missions definition -# mission_name: payload -# times: 0, 50, 280, 300 -# altitudes: 0, 30000, 30000, 0 -# machs: 0.30, 0.77, 0.77, 0.30 -# optimize_altitudes: F,F,F -# optimize_machs: F,F,F -# takeoff: F -# landing: F diff --git a/c5_models/c5_ferry_phase_info.py b/c5_models/c5_ferry_phase_info.py deleted file mode 100644 index 6a472ed2f..000000000 --- a/c5_models/c5_ferry_phase_info.py +++ /dev/null @@ -1,83 +0,0 @@ -phase_info = { - "pre_mission": {"include_takeoff": False, "optimize_mass": True}, - "climb_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.3, "unitless"), - "final_mach": (0.77, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), - "initial_altitude": (0.0, "ft"), - "final_altitude": (29500.0, "ft"), - "altitude_bounds": ((0.0, 30000.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": True, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((0.0, 0.0), "min"), - "duration_bounds": ((25.0, 75.0), "min"), - }, - "initial_guesses": {"time": ([0.0, 50.0], "min")}, - }, - "climb_2": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.77, "unitless"), - "final_mach": (0.77, "unitless"), - "mach_bounds": ((0.75, 0.79), "unitless"), - "initial_altitude": (29500.0, "ft"), - "final_altitude": (32000.0, "ft"), - "altitude_bounds": ((29000.0, 32500.0), "ft"), - "throttle_enforcement": "boundary_constraint", - "fix_initial": False, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((25.0, 75.0), "min"), - "duration_bounds": ((381.0, 1143.0), "min"), - }, - "initial_guesses": {"time": ([50.0, 762.0], "min")}, - }, - "descent_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.77, "unitless"), - "final_mach": (0.3, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), - "initial_altitude": (32000.0, "ft"), - "final_altitude": (0.0, "ft"), - "altitude_bounds": ((0.0, 32500.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": False, - "constrain_final": True, - "fix_duration": False, - "initial_bounds": ((406.0, 1218.0), "min"), - "duration_bounds": ((15.5, 46.5), "min"), - }, - "initial_guesses": {"time": ([812.0, 31.0], "min")}, - }, - "post_mission": { - "include_landing": False, - "constrain_range": True, - "target_range": (7001.59, "nmi"), - }, -} diff --git a/c5_models/c5_intermediate.csv b/c5_models/c5_intermediate.csv deleted file mode 100644 index bb4565239..000000000 --- a/c5_models/c5_intermediate.csv +++ /dev/null @@ -1,167 +0,0 @@ -# author: Chris Psenica -#aircraft:air_conditioning:mass_scaler,1.0,unitless -#aircraft:anti_icing:mass_scaler,1.0,unitless -#aircraft:apu:mass_scaler,1.0,unitless -#aircraft:avionics:mass_scaler,1.0,unitless -#aircraft:canard:area,0.0,ft**2 -#aircraft:canard:aspect_ratio,0.0,unitless -#aircraft:canard:thickness_to_chord,0.0,unitless -aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm -#aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless -#aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:mass_per_passenger,180.0,lbm - -aircraft:crew_and_payload:cargo_mass,120000.0,lbm -#aircraft:crew_and_payload:num_passengers,82,unitless - -#aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:num_flight_crew,7,unitless -#aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless -#aircraft:crew_and_payload:wing_cargo,0.0,lbm -#aircraft:design:base_area,0.0,ft**2 -#aircraft:design:empty_mass_margin_scaler,1.0,unitless -#aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless -#aircraft:design:touchdown_mass,498554,lbm -aircraft:design:reserve_fuel_additional,0,lbm -#aircraft:design:subsonic_drag_coeff_factor,1.0,unitless -#aircraft:design:supersonic_drag_coeff_factor,1.0,unitless -aircraft:design:use_alt_mass,False,unitless -#aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless -#aircraft:electrical:mass_scaler,1.0,unitless - -aircraft:engine:data_file,models/engines/CF6.deck,unitless - -aircraft:engine:additional_mass_fraction,0.,unitless -aircraft:engine:constant_fuel_consumption,0.,lbm/h - -aircraft:engine:flight_idle_thrust_fraction,0.0,unitless -aircraft:engine:flight_idle_max_fraction,1.0,unitless -aircraft:engine:flight_idle_min_fraction,0.08,unitless -#aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless -#aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless -aircraft:engine:generate_flight_idle,False,unitless -aircraft:engine:geopotential_alt,False,unitless -aircraft:engine:ignore_negative_thrust,False,unitless -aircraft:engine:interpolation_method,slinear,unitless -aircraft:engine:mass_scaler,1.0,unitless -aircraft:engine:mass,8176,lbm -aircraft:engine:reference_mass,8176,lbm -aircraft:engine:reference_sls_thrust,51250.,lbf -aircraft:engine:scale_mass,True,unitless -aircraft:engine:scale_performance,True,unitless -aircraft:engine:scaled_sls_thrust,51250,lbf -#aircraft:engine:subsonic_fuel_flow_scaler,1.0,unitless -#aircraft:engine:supersonic_fuel_flow_scaler,1.0,unitless -#aircraft:engine:thrust_reversers_mass_scaler,1.0,unitless -aircraft:engine:num_fuselage_engines,0,unitless -aircraft:engine:num_engines,4,unitless -aircraft:engine:num_wing_engines,4,unitless -aircraft:engine:wing_locations,[0.3561541339,0.555929667],unitless -#aircraft:fins:area,0.0,ft**2 -#aircraft:fins:mass_scaler,1.0,unitless -#aircraft:fins:mass,0.0,lbm -#aircraft:fins:num_fins,0,unitless -#aircraft:fins:taper_ratio,10.0,unitless -aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm -#aircraft:fuel:density_ratio,1.0,unitless -#aircraft:fuel:fuel_system_mass_scaler,1.0,unitless -aircraft:fuel:fuselage_fuel_capacity,0.0,lbm -aircraft:fuel:num_tanks,12,unitless -aircraft:fuel:total_capacity,341446,lbm -#aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless -#aircraft:furnishings:mass_scaler,1.0,unitless -aircraft:fuselage:length,230.58,ft -#aircraft:fuselage:mass_scaler,1.0,unitless -aircraft:fuselage:max_height,26.83,ft -aircraft:fuselage:max_width,23.9,ft -aircraft:fuselage:military_cargo_floor,True,unitless -aircraft:fuselage:num_fuselages,1,unitless -aircraft:fuselage:passenger_compartment_length,143.75,ft -aircraft:fuselage:planform_area,4462.78,ft**2 -#aircraft:fuselage:wetted_area_scaler,1.0,unitless -aircraft:horizontal_tail:area,965.8,ft**2 -aircraft:horizontal_tail:aspect_ratio,4.2,unitless -#aircraft:horizontal_tail:mass_scaler,1.0,unitless -aircraft:horizontal_tail:taper_ratio,0.43,unitless -aircraft:horizontal_tail:thickness_to_chord,0.16,unitless -aircraft:horizontal_tail:vertical_tail_fraction,1.0,unitless -#aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless -#aircraft:hydraulics:mass_scaler,1.0,unitless -#aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 -#aircraft:instruments:mass_scaler,1.0,unitless -#aircraft:landing_gear:carrier_based,False,unitless -#aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless -#aircraft:landing_gear:main_gear_oleo_length,45,inch -#aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless -#aircraft:landing_gear:nose_gear_oleo_length,45,inch -aircraft:nacelle:avg_diameter,9.15,ft -aircraft:nacelle:avg_length,20.56,ft -#aircraft:nacelle:mass_scaler,1.0,unitless -#aircraft:nacelle:wetted_area_scaler,1.0,unitless -#aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 -#aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless -#aircraft:propulsion:misc_mass_scaler,1.0,unitless -aircraft:vertical_tail:area,537.9,ft**2 -aircraft:vertical_tail:aspect_ratio,0.958,unitless -#aircraft:vertical_tail:mass_scaler,1.0,unitless -aircraft:vertical_tail:num_tails,1,unitless -aircraft:vertical_tail:taper_ratio,0.846,unitless -aircraft:vertical_tail:thickness_to_chord,0.157,unitless -#aircraft:vertical_tail:wetted_area_scaler,1.0,unitless -aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless -aircraft:wing:airfoil_technology,1.0,unitless -aircraft:wing:area,6200,ft**2 -aircraft:wing:aspect_ratio,7.75,unitless -#aircraft:wing:bending_mass_scaler,1.0,unitless -#aircraft:wing:composite_fraction,0.1,unitless -aircraft:wing:control_surface_area,2323.7,ft**2 -aircraft:wing:control_surface_area_ratio,0.37479,unitless -aircraft:wing:load_distribution_control,2.0,unitless -aircraft:wing:load_fraction,1.0,unitless -#aircraft:wing:mass_scaler,1.0,unitless -aircraft:wing:max_camber_at_70_semispan,0.0,unitless -#aircraft:wing:misc_mass_scaler,1.0,unitless -#aircraft:wing:shear_control_mass_scaler,1.0,unitless -aircraft:wing:span_efficiency_reduction,False,unitless -aircraft:wing:span,222.75,ft -#aircraft:wing:strut_bracing_factor,0.0,unitless -#aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless -aircraft:wing:sweep,20.0,deg -aircraft:wing:taper_ratio,0.419,unitless -aircraft:wing:thickness_to_chord,0.1284,unitless -aircraft:wing:ultimate_load_factor,3.75,unitless -aircraft:wing:var_sweep_mass_penalty,0.0,unitless -#aircraft:wing:wetted_area_scaler,1.0,unitless -aircraft:wing:num_integration_stations,50,unitless -aircraft:wing:thickness_to_chord_dist,0.1239,0.108,0.013,unitless -aircraft:wing:load_path_sweep_dist,0.0,0.0,deg -aircraft:wing:input_station_dist,0.0,0.3298,0.884,unitless -aircraft:wing:chord_per_semispan,0.362,0.2667,0.0456,unitless -aircraft:wing:glove_and_bat,0.0,ft**2 -aircraft:wing:detailed_wing,False,unitless - - -mission:constraints:max_mach,0.77,unitless -mission:design:cruise_altitude,34000,ft -mission:design:gross_mass,840000,lbm -mission:design:range,4800.0,NM -mission:design:thrust_takeoff_per_eng,51250,lbf -mission:landing:lift_coefficient_max,3.0,unitless -mission:design:mach,0.77,unitless -#mission:summary:fuel_flow_scaler,1.0,unitless -mission:takeoff:fuel_simple,6.32,lbm -mission:takeoff:lift_coefficient_max,3.62,unitless -mission:takeoff:lift_over_drag,19.5,unitless -settings:equations_of_motion,height_energy -settings:mass_method,FLOPS - - -### missions definition -# mission_name: payload -# times: 0, 50, 280, 300 -# altitudes: 0, 30000, 30000, 0 -# machs: 0.30, 0.77, 0.77, 0.30 -# optimize_altitudes: F,F,F -# optimize_machs: F,F,F -# takeoff: F -# landing: F diff --git a/c5_models/c5_intermediate_phase_info.py b/c5_models/c5_intermediate_phase_info.py deleted file mode 100644 index a8b462673..000000000 --- a/c5_models/c5_intermediate_phase_info.py +++ /dev/null @@ -1,83 +0,0 @@ -phase_info = { - "pre_mission": {"include_takeoff": False, "optimize_mass": True}, - "climb_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.3, "unitless"), - "final_mach": (0.77, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), - "initial_altitude": (0.0, "ft"), - "final_altitude": (29500.0, "ft"), - "altitude_bounds": ((0.0, 30000.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": True, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((0.0, 0.0), "min"), - "duration_bounds": ((25.0, 75.0), "min"), - }, - "initial_guesses": {"time": ([0.0, 50.0], "min")}, - }, - "climb_2": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.77, "unitless"), - "final_mach": (0.77, "unitless"), - "mach_bounds": ((0.75, 0.79), "unitless"), - "initial_altitude": (29500.0, "ft"), - "final_altitude": (32000.0, "ft"), - "altitude_bounds": ((29000.0, 32500.0), "ft"), - "throttle_enforcement": "boundary_constraint", - "fix_initial": False, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((25.0, 75.0), "min"), - "duration_bounds": ((255.0, 765.0), "min"), - }, - "initial_guesses": {"time": ([50.0, 510.0], "min")}, - }, - "descent_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.77, "unitless"), - "final_mach": (0.3, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), - "initial_altitude": (32000.0, "ft"), - "final_altitude": (0.0, "ft"), - "altitude_bounds": ((0.0, 32500.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": False, - "constrain_final": True, - "fix_duration": False, - "initial_bounds": ((280.0, 840.0), "min"), - "duration_bounds": ((15.0, 45.0), "min"), - }, - "initial_guesses": {"time": ([560.0, 30.0], "min")}, - }, - "post_mission": { - "include_landing": False, - "constrain_range": True, - "target_range": (4839.41, "nmi"), - }, -} diff --git a/c5_models/c5_maxpayload.csv b/c5_models/c5_maxpayload.csv deleted file mode 100644 index 07a6fb381..000000000 --- a/c5_models/c5_maxpayload.csv +++ /dev/null @@ -1,167 +0,0 @@ -# author: Chris Psenica -#aircraft:air_conditioning:mass_scaler,1.0,unitless -#aircraft:anti_icing:mass_scaler,1.0,unitless -#aircraft:apu:mass_scaler,1.0,unitless -#aircraft:avionics:mass_scaler,1.0,unitless -#aircraft:canard:area,0.0,ft**2 -#aircraft:canard:aspect_ratio,0.0,unitless -#aircraft:canard:thickness_to_chord,0.0,unitless -aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm -#aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless -#aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:mass_per_passenger,180.0,lbm - -aircraft:crew_and_payload:cargo_mass,281000.0,lbm -#aircraft:crew_and_payload:num_passengers,82,unitless - -#aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:num_flight_crew,7,unitless -#aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless -#aircraft:crew_and_payload:wing_cargo,0.0,lbm -#aircraft:design:base_area,0.0,ft**2 -#aircraft:design:empty_mass_margin_scaler,1.0,unitless -#aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless -#aircraft:design:touchdown_mass,498554,lbm -aircraft:design:reserve_fuel_additional,0,lbm -#aircraft:design:subsonic_drag_coeff_factor,1.0,unitless -#aircraft:design:supersonic_drag_coeff_factor,1.0,unitless -aircraft:design:use_alt_mass,False,unitless -#aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless -#aircraft:electrical:mass_scaler,1.0,unitless - -aircraft:engine:data_file,models/engines/CF6.deck,unitless - -aircraft:engine:additional_mass_fraction,0.,unitless -aircraft:engine:constant_fuel_consumption,0.,lbm/h - -aircraft:engine:flight_idle_thrust_fraction,0.0,unitless -aircraft:engine:flight_idle_max_fraction,1.0,unitless -aircraft:engine:flight_idle_min_fraction,0.08,unitless -#aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless -#aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless -aircraft:engine:generate_flight_idle,False,unitless -aircraft:engine:geopotential_alt,False,unitless -aircraft:engine:ignore_negative_thrust,False,unitless -aircraft:engine:interpolation_method,slinear,unitless -aircraft:engine:mass_scaler,1.0,unitless -aircraft:engine:mass,8176,lbm -aircraft:engine:reference_mass,8176,lbm -aircraft:engine:reference_sls_thrust,51250.,lbf -aircraft:engine:scale_mass,True,unitless -aircraft:engine:scale_performance,True,unitless -aircraft:engine:scaled_sls_thrust,51250,lbf -#aircraft:engine:subsonic_fuel_flow_scaler,1.0,unitless -#aircraft:engine:supersonic_fuel_flow_scaler,1.0,unitless -#aircraft:engine:thrust_reversers_mass_scaler,1.0,unitless -aircraft:engine:num_fuselage_engines,0,unitless -aircraft:engine:num_engines,4,unitless -aircraft:engine:num_wing_engines,4,unitless -aircraft:engine:wing_locations,[0.3561541339,0.555929667],unitless -#aircraft:fins:area,0.0,ft**2 -#aircraft:fins:mass_scaler,1.0,unitless -#aircraft:fins:mass,0.0,lbm -#aircraft:fins:num_fins,0,unitless -#aircraft:fins:taper_ratio,10.0,unitless -aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm -#aircraft:fuel:density_ratio,1.0,unitless -#aircraft:fuel:fuel_system_mass_scaler,1.0,unitless -aircraft:fuel:fuselage_fuel_capacity,0.0,lbm -aircraft:fuel:num_tanks,12,unitless -aircraft:fuel:total_capacity,341446,lbm -#aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless -#aircraft:furnishings:mass_scaler,1.0,unitless -aircraft:fuselage:length,230.58,ft -#aircraft:fuselage:mass_scaler,1.0,unitless -aircraft:fuselage:max_height,26.83,ft -aircraft:fuselage:max_width,23.9,ft -aircraft:fuselage:military_cargo_floor,True,unitless -aircraft:fuselage:num_fuselages,1,unitless -aircraft:fuselage:passenger_compartment_length,143.75,ft -aircraft:fuselage:planform_area,4462.78,ft**2 -#aircraft:fuselage:wetted_area_scaler,1.0,unitless -aircraft:horizontal_tail:area,965.8,ft**2 -aircraft:horizontal_tail:aspect_ratio,4.2,unitless -#aircraft:horizontal_tail:mass_scaler,1.0,unitless -aircraft:horizontal_tail:taper_ratio,0.43,unitless -aircraft:horizontal_tail:thickness_to_chord,0.16,unitless -aircraft:horizontal_tail:vertical_tail_fraction,1.0,unitless -#aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless -#aircraft:hydraulics:mass_scaler,1.0,unitless -#aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 -#aircraft:instruments:mass_scaler,1.0,unitless -#aircraft:landing_gear:carrier_based,False,unitless -#aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless -#aircraft:landing_gear:main_gear_oleo_length,45,inch -#aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless -#aircraft:landing_gear:nose_gear_oleo_length,45,inch -aircraft:nacelle:avg_diameter,9.15,ft -aircraft:nacelle:avg_length,20.56,ft -#aircraft:nacelle:mass_scaler,1.0,unitless -#aircraft:nacelle:wetted_area_scaler,1.0,unitless -#aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 -#aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless -#aircraft:propulsion:misc_mass_scaler,1.0,unitless -aircraft:vertical_tail:area,537.9,ft**2 -aircraft:vertical_tail:aspect_ratio,0.958,unitless -#aircraft:vertical_tail:mass_scaler,1.0,unitless -aircraft:vertical_tail:num_tails,1,unitless -aircraft:vertical_tail:taper_ratio,0.846,unitless -aircraft:vertical_tail:thickness_to_chord,0.157,unitless -#aircraft:vertical_tail:wetted_area_scaler,1.0,unitless -aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless -aircraft:wing:airfoil_technology,1.0,unitless -aircraft:wing:area,6200,ft**2 -aircraft:wing:aspect_ratio,7.75,unitless -#aircraft:wing:bending_mass_scaler,1.0,unitless -#aircraft:wing:composite_fraction,0.1,unitless -aircraft:wing:control_surface_area,2323.7,ft**2 -aircraft:wing:control_surface_area_ratio,0.37479,unitless -aircraft:wing:load_distribution_control,2.0,unitless -aircraft:wing:load_fraction,1.0,unitless -#aircraft:wing:mass_scaler,1.0,unitless -aircraft:wing:max_camber_at_70_semispan,0.0,unitless -#aircraft:wing:misc_mass_scaler,1.0,unitless -#aircraft:wing:shear_control_mass_scaler,1.0,unitless -aircraft:wing:span_efficiency_reduction,False,unitless -aircraft:wing:span,222.75,ft -#aircraft:wing:strut_bracing_factor,0.0,unitless -#aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless -aircraft:wing:sweep,20.0,deg -aircraft:wing:taper_ratio,0.419,unitless -aircraft:wing:thickness_to_chord,0.1284,unitless -aircraft:wing:ultimate_load_factor,3.75,unitless -aircraft:wing:var_sweep_mass_penalty,0.0,unitless -#aircraft:wing:wetted_area_scaler,1.0,unitless -aircraft:wing:num_integration_stations,50,unitless -aircraft:wing:thickness_to_chord_dist,0.1239,0.108,0.013,unitless -aircraft:wing:load_path_sweep_dist,0.0,0.0,deg -aircraft:wing:input_station_dist,0.0,0.3298,0.884,unitless -aircraft:wing:chord_per_semispan,0.362,0.2667,0.0456,unitless -aircraft:wing:glove_and_bat,0.0,ft**2 -aircraft:wing:detailed_wing,False,unitless - - -mission:constraints:max_mach,0.77,unitless -mission:design:cruise_altitude,34000,ft -mission:design:gross_mass,840000,lbm -mission:design:range,2150.0,NM -mission:design:thrust_takeoff_per_eng,51250,lbf -mission:landing:lift_coefficient_max,3.0,unitless -mission:design:mach,0.77,unitless -#mission:summary:fuel_flow_scaler,1.0,unitless -mission:takeoff:fuel_simple,6.32,lbm -mission:takeoff:lift_coefficient_max,3.62,unitless -mission:takeoff:lift_over_drag,19.5,unitless -settings:equations_of_motion,height_energy -settings:mass_method,FLOPS - - -### missions definition -# mission_name: payload -# times: 0, 50, 280, 300 -# altitudes: 0, 30000, 30000, 0 -# machs: 0.30, 0.77, 0.77, 0.30 -# optimize_altitudes: F,F,F -# optimize_machs: F,F,F -# takeoff: F -# landing: F diff --git a/c5_models/c5_maxpayload_phase_info.py b/c5_models/c5_maxpayload_phase_info.py deleted file mode 100644 index a52acec96..000000000 --- a/c5_models/c5_maxpayload_phase_info.py +++ /dev/null @@ -1,83 +0,0 @@ -phase_info = { - "pre_mission": {"include_takeoff": False, "optimize_mass": True}, - "climb_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.3, "unitless"), - "final_mach": (0.77, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), - "initial_altitude": (0.0, "ft"), - "final_altitude": (29500.0, "ft"), - "altitude_bounds": ((0.0, 30000.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": True, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((0.0, 0.0), "min"), - "duration_bounds": ((25.0, 75.0), "min"), - }, - "initial_guesses": {"time": ([0.0, 50.0], "min")}, - }, - "climb_2": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.77, "unitless"), - "final_mach": (0.77, "unitless"), - "mach_bounds": ((0.75, 0.79), "unitless"), - "initial_altitude": (29500.0, "ft"), - "final_altitude": (32000.0, "ft"), - "altitude_bounds": ((29000.0, 32500.0), "ft"), - "throttle_enforcement": "boundary_constraint", - "fix_initial": False, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((25.0, 75.0), "min"), - "duration_bounds": ((105.0, 315.0), "min"), - }, - "initial_guesses": {"time": ([50.0, 210.0], "min")}, - }, - "descent_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.77, "unitless"), - "final_mach": (0.3, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), - "initial_altitude": (32000.0, "ft"), - "final_altitude": (0.0, "ft"), - "altitude_bounds": ((0.0, 32500.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": False, - "constrain_final": True, - "fix_duration": False, - "initial_bounds": ((130.0, 390.0), "min"), - "duration_bounds": ((15.0, 45.0), "min"), - }, - "initial_guesses": {"time": ([260.0, 30.0], "min")}, - }, - "post_mission": { - "include_landing": False, - "constrain_range": True, - "target_range": (2272.47, "nmi"), - }, -} diff --git a/c5_runfile_single_aviary.py b/c5_runfile_single_aviary.py deleted file mode 100644 index e130dc092..000000000 --- a/c5_runfile_single_aviary.py +++ /dev/null @@ -1,49 +0,0 @@ -import aviary.api as av -# from easy_phase_info_max import phase_info as max_phase_info -# from easy_phase_info_inter import phase_info as inter_phase_info -from c5_models.c5_maxpayload_phase_info import phase_info as max_phase_info -from c5_models.c5_intermediate_phase_info import phase_info as inter_phase_info -from aviary.variable_info.variables import Mission, Aircraft - - -outputs = {Mission.Summary.FUEL_BURNED: [], - Aircraft.Design.EMPTY_MASS: []} -for plane, phase_info in zip( - ['c5_maxpayload', 'c5_intermediate'], - [max_phase_info, inter_phase_info]): - - prob = av.AviaryProblem() - prob.load_inputs(f"c5_models/{plane}.csv", phase_info) - prob.check_and_preprocess_inputs() - prob.add_pre_mission_systems() - prob.add_phases() - prob.add_post_mission_systems() - prob.link_phases() - prob.add_driver('SLSQP') - prob.add_design_variables() - - # Load optimization problem formulation - # Detail which variables the optimizer can control - prob.add_objective() - - prob.setup() - - prob.set_initial_guesses() - # prob.final_setup() - prob.run_aviary_problem() - - for key in outputs.keys(): - outputs[key].append(prob.get_val(key)[0]) - -print("\n\n=============================\n") -for key, item in outputs.items(): - print(f"Variable: {key}") - print(f"Values: {item}") - -""" -Current output: -Variable: mission:summary:fuel_burned -Values: [164988.61692553537, 306345.04738212295] -Variable: aircraft:design:empty_mass -Values: [339001.4003946201, 355540.377187145] -""" From 6ccc97f214e954fcd3be475dead3c80528f7fa6e Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Wed, 11 Sep 2024 15:25:47 -0400 Subject: [PATCH 058/113] removed more c5 folders --- .../multi_missions/c5_models/c5_ferry.csv | 169 ------------------ .../c5_models/c5_ferry_phase_info.py | 83 --------- .../c5_models/c5_intermediate.csv | 168 ----------------- .../c5_models/c5_intermediate_phase_info.py | 83 --------- .../c5_models/c5_maxpayload.csv | 168 ----------------- .../c5_models/c5_maxpayload_phase_info.py | 83 --------- 6 files changed, 754 deletions(-) delete mode 100644 aviary/examples/multi_missions/c5_models/c5_ferry.csv delete mode 100644 aviary/examples/multi_missions/c5_models/c5_ferry_phase_info.py delete mode 100644 aviary/examples/multi_missions/c5_models/c5_intermediate.csv delete mode 100644 aviary/examples/multi_missions/c5_models/c5_intermediate_phase_info.py delete mode 100644 aviary/examples/multi_missions/c5_models/c5_maxpayload.csv delete mode 100644 aviary/examples/multi_missions/c5_models/c5_maxpayload_phase_info.py diff --git a/aviary/examples/multi_missions/c5_models/c5_ferry.csv b/aviary/examples/multi_missions/c5_models/c5_ferry.csv deleted file mode 100644 index 6f9e54275..000000000 --- a/aviary/examples/multi_missions/c5_models/c5_ferry.csv +++ /dev/null @@ -1,169 +0,0 @@ -# author: Chris Psenica -#aircraft:air_conditioning:mass_scaler,1.0,unitless -#aircraft:anti_icing:mass_scaler,1.0,unitless -#aircraft:apu:mass_scaler,1.0,unitless -#aircraft:avionics:mass_scaler,1.0,unitless -#aircraft:canard:area,0.0,ft**2 -#aircraft:canard:aspect_ratio,0.0,unitless -#aircraft:canard:thickness_to_chord,0.0,unitless -aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm -#aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless -#aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:mass_per_passenger,180.0,lbm - -aircraft:crew_and_payload:cargo_mass,0,lbm -#aircraft:crew_and_payload:num_passengers,82,unitless -#aircraft:crew_and_payload:design:num_passengers,82,unitless - -#aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:num_flight_crew,7,unitless -#aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless -#aircraft:crew_and_payload:wing_cargo,0.0,lbm -#aircraft:design:base_area,0.0,ft**2 -#aircraft:design:empty_mass_margin_scaler,1.0,unitless -aircraft:design:landing_to_takeoff_mass_ratio,0.91, unitless -#aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless -#aircraft:design:touchdown_mass,498554,lbm -aircraft:design:reserve_fuel_additional,0,lbm -#aircraft:design:subsonic_drag_coeff_factor,1.0,unitless -#aircraft:design:supersonic_drag_coeff_factor,1.0,unitless -aircraft:design:use_alt_mass,False,unitless -#aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless -#aircraft:electrical:mass_scaler,1.0,unitless - -aircraft:engine:data_file,models/engines/CF6.deck,unitless - -aircraft:engine:additional_mass_fraction,0.,unitless -aircraft:engine:constant_fuel_consumption,0.,lbm/h - -aircraft:engine:flight_idle_thrust_fraction,0.0,unitless -aircraft:engine:flight_idle_max_fraction,1.0,unitless -aircraft:engine:flight_idle_min_fraction,0.08,unitless -#aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless -#aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless -aircraft:engine:generate_flight_idle,False,unitless -aircraft:engine:geopotential_alt,False,unitless -aircraft:engine:ignore_negative_thrust,False,unitless -aircraft:engine:interpolation_method,slinear,unitless -aircraft:engine:mass_scaler,1.0,unitless -aircraft:engine:mass,8176,lbm -aircraft:engine:reference_mass,8176,lbm -aircraft:engine:reference_sls_thrust,51250.,lbf -aircraft:engine:scale_mass,True,unitless -aircraft:engine:scale_performance,True,unitless -aircraft:engine:scaled_sls_thrust,51250,lbf -#aircraft:engine:subsonic_fuel_flow_scaler,1.0,unitless -#aircraft:engine:supersonic_fuel_flow_scaler,1.0,unitless -#aircraft:engine:thrust_reversers_mass_scaler,1.0,unitless -aircraft:engine:num_fuselage_engines,0,unitless -aircraft:engine:num_engines,4,unitless -aircraft:engine:num_wing_engines,4,unitless -aircraft:engine:wing_locations,[0.3561541339,0.555929667],unitless -#aircraft:fins:area,0.0,ft**2 -#aircraft:fins:mass_scaler,1.0,unitless -#aircraft:fins:mass,0.0,lbm -#aircraft:fins:num_fins,0,unitless -#aircraft:fins:taper_ratio,10.0,unitless -aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm -#aircraft:fuel:density_ratio,1.0,unitless -#aircraft:fuel:fuel_system_mass_scaler,1.0,unitless -aircraft:fuel:fuselage_fuel_capacity,0.0,lbm -aircraft:fuel:num_tanks,12,unitless -aircraft:fuel:total_capacity,341446,lbm -#aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless -#aircraft:furnishings:mass_scaler,1.0,unitless -aircraft:fuselage:length,230.58,ft -#aircraft:fuselage:mass_scaler,1.0,unitless -aircraft:fuselage:max_height,26.83,ft -aircraft:fuselage:max_width,23.9,ft -aircraft:fuselage:military_cargo_floor,True,unitless -aircraft:fuselage:num_fuselages,1,unitless -aircraft:fuselage:passenger_compartment_length,143.75,ft -aircraft:fuselage:planform_area,4462.78,ft**2 -#aircraft:fuselage:wetted_area_scaler,1.0,unitless -aircraft:horizontal_tail:area,965.8,ft**2 -aircraft:horizontal_tail:aspect_ratio,4.2,unitless -#aircraft:horizontal_tail:mass_scaler,1.0,unitless -aircraft:horizontal_tail:taper_ratio,0.43,unitless -aircraft:horizontal_tail:thickness_to_chord,0.16,unitless -aircraft:horizontal_tail:vertical_tail_fraction,1.0,unitless -#aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless -#aircraft:hydraulics:mass_scaler,1.0,unitless -#aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 -#aircraft:instruments:mass_scaler,1.0,unitless -#aircraft:landing_gear:carrier_based,False,unitless -#aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless -#aircraft:landing_gear:main_gear_oleo_length,45,inch -#aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless -#aircraft:landing_gear:nose_gear_oleo_length,45,inch -aircraft:nacelle:avg_diameter,9.15,ft -aircraft:nacelle:avg_length,20.56,ft -#aircraft:nacelle:mass_scaler,1.0,unitless -#aircraft:nacelle:wetted_area_scaler,1.0,unitless -#aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 -#aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless -#aircraft:propulsion:misc_mass_scaler,1.0,unitless -aircraft:vertical_tail:area,537.9,ft**2 -aircraft:vertical_tail:aspect_ratio,0.958,unitless -#aircraft:vertical_tail:mass_scaler,1.0,unitless -aircraft:vertical_tail:num_tails,1,unitless -aircraft:vertical_tail:taper_ratio,0.846,unitless -aircraft:vertical_tail:thickness_to_chord,0.157,unitless -#aircraft:vertical_tail:wetted_area_scaler,1.0,unitless -aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless -aircraft:wing:airfoil_technology,1.0,unitless -aircraft:wing:area,6200,ft**2 -aircraft:wing:aspect_ratio,7.75,unitless -#aircraft:wing:bending_mass_scaler,1.0,unitless -#aircraft:wing:composite_fraction,0.1,unitless -aircraft:wing:control_surface_area,2323.7,ft**2 -aircraft:wing:control_surface_area_ratio,0.37479,unitless -aircraft:wing:load_distribution_control,2.0,unitless -aircraft:wing:load_fraction,1.0,unitless -#aircraft:wing:mass_scaler,1.0,unitless -aircraft:wing:max_camber_at_70_semispan,0.0,unitless -#aircraft:wing:misc_mass_scaler,1.0,unitless -#aircraft:wing:shear_control_mass_scaler,1.0,unitless -aircraft:wing:span_efficiency_reduction,False,unitless -aircraft:wing:span,222.75,ft -#aircraft:wing:strut_bracing_factor,0.0,unitless -#aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless -aircraft:wing:sweep,20.0,deg -aircraft:wing:taper_ratio,0.419,unitless -aircraft:wing:thickness_to_chord,0.1284,unitless -aircraft:wing:ultimate_load_factor,3.75,unitless -aircraft:wing:var_sweep_mass_penalty,0.0,unitless -#aircraft:wing:wetted_area_scaler,1.0,unitless -aircraft:wing:num_integration_stations,50,unitless -aircraft:wing:thickness_to_chord_dist,0.1239,0.108,0.013,unitless -aircraft:wing:load_path_sweep_dist,0.0,0.0,deg -aircraft:wing:input_station_dist,0.0,0.3298,0.884,unitless -aircraft:wing:chord_per_semispan,0.362,0.2667,0.0456,unitless -aircraft:wing:glove_and_bat,0.0,ft**2 -aircraft:wing:detailed_wing,False,unitless - - -mission:constraints:max_mach,0.77,unitless -mission:design:cruise_altitude,34000,ft -mission:design:gross_mass,840000,lbm -mission:design:range,7000.0,NM -mission:design:thrust_takeoff_per_eng,51250,lbf -mission:landing:lift_coefficient_max,3.0,unitless -mission:design:mach,0.77,unitless -#mission:summary:fuel_flow_scaler,1.0,unitless -mission:takeoff:fuel_simple,6.32,lbm -mission:takeoff:lift_coefficient_max,3.62,unitless -mission:takeoff:lift_over_drag,19.5,unitless -settings:equations_of_motion,height_energy -settings:mass_method,FLOPS - - -### missions definition -# mission_name: payload -# times: 0, 50, 280, 300 -# altitudes: 0, 30000, 30000, 0 -# machs: 0.30, 0.77, 0.77, 0.30 -# optimize_altitudes: F,F,F -# optimize_machs: F,F,F -# takeoff: F -# landing: F diff --git a/aviary/examples/multi_missions/c5_models/c5_ferry_phase_info.py b/aviary/examples/multi_missions/c5_models/c5_ferry_phase_info.py deleted file mode 100644 index 6a472ed2f..000000000 --- a/aviary/examples/multi_missions/c5_models/c5_ferry_phase_info.py +++ /dev/null @@ -1,83 +0,0 @@ -phase_info = { - "pre_mission": {"include_takeoff": False, "optimize_mass": True}, - "climb_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.3, "unitless"), - "final_mach": (0.77, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), - "initial_altitude": (0.0, "ft"), - "final_altitude": (29500.0, "ft"), - "altitude_bounds": ((0.0, 30000.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": True, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((0.0, 0.0), "min"), - "duration_bounds": ((25.0, 75.0), "min"), - }, - "initial_guesses": {"time": ([0.0, 50.0], "min")}, - }, - "climb_2": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.77, "unitless"), - "final_mach": (0.77, "unitless"), - "mach_bounds": ((0.75, 0.79), "unitless"), - "initial_altitude": (29500.0, "ft"), - "final_altitude": (32000.0, "ft"), - "altitude_bounds": ((29000.0, 32500.0), "ft"), - "throttle_enforcement": "boundary_constraint", - "fix_initial": False, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((25.0, 75.0), "min"), - "duration_bounds": ((381.0, 1143.0), "min"), - }, - "initial_guesses": {"time": ([50.0, 762.0], "min")}, - }, - "descent_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.77, "unitless"), - "final_mach": (0.3, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), - "initial_altitude": (32000.0, "ft"), - "final_altitude": (0.0, "ft"), - "altitude_bounds": ((0.0, 32500.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": False, - "constrain_final": True, - "fix_duration": False, - "initial_bounds": ((406.0, 1218.0), "min"), - "duration_bounds": ((15.5, 46.5), "min"), - }, - "initial_guesses": {"time": ([812.0, 31.0], "min")}, - }, - "post_mission": { - "include_landing": False, - "constrain_range": True, - "target_range": (7001.59, "nmi"), - }, -} diff --git a/aviary/examples/multi_missions/c5_models/c5_intermediate.csv b/aviary/examples/multi_missions/c5_models/c5_intermediate.csv deleted file mode 100644 index cf7f415be..000000000 --- a/aviary/examples/multi_missions/c5_models/c5_intermediate.csv +++ /dev/null @@ -1,168 +0,0 @@ -# author: Chris Psenica -#aircraft:air_conditioning:mass_scaler,1.0,unitless -#aircraft:anti_icing:mass_scaler,1.0,unitless -#aircraft:apu:mass_scaler,1.0,unitless -#aircraft:avionics:mass_scaler,1.0,unitless -#aircraft:canard:area,0.0,ft**2 -#aircraft:canard:aspect_ratio,0.0,unitless -#aircraft:canard:thickness_to_chord,0.0,unitless -aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm -#aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless -#aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:mass_per_passenger,180.0,lbm - -aircraft:crew_and_payload:cargo_mass,120000.0,lbm -#aircraft:crew_and_payload:num_passengers,82,unitless -#aircraft:crew_and_payload:design:num_passengers,82,unitless - -#aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:num_flight_crew,7,unitless -#aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless -#aircraft:crew_and_payload:wing_cargo,0.0,lbm -#aircraft:design:base_area,0.0,ft**2 -#aircraft:design:empty_mass_margin_scaler,1.0,unitless -#aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless -#aircraft:design:touchdown_mass,498554,lbm -aircraft:design:reserve_fuel_additional,0,lbm -#aircraft:design:subsonic_drag_coeff_factor,1.0,unitless -#aircraft:design:supersonic_drag_coeff_factor,1.0,unitless -aircraft:design:use_alt_mass,False,unitless -#aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless -#aircraft:electrical:mass_scaler,1.0,unitless - -aircraft:engine:data_file,models/engines/CF6.deck,unitless - -aircraft:engine:additional_mass_fraction,0.,unitless -aircraft:engine:constant_fuel_consumption,0.,lbm/h - -aircraft:engine:flight_idle_thrust_fraction,0.0,unitless -aircraft:engine:flight_idle_max_fraction,1.0,unitless -aircraft:engine:flight_idle_min_fraction,0.08,unitless -#aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless -#aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless -aircraft:engine:generate_flight_idle,False,unitless -aircraft:engine:geopotential_alt,False,unitless -aircraft:engine:ignore_negative_thrust,False,unitless -aircraft:engine:interpolation_method,slinear,unitless -aircraft:engine:mass_scaler,1.0,unitless -aircraft:engine:mass,8176,lbm -aircraft:engine:reference_mass,8176,lbm -aircraft:engine:reference_sls_thrust,51250.,lbf -aircraft:engine:scale_mass,True,unitless -aircraft:engine:scale_performance,True,unitless -aircraft:engine:scaled_sls_thrust,51250,lbf -#aircraft:engine:subsonic_fuel_flow_scaler,1.0,unitless -#aircraft:engine:supersonic_fuel_flow_scaler,1.0,unitless -#aircraft:engine:thrust_reversers_mass_scaler,1.0,unitless -aircraft:engine:num_fuselage_engines,0,unitless -aircraft:engine:num_engines,4,unitless -aircraft:engine:num_wing_engines,4,unitless -aircraft:engine:wing_locations,[0.3561541339,0.555929667],unitless -#aircraft:fins:area,0.0,ft**2 -#aircraft:fins:mass_scaler,1.0,unitless -#aircraft:fins:mass,0.0,lbm -#aircraft:fins:num_fins,0,unitless -#aircraft:fins:taper_ratio,10.0,unitless -aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm -#aircraft:fuel:density_ratio,1.0,unitless -#aircraft:fuel:fuel_system_mass_scaler,1.0,unitless -aircraft:fuel:fuselage_fuel_capacity,0.0,lbm -aircraft:fuel:num_tanks,12,unitless -aircraft:fuel:total_capacity,341446,lbm -#aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless -#aircraft:furnishings:mass_scaler,1.0,unitless -aircraft:fuselage:length,230.58,ft -#aircraft:fuselage:mass_scaler,1.0,unitless -aircraft:fuselage:max_height,26.83,ft -aircraft:fuselage:max_width,23.9,ft -aircraft:fuselage:military_cargo_floor,True,unitless -aircraft:fuselage:num_fuselages,1,unitless -aircraft:fuselage:passenger_compartment_length,143.75,ft -aircraft:fuselage:planform_area,4462.78,ft**2 -#aircraft:fuselage:wetted_area_scaler,1.0,unitless -aircraft:horizontal_tail:area,965.8,ft**2 -aircraft:horizontal_tail:aspect_ratio,4.2,unitless -#aircraft:horizontal_tail:mass_scaler,1.0,unitless -aircraft:horizontal_tail:taper_ratio,0.43,unitless -aircraft:horizontal_tail:thickness_to_chord,0.16,unitless -aircraft:horizontal_tail:vertical_tail_fraction,1.0,unitless -#aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless -#aircraft:hydraulics:mass_scaler,1.0,unitless -#aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 -#aircraft:instruments:mass_scaler,1.0,unitless -#aircraft:landing_gear:carrier_based,False,unitless -#aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless -#aircraft:landing_gear:main_gear_oleo_length,45,inch -#aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless -#aircraft:landing_gear:nose_gear_oleo_length,45,inch -aircraft:nacelle:avg_diameter,9.15,ft -aircraft:nacelle:avg_length,20.56,ft -#aircraft:nacelle:mass_scaler,1.0,unitless -#aircraft:nacelle:wetted_area_scaler,1.0,unitless -#aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 -#aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless -#aircraft:propulsion:misc_mass_scaler,1.0,unitless -aircraft:vertical_tail:area,537.9,ft**2 -aircraft:vertical_tail:aspect_ratio,0.958,unitless -#aircraft:vertical_tail:mass_scaler,1.0,unitless -aircraft:vertical_tail:num_tails,1,unitless -aircraft:vertical_tail:taper_ratio,0.846,unitless -aircraft:vertical_tail:thickness_to_chord,0.157,unitless -#aircraft:vertical_tail:wetted_area_scaler,1.0,unitless -aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless -aircraft:wing:airfoil_technology,1.0,unitless -aircraft:wing:area,6200,ft**2 -aircraft:wing:aspect_ratio,7.75,unitless -#aircraft:wing:bending_mass_scaler,1.0,unitless -#aircraft:wing:composite_fraction,0.1,unitless -aircraft:wing:control_surface_area,2323.7,ft**2 -aircraft:wing:control_surface_area_ratio,0.37479,unitless -aircraft:wing:load_distribution_control,2.0,unitless -aircraft:wing:load_fraction,1.0,unitless -#aircraft:wing:mass_scaler,1.0,unitless -aircraft:wing:max_camber_at_70_semispan,0.0,unitless -#aircraft:wing:misc_mass_scaler,1.0,unitless -#aircraft:wing:shear_control_mass_scaler,1.0,unitless -aircraft:wing:span_efficiency_reduction,False,unitless -aircraft:wing:span,222.75,ft -#aircraft:wing:strut_bracing_factor,0.0,unitless -#aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless -aircraft:wing:sweep,20.0,deg -aircraft:wing:taper_ratio,0.419,unitless -aircraft:wing:thickness_to_chord,0.1284,unitless -aircraft:wing:ultimate_load_factor,3.75,unitless -aircraft:wing:var_sweep_mass_penalty,0.0,unitless -#aircraft:wing:wetted_area_scaler,1.0,unitless -aircraft:wing:num_integration_stations,50,unitless -aircraft:wing:thickness_to_chord_dist,0.1239,0.108,0.013,unitless -aircraft:wing:load_path_sweep_dist,0.0,0.0,deg -aircraft:wing:input_station_dist,0.0,0.3298,0.884,unitless -aircraft:wing:chord_per_semispan,0.362,0.2667,0.0456,unitless -aircraft:wing:glove_and_bat,0.0,ft**2 -aircraft:wing:detailed_wing,False,unitless - - -mission:constraints:max_mach,0.77,unitless -mission:design:cruise_altitude,34000,ft -mission:design:gross_mass,840000,lbm -mission:design:range,4800.0,NM -mission:design:thrust_takeoff_per_eng,51250,lbf -mission:landing:lift_coefficient_max,3.0,unitless -mission:design:mach,0.77,unitless -#mission:summary:fuel_flow_scaler,1.0,unitless -mission:takeoff:fuel_simple,6.32,lbm -mission:takeoff:lift_coefficient_max,3.62,unitless -mission:takeoff:lift_over_drag,19.5,unitless -settings:equations_of_motion,height_energy -settings:mass_method,FLOPS - - -### missions definition -# mission_name: payload -# times: 0, 50, 280, 300 -# altitudes: 0, 30000, 30000, 0 -# machs: 0.30, 0.77, 0.77, 0.30 -# optimize_altitudes: F,F,F -# optimize_machs: F,F,F -# takeoff: F -# landing: F diff --git a/aviary/examples/multi_missions/c5_models/c5_intermediate_phase_info.py b/aviary/examples/multi_missions/c5_models/c5_intermediate_phase_info.py deleted file mode 100644 index 88f121ca1..000000000 --- a/aviary/examples/multi_missions/c5_models/c5_intermediate_phase_info.py +++ /dev/null @@ -1,83 +0,0 @@ -phase_info = { - "pre_mission": {"include_takeoff": False, "optimize_mass": True}, - "climb_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.3, "unitless"), - "final_mach": (0.73, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), - "initial_altitude": (0.0, "ft"), - "final_altitude": (29500.0, "ft"), - "altitude_bounds": ((0.0, 30000.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": True, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((0.0, 0.0), "min"), - "duration_bounds": ((25.0, 75.0), "min"), - }, - "initial_guesses": {"time": ([0.0, 50.0], "min")}, - }, - "climb_2": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.73, "unitless"), - "final_mach": (0.73, "unitless"), - "mach_bounds": ((0.72, 0.74), "unitless"), - "initial_altitude": (29500.0, "ft"), - "final_altitude": (32000.0, "ft"), - "altitude_bounds": ((29000.0, 32500.0), "ft"), - "throttle_enforcement": "boundary_constraint", - "fix_initial": False, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((25.0, 75.0), "min"), - "duration_bounds": ((255.0, 765.0), "min"), - }, - "initial_guesses": {"time": ([50.0, 510.0], "min")}, - }, - "descent_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.73, "unitless"), - "final_mach": (0.3, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), - "initial_altitude": (32000.0, "ft"), - "final_altitude": (0.0, "ft"), - "altitude_bounds": ((0.0, 32500.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": False, - "constrain_final": True, - "fix_duration": False, - "initial_bounds": ((280.0, 840.0), "min"), - "duration_bounds": ((15.0, 45.0), "min"), - }, - "initial_guesses": {"time": ([560.0, 30.0], "min")}, - }, - "post_mission": { - "include_landing": False, - "constrain_range": True, - "target_range": (4839.41, "nmi"), - }, -} diff --git a/aviary/examples/multi_missions/c5_models/c5_maxpayload.csv b/aviary/examples/multi_missions/c5_models/c5_maxpayload.csv deleted file mode 100644 index f1f67b76d..000000000 --- a/aviary/examples/multi_missions/c5_models/c5_maxpayload.csv +++ /dev/null @@ -1,168 +0,0 @@ -# author: Chris Psenica -#aircraft:air_conditioning:mass_scaler,1.0,unitless -#aircraft:anti_icing:mass_scaler,1.0,unitless -#aircraft:apu:mass_scaler,1.0,unitless -#aircraft:avionics:mass_scaler,1.0,unitless -#aircraft:canard:area,0.0,ft**2 -#aircraft:canard:aspect_ratio,0.0,unitless -#aircraft:canard:thickness_to_chord,0.0,unitless -aircraft:crew_and_payload:baggage_mass_per_passenger,0.0,lbm -#aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless -#aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:mass_per_passenger,180.0,lbm - -aircraft:crew_and_payload:cargo_mass,281000.0,lbm -#aircraft:crew_and_payload:num_passengers,82,unitless -#aircraft:crew_and_payload:design:num_passengers,82,unitless - -#aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:num_flight_crew,7,unitless -#aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless -#aircraft:crew_and_payload:wing_cargo,0.0,lbm -#aircraft:design:base_area,0.0,ft**2 -#aircraft:design:empty_mass_margin_scaler,1.0,unitless -#aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless -#aircraft:design:touchdown_mass,498554,lbm -aircraft:design:reserve_fuel_additional,0,lbm -#aircraft:design:subsonic_drag_coeff_factor,1.0,unitless -#aircraft:design:supersonic_drag_coeff_factor,1.0,unitless -aircraft:design:use_alt_mass,False,unitless -#aircraft:design:zero_lift_drag_coeff_factor,1.0,unitless -#aircraft:electrical:mass_scaler,1.0,unitless - -aircraft:engine:data_file,models/engines/CF6.deck,unitless - -aircraft:engine:additional_mass_fraction,0.,unitless -aircraft:engine:constant_fuel_consumption,0.,lbm/h - -aircraft:engine:flight_idle_thrust_fraction,0.0,unitless -aircraft:engine:flight_idle_max_fraction,1.0,unitless -aircraft:engine:flight_idle_min_fraction,0.08,unitless -#aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless -#aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless -aircraft:engine:generate_flight_idle,False,unitless -aircraft:engine:geopotential_alt,False,unitless -aircraft:engine:ignore_negative_thrust,False,unitless -aircraft:engine:interpolation_method,slinear,unitless -aircraft:engine:mass_scaler,1.0,unitless -aircraft:engine:mass,8176,lbm -aircraft:engine:reference_mass,8176,lbm -aircraft:engine:reference_sls_thrust,51250.,lbf -aircraft:engine:scale_mass,True,unitless -aircraft:engine:scale_performance,True,unitless -aircraft:engine:scaled_sls_thrust,51250,lbf -#aircraft:engine:subsonic_fuel_flow_scaler,1.0,unitless -#aircraft:engine:supersonic_fuel_flow_scaler,1.0,unitless -#aircraft:engine:thrust_reversers_mass_scaler,1.0,unitless -aircraft:engine:num_fuselage_engines,0,unitless -aircraft:engine:num_engines,4,unitless -aircraft:engine:num_wing_engines,4,unitless -aircraft:engine:wing_locations,[0.3561541339,0.555929667],unitless -#aircraft:fins:area,0.0,ft**2 -#aircraft:fins:mass_scaler,1.0,unitless -#aircraft:fins:mass,0.0,lbm -#aircraft:fins:num_fins,0,unitless -#aircraft:fins:taper_ratio,10.0,unitless -aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm -#aircraft:fuel:density_ratio,1.0,unitless -#aircraft:fuel:fuel_system_mass_scaler,1.0,unitless -aircraft:fuel:fuselage_fuel_capacity,0.0,lbm -aircraft:fuel:num_tanks,12,unitless -aircraft:fuel:total_capacity,341446,lbm -#aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless -#aircraft:furnishings:mass_scaler,1.0,unitless -aircraft:fuselage:length,230.58,ft -#aircraft:fuselage:mass_scaler,1.0,unitless -aircraft:fuselage:max_height,26.83,ft -aircraft:fuselage:max_width,23.9,ft -aircraft:fuselage:military_cargo_floor,True,unitless -aircraft:fuselage:num_fuselages,1,unitless -aircraft:fuselage:passenger_compartment_length,143.75,ft -aircraft:fuselage:planform_area,4462.78,ft**2 -#aircraft:fuselage:wetted_area_scaler,1.0,unitless -aircraft:horizontal_tail:area,965.8,ft**2 -aircraft:horizontal_tail:aspect_ratio,4.2,unitless -#aircraft:horizontal_tail:mass_scaler,1.0,unitless -aircraft:horizontal_tail:taper_ratio,0.43,unitless -aircraft:horizontal_tail:thickness_to_chord,0.16,unitless -aircraft:horizontal_tail:vertical_tail_fraction,1.0,unitless -#aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless -#aircraft:hydraulics:mass_scaler,1.0,unitless -#aircraft:hydraulics:system_pressure,3000.0,lbf/ft**2 -#aircraft:instruments:mass_scaler,1.0,unitless -#aircraft:landing_gear:carrier_based,False,unitless -#aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless -#aircraft:landing_gear:main_gear_oleo_length,45,inch -#aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless -#aircraft:landing_gear:nose_gear_oleo_length,45,inch -aircraft:nacelle:avg_diameter,9.15,ft -aircraft:nacelle:avg_length,20.56,ft -#aircraft:nacelle:mass_scaler,1.0,unitless -#aircraft:nacelle:wetted_area_scaler,1.0,unitless -#aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 -#aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless -#aircraft:propulsion:misc_mass_scaler,1.0,unitless -aircraft:vertical_tail:area,537.9,ft**2 -aircraft:vertical_tail:aspect_ratio,0.958,unitless -#aircraft:vertical_tail:mass_scaler,1.0,unitless -aircraft:vertical_tail:num_tails,1,unitless -aircraft:vertical_tail:taper_ratio,0.846,unitless -aircraft:vertical_tail:thickness_to_chord,0.157,unitless -#aircraft:vertical_tail:wetted_area_scaler,1.0,unitless -aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless -aircraft:wing:airfoil_technology,1.0,unitless -aircraft:wing:area,6200,ft**2 -aircraft:wing:aspect_ratio,7.75,unitless -#aircraft:wing:bending_mass_scaler,1.0,unitless -#aircraft:wing:composite_fraction,0.1,unitless -aircraft:wing:control_surface_area,2323.7,ft**2 -aircraft:wing:control_surface_area_ratio,0.37479,unitless -aircraft:wing:load_distribution_control,2.0,unitless -aircraft:wing:load_fraction,1.0,unitless -#aircraft:wing:mass_scaler,1.0,unitless -aircraft:wing:max_camber_at_70_semispan,0.0,unitless -#aircraft:wing:misc_mass_scaler,1.0,unitless -#aircraft:wing:shear_control_mass_scaler,1.0,unitless -aircraft:wing:span_efficiency_reduction,False,unitless -aircraft:wing:span,222.75,ft -#aircraft:wing:strut_bracing_factor,0.0,unitless -#aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless -aircraft:wing:sweep,20.0,deg -aircraft:wing:taper_ratio,0.419,unitless -aircraft:wing:thickness_to_chord,0.1284,unitless -aircraft:wing:ultimate_load_factor,3.75,unitless -aircraft:wing:var_sweep_mass_penalty,0.0,unitless -#aircraft:wing:wetted_area_scaler,1.0,unitless -aircraft:wing:num_integration_stations,50,unitless -aircraft:wing:thickness_to_chord_dist,0.1239,0.108,0.013,unitless -aircraft:wing:load_path_sweep_dist,0.0,0.0,deg -aircraft:wing:input_station_dist,0.0,0.3298,0.884,unitless -aircraft:wing:chord_per_semispan,0.362,0.2667,0.0456,unitless -aircraft:wing:glove_and_bat,0.0,ft**2 -aircraft:wing:detailed_wing,False,unitless - - -mission:constraints:max_mach,0.77,unitless -mission:design:cruise_altitude,34000,ft -mission:design:gross_mass,840000,lbm -mission:design:range,2150.0,NM -mission:design:thrust_takeoff_per_eng,51250,lbf -mission:landing:lift_coefficient_max,3.0,unitless -mission:design:mach,0.77,unitless -#mission:summary:fuel_flow_scaler,1.0,unitless -mission:takeoff:fuel_simple,6.32,lbm -mission:takeoff:lift_coefficient_max,3.62,unitless -mission:takeoff:lift_over_drag,19.5,unitless -settings:equations_of_motion,height_energy -settings:mass_method,FLOPS - - -### missions definition -# mission_name: payload -# times: 0, 50, 280, 300 -# altitudes: 0, 30000, 30000, 0 -# machs: 0.30, 0.77, 0.77, 0.30 -# optimize_altitudes: F,F,F -# optimize_machs: F,F,F -# takeoff: F -# landing: F diff --git a/aviary/examples/multi_missions/c5_models/c5_maxpayload_phase_info.py b/aviary/examples/multi_missions/c5_models/c5_maxpayload_phase_info.py deleted file mode 100644 index a52acec96..000000000 --- a/aviary/examples/multi_missions/c5_models/c5_maxpayload_phase_info.py +++ /dev/null @@ -1,83 +0,0 @@ -phase_info = { - "pre_mission": {"include_takeoff": False, "optimize_mass": True}, - "climb_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.3, "unitless"), - "final_mach": (0.77, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), - "initial_altitude": (0.0, "ft"), - "final_altitude": (29500.0, "ft"), - "altitude_bounds": ((0.0, 30000.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": True, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((0.0, 0.0), "min"), - "duration_bounds": ((25.0, 75.0), "min"), - }, - "initial_guesses": {"time": ([0.0, 50.0], "min")}, - }, - "climb_2": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.77, "unitless"), - "final_mach": (0.77, "unitless"), - "mach_bounds": ((0.75, 0.79), "unitless"), - "initial_altitude": (29500.0, "ft"), - "final_altitude": (32000.0, "ft"), - "altitude_bounds": ((29000.0, 32500.0), "ft"), - "throttle_enforcement": "boundary_constraint", - "fix_initial": False, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((25.0, 75.0), "min"), - "duration_bounds": ((105.0, 315.0), "min"), - }, - "initial_guesses": {"time": ([50.0, 210.0], "min")}, - }, - "descent_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.77, "unitless"), - "final_mach": (0.3, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.79), "unitless"), - "initial_altitude": (32000.0, "ft"), - "final_altitude": (0.0, "ft"), - "altitude_bounds": ((0.0, 32500.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": False, - "constrain_final": True, - "fix_duration": False, - "initial_bounds": ((130.0, 390.0), "min"), - "duration_bounds": ((15.0, 45.0), "min"), - }, - "initial_guesses": {"time": ([260.0, 30.0], "min")}, - }, - "post_mission": { - "include_landing": False, - "constrain_range": True, - "target_range": (2272.47, "nmi"), - }, -} From 1cb3a9e2d5ed4256536b71bfccbf4e2cded7d01b Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Wed, 11 Sep 2024 15:28:50 -0400 Subject: [PATCH 059/113] removed FwFm.csv changes --- .../test_aircraft/aircraft_for_bench_FwFm.csv | 11 +- .../aircraft_for_bench_FwFm_deadhead.csv | 162 ------------------ 2 files changed, 2 insertions(+), 171 deletions(-) delete mode 100644 aviary/models/test_aircraft/aircraft_for_bench_FwFm_deadhead.csv diff --git a/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv b/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv index 55ee2cac3..c2fa1d8a1 100644 --- a/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv +++ b/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv @@ -11,20 +11,13 @@ aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless aircraft:crew_and_payload:mass_per_passenger,180.0,lbm aircraft:crew_and_payload:misc_cargo,0.0,lbm aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless - +aircraft:crew_and_payload:num_business_class,0,unitless +aircraft:crew_and_payload:num_first_class,11,unitless aircraft:crew_and_payload:num_flight_attendants,3,unitless aircraft:crew_and_payload:num_flight_crew,2,unitless aircraft:crew_and_payload:num_galley_crew,0,unitless - -aircraft:crew_and_payload:design:num_passengers,169,unitless -aircraft:crew_and_payload:design:num_tourist_class,158,unitless -aircraft:crew_and_payload:design:num_business_class,0,unitless -aircraft:crew_and_payload:design:num_first_class,11,unitless aircraft:crew_and_payload:num_passengers,169,unitless aircraft:crew_and_payload:num_tourist_class,158,unitless -aircraft:crew_and_payload:num_business_class,0,unitless -aircraft:crew_and_payload:num_first_class,11,unitless - aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless aircraft:crew_and_payload:wing_cargo,0.0,lbm aircraft:design:base_area,0.0,ft**2 diff --git a/aviary/models/test_aircraft/aircraft_for_bench_FwFm_deadhead.csv b/aviary/models/test_aircraft/aircraft_for_bench_FwFm_deadhead.csv deleted file mode 100644 index 1e61f864a..000000000 --- a/aviary/models/test_aircraft/aircraft_for_bench_FwFm_deadhead.csv +++ /dev/null @@ -1,162 +0,0 @@ -aircraft:air_conditioning:mass_scaler,1.0,unitless -aircraft:anti_icing:mass_scaler,1.0,unitless -aircraft:apu:mass_scaler,1.1,unitless -aircraft:avionics:mass_scaler,1.2,unitless -aircraft:canard:area,0.0,ft**2 -aircraft:canard:aspect_ratio,0.0,unitless -aircraft:canard:thickness_to_chord,0.0,unitless -aircraft:crew_and_payload:baggage_mass_per_passenger,45.0,lbm -aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless -aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:mass_per_passenger,180.0,lbm -aircraft:crew_and_payload:misc_cargo,0.0,lbm -aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:num_flight_attendants,3,unitless -aircraft:crew_and_payload:num_flight_crew,2,unitless -aircraft:crew_and_payload:num_galley_crew,0,unitless - -aircraft:crew_and_payload:design:num_passengers,169,unitless -aircraft:crew_and_payload:design:num_tourist_class,158,unitless -aircraft:crew_and_payload:design:num_business_class,0,unitless -aircraft:crew_and_payload:design:num_first_class,11,unitless -aircraft:crew_and_payload:num_passengers,0,unitless -aircraft:crew_and_payload:num_tourist_class,0,unitless -aircraft:crew_and_payload:num_business_class,0,unitless -aircraft:crew_and_payload:num_first_class,0,unitless - -aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless -aircraft:crew_and_payload:wing_cargo,0.0,lbm -aircraft:design:base_area,0.0,ft**2 -aircraft:design:empty_mass_margin_scaler,0.0,unitless -aircraft:design:lift_dependent_drag_coeff_factor,0.909839381134961,unitless -aircraft:design:touchdown_mass,152800.0,lbm -aircraft:design:reserve_fuel_additional,3000.,lbm -aircraft:design:subsonic_drag_coeff_factor,1.0,unitless -aircraft:design:supersonic_drag_coeff_factor,1.0,unitless -aircraft:design:use_alt_mass,False,unitless -aircraft:design:zero_lift_drag_coeff_factor,0.930890028006548,unitless -aircraft:electrical:mass_scaler,1.25,unitless -aircraft:engine:additional_mass_fraction,0.,unitless -aircraft:engine:constant_fuel_consumption,0.,lbm/h -aircraft:engine:data_file,models/engines/turbofan_28k.deck,unitless -aircraft:engine:flight_idle_thrust_fraction,0.0,unitless -aircraft:engine:flight_idle_max_fraction,1.0,unitless -aircraft:engine:flight_idle_min_fraction,0.08,unitless -aircraft:engine:fuel_flow_scaler_constant_term,0.,unitless -aircraft:engine:fuel_flow_scaler_linear_term,0.,unitless -aircraft:engine:generate_flight_idle,True,unitless -aircraft:engine:geopotential_alt,False,unitless -aircraft:engine:ignore_negative_thrust,False,unitless -aircraft:engine:interpolation_method,slinear,unitless -aircraft:engine:mass_scaler,1.15,unitless -aircraft:engine:mass,7400,lbm -aircraft:engine:num_engines,2,unitless -aircraft:engine:num_fuselage_engines,0,unitless -aircraft:engine:num_wing_engines,2,unitless -aircraft:engine:reference_mass,7400,lbm -aircraft:engine:reference_sls_thrust,28928.1,lbf -aircraft:engine:scale_mass,True,unitless -aircraft:engine:scale_performance,True,unitless -aircraft:engine:scaled_sls_thrust,28928.1,lbf -aircraft:engine:subsonic_fuel_flow_scaler,1.,unitless -aircraft:engine:supersonic_fuel_flow_scaler,1.,unitless -aircraft:engine:thrust_reversers_mass_scaler,0.0,unitless -aircraft:engine:wing_locations,[0.26869218],unitless -aircraft:fins:area,0.0,ft**2 -aircraft:fins:mass_scaler,1.0,unitless -aircraft:fins:mass,0.0,lbm -aircraft:fins:num_fins,0,unitless -aircraft:fins:taper_ratio,10.0,unitless -aircraft:fuel:auxiliary_fuel_capacity,0.0,lbm -aircraft:fuel:density_ratio,1.0,unitless -aircraft:fuel:fuel_system_mass_scaler,1.0,unitless -aircraft:fuel:fuselage_fuel_capacity,0.0,lbm -aircraft:fuel:num_tanks,7,unitless -aircraft:fuel:total_capacity,45694.0,lbm -aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless -aircraft:furnishings:mass_scaler,1.1,unitless -aircraft:fuselage:length,128.0,ft -aircraft:fuselage:mass_scaler,1.05,unitless -aircraft:fuselage:max_height,13.17,ft -aircraft:fuselage:max_width,12.33,ft -aircraft:fuselage:military_cargo_floor,False,unitless -aircraft:fuselage:num_fuselages,1,unitless -aircraft:fuselage:passenger_compartment_length,85.5,ft -aircraft:fuselage:planform_area,1578.24,ft**2 -aircraft:fuselage:wetted_area_scaler,1.0,unitless -aircraft:fuselage:wetted_area,4158.62,ft**2 -aircraft:horizontal_tail:area,355.0,ft**2 -aircraft:horizontal_tail:aspect_ratio,6.0,unitless -aircraft:horizontal_tail:mass_scaler,1.2,unitless -aircraft:horizontal_tail:taper_ratio,0.22,unitless -aircraft:horizontal_tail:thickness_to_chord,0.125,unitless -aircraft:horizontal_tail:vertical_tail_fraction,0.0,unitless -aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless -aircraft:horizontal_tail:wetted_area,592.65,ft**2 -aircraft:hydraulics:mass_scaler,1.0,unitless -aircraft:hydraulics:system_pressure,3000,psi -aircraft:instruments:mass_scaler,1.25,unitless -aircraft:landing_gear:carrier_based,False,unitless -aircraft:landing_gear:main_gear_mass_scaler,1.1,unitless -aircraft:landing_gear:main_gear_oleo_length,102.0,inch -aircraft:landing_gear:nose_gear_mass_scaler,1.0,unitless -aircraft:landing_gear:nose_gear_oleo_length,67.0,inch -aircraft:nacelle:avg_diameter,7.94,ft -aircraft:nacelle:avg_length,12.3,ft -aircraft:nacelle:mass_scaler,1.0,unitless -aircraft:nacelle:wetted_area_scaler,1.0,unitless -aircraft:paint:mass_per_unit_area,0.037,lbm/ft**2 -aircraft:propulsion:engine_oil_mass_scaler,1.0,unitless -aircraft:propulsion:misc_mass_scaler,1.0,unitless -aircraft:vertical_tail:area,284.0,ft**2 -aircraft:vertical_tail:aspect_ratio,1.75,unitless -aircraft:vertical_tail:mass_scaler,1.0,unitless -aircraft:vertical_tail:num_tails,1,unitless -aircraft:vertical_tail:taper_ratio,0.33,unitless -aircraft:vertical_tail:thickness_to_chord,0.1195,unitless -aircraft:vertical_tail:wetted_area_scaler,1.0,unitless -aircraft:vertical_tail:wetted_area,581.13,ft**2 -aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless -aircraft:wing:airfoil_technology,1.92669766647637,unitless -aircraft:wing:area,1370.0,ft**2 -aircraft:wing:aspect_ratio,11.22091,unitless -aircraft:wing:bending_mass_scaler,1.0,unitless -aircraft:wing:chord_per_semispan,0.31,0.23,0.084,unitless -aircraft:wing:composite_fraction,0.2,unitless -aircraft:wing:control_surface_area,137,ft**2 -aircraft:wing:control_surface_area_ratio,0.1,unitless -aircraft:wing:glove_and_bat,134.0,ft**2 -aircraft:wing:input_station_dist,0.,0.2759,0.9367,unitless -aircraft:wing:load_distribution_control,2.0,unitless -aircraft:wing:load_fraction,1.0,unitless -aircraft:wing:load_path_sweep_dist,0.,22.,deg -aircraft:wing:mass_scaler,1.23,unitless -aircraft:wing:max_camber_at_70_semispan,0.0,unitless -aircraft:wing:misc_mass_scaler,1.0,unitless -aircraft:wing:num_integration_stations,50,unitless -aircraft:wing:shear_control_mass_scaler,1.0,unitless -aircraft:wing:span_efficiency_reduction,False,unitless -aircraft:wing:span,117.83,ft -aircraft:wing:strut_bracing_factor,0.0,unitless -aircraft:wing:surface_ctrl_mass_scaler,1.0,unitless -aircraft:wing:sweep,25.0,deg -aircraft:wing:taper_ratio,0.278,unitless -aircraft:wing:thickness_to_chord_dist,0.145,0.115,0.104,unitless -aircraft:wing:thickness_to_chord,0.13,unitless -aircraft:wing:ultimate_load_factor,3.75,unitless -aircraft:wing:var_sweep_mass_penalty,0.0,unitless -aircraft:wing:wetted_area_scaler,1.0,unitless -aircraft:wing:wetted_area,2396.56,ft**2 -mission:constraints:max_mach,0.785,unitless -mission:design:cruise_altitude,35000,ft -mission:design:gross_mass,175400.0,lbm -mission:design:range,3500,NM -mission:design:thrust_takeoff_per_eng,28928.1,lbf -mission:landing:lift_coefficient_max,2.0,unitless -mission:summary:cruise_mach,0.785,unitless -mission:summary:fuel_flow_scaler,1.0,unitless -mission:takeoff:fuel_simple,577,lbm -mission:takeoff:lift_coefficient_max,3.0,unitless -mission:takeoff:lift_over_drag,17.354,unitless -settings:equations_of_motion,height_energy -settings:mass_method,FLOPS \ No newline at end of file From deab1d6688b0d3a5da5cf4f11bcf8a88f9685695 Mon Sep 17 00:00:00 2001 From: Kaushik Ponnapalli Date: Wed, 11 Sep 2024 14:29:25 -0500 Subject: [PATCH 060/113] Connected mass of first flight phase to gross_mass --- aviary/interface/methods_for_level2.py | 22 ++++++++++++++++++++++ 1 file changed, 22 insertions(+) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index 6d5c016e2..fe380397d 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -1102,6 +1102,13 @@ def add_subsystem_timeseries_outputs(phase, phase_name): traj = setup_trajectory_params( self.model, traj, self.aviary_inputs, phases, meta_data=self.meta_data, external_parameters=external_parameters) + if self.mission_method is HEIGHT_ENERGY: + if not self.pre_mission_info['include_takeoff']: + first_flight_phase_name = list(phase_info.keys())[0] + first_flight_phase = traj._phases[first_flight_phase_name] + first_flight_phase.set_state_options(Dynamic.Mission.MASS, + fix_initial=False) + self.traj = traj return traj @@ -1428,6 +1435,21 @@ def link_phases(self): Mission.Summary.RANGE, src_indices=[-1], flat_src_indices=True) + if not self.pre_mission_info['include_takeoff']: + first_flight_phase_name = list(self.phase_info.keys())[0] + eq = self.model.add_subsystem(f'link_{first_flight_phase_name}_mass', + om.EQConstraintComp(), + promotes_inputs=[('rhs:mass', + Mission.Summary.GROSS_MASS)]) + eq.add_eq_output('mass', eq_units='lbm', normalize=False, + ref=10000., add_constraint=True) + self.model.connect( + f'traj.{first_flight_phase_name}.states:mass', + 'link_climb_mass.lhs:mass', + src_indices=[0], + flat_src_indices=True, + ) + elif self.mission_method is SOLVED_2DOF: self.traj.link_phases(phases, [Dynamic.Mission.MASS], connected=True) self.traj.link_phases( From e16273c8002e60b154bd40460fa2c05963c2e832 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Wed, 11 Sep 2024 15:31:37 -0400 Subject: [PATCH 061/113] removed additional unneeded files --- cannonball_models/cannonball.py | 308 ----------- .../multi_cannonball_copymodel.py | 409 --------------- .../multi_cannonball_copyparts.py | 484 ------------------ easy_phase_info_inter.py | 83 --- easy_phase_info_max.py | 83 --- min_time_climb_models/min_time_climb.py | 301 ----------- .../multi_min_time_to_climb.py | 173 ------- min_time_climb_models/plot_helper.py | 98 ---- multi_aviary_submodel.py | 125 ----- single_aviary.py | 129 ----- 10 files changed, 2193 deletions(-) delete mode 100644 cannonball_models/cannonball.py delete mode 100644 cannonball_models/multi_cannonball_copymodel.py delete mode 100644 cannonball_models/multi_cannonball_copyparts.py delete mode 100644 easy_phase_info_inter.py delete mode 100644 easy_phase_info_max.py delete mode 100644 min_time_climb_models/min_time_climb.py delete mode 100644 min_time_climb_models/multi_min_time_to_climb.py delete mode 100644 min_time_climb_models/plot_helper.py delete mode 100644 multi_aviary_submodel.py delete mode 100644 single_aviary.py diff --git a/cannonball_models/cannonball.py b/cannonball_models/cannonball.py deleted file mode 100644 index fc2fe1b9a..000000000 --- a/cannonball_models/cannonball.py +++ /dev/null @@ -1,308 +0,0 @@ -# Cannonball Multi Mission Example -# A single openMDAO problem is populated with Sizing (pre-mission) -# and Trajectory subsystems (any number of missions) -import numpy as np -from scipy.interpolate import interp1d -import matplotlib.pyplot as plt -import openmdao.api as om -import dymos as dm -from dymos.models.atmosphere.atmos_1976 import USatm1976Data - -""" -Currently has linked sizing and motion ODEs, want to add ability to have -multiple trajectories (and associated ODEs) that are linked with the same -sizing class. radii/density etc can be defined as 1xn inputs, with n corresponding -to num of missions. - -Additionally need to incorporate some output into a compound objective that is optimized, -aside from each mission optimizing for max range. Could for example assign $/kg of material. - -Could also add a "fuel" parameter which can then be minimized. -""" - - -class CannonballSizing(om.ExplicitComponent): - def setup(self): - self.add_input(name='radius', val=1.0, units='m') - self.add_input(name='dens', val=7870., units='kg/m**3') - - self.add_output(name='mass', shape=(1,), units='kg') - self.add_output(name='S', shape=(1,), units='m**2') - self.add_output(name='price', shape=(1,), units='USD') - - self.declare_partials(of='mass', wrt='dens') - self.declare_partials(of='mass', wrt='radius') - self.declare_partials(of='S', wrt='radius') - self.declare_partials(of='price', wrt='radius') - self.declare_partials(of='price', wrt='dens') - - def compute(self, inputs, outputs): - radius = inputs['radius'] - dens = inputs['dens'] - outputs['mass'] = (4/3.) * dens * np.pi * radius ** 3 - outputs['S'] = np.pi * radius ** 2 - outputs['price'] = (4/3.) * dens * np.pi * radius ** 3 * 10 # $10 per kg - - def compute_partials(self, inputs, partials): - radius = inputs['radius'] - dens = inputs['dens'] - partials['mass', 'dens'] = (4/3.) * np.pi * radius ** 3 - partials['mass', 'radius'] = 4. * dens * np.pi * radius ** 2 - partials['S', 'radius'] = 2 * np.pi * radius - partials['price', 'dens'] = (4/3.) * np.pi * radius ** 3 * 10 - partials['price', 'radius'] = 4. * dens * np.pi * radius ** 2 * 10 - - -class CannonballODE(om.ExplicitComponent): - def initialize(self): - self.options.declare('num_nodes', types=int) - - def setup(self): - nn = self.options['num_nodes'] - # static params - self.add_input('m', units='kg') - self.add_input('S', units='m**2') - self.add_input('CD', 0.5) - - # time varying inputs - self.add_input('h', units='m', shape=nn) - self.add_input('v', units='m/s', shape=nn) - self.add_input('gam', units='rad', shape=nn) - - # state rates - self.add_output('v_dot', shape=nn, units='m/s**2', - tags=['dymos.state_rate_source:v']) - self.add_output('gam_dot', shape=nn, units='rad/s', - tags=['dymos.state_rate_source:gam']) - self.add_output('h_dot', shape=nn, units='m/s', - tags=['dymos.state_rate_source:h']) - self.add_output('r_dot', shape=nn, units='m/s', - tags=['dymos.state_rate_source:r']) - self.add_output('ke', shape=nn, units='J') - - # Ask OpenMDAO to compute the partial derivatives using complex-step - # with a partial coloring algorithm for improved performance, and use - # a graph coloring algorithm to automatically detect the sparsity pattern. - self.declare_coloring(wrt='*', method='cs') - - alt_data = USatm1976Data.alt * om.unit_conversion('ft', 'm')[0] - rho_data = USatm1976Data.rho * om.unit_conversion('slug/ft**3', 'kg/m**3')[0] - self.rho_interp = interp1d(np.array(alt_data, dtype=complex), - np.array(rho_data, dtype=complex), - kind='linear') - - def compute(self, inputs, outputs): - - gam = inputs['gam'] - v = inputs['v'] - h = inputs['h'] - m = inputs['m'] - S = inputs['S'] - CD = inputs['CD'] - - GRAVITY = 9.80665 # m/s**2 - - # handle complex-step gracefully from the interpolant - if np.iscomplexobj(h): - rho = self.rho_interp(inputs['h']) - else: - rho = self.rho_interp(inputs['h']).real - - q = 0.5*rho*inputs['v']**2 - qS = q * S - D = qS * CD - cgam = np.cos(gam) - sgam = np.sin(gam) - outputs['v_dot'] = - D/m-GRAVITY*sgam - outputs['gam_dot'] = -(GRAVITY/v)*cgam - outputs['h_dot'] = v*sgam - outputs['r_dot'] = v*cgam - outputs['ke'] = 0.5*m*v**2 - - -# ODEs are unique to each traj created -def createTrajectory(ke_max): - traj = dm.Trajectory() - transcription = dm.Radau(num_segments=5, order=3, compressed=True) - ascent = dm.Phase(ode_class=CannonballODE, transcription=transcription) - traj.add_phase('ascent', ascent) - - transcription = dm.GaussLobatto(num_segments=5, order=3, compressed=True) - descent = dm.Phase(ode_class=CannonballODE, transcription=transcription) - traj.add_phase('descent', descent) - - for phase in (ascent, descent): - is_ascent = phase.name == "ascent" - phase.set_time_options(fix_initial=True if is_ascent else False, - duration_bounds=(1, 100), duration_ref=100, units='s') - phase.set_state_options('r', fix_initial=is_ascent, fix_final=False) - phase.set_state_options('h', fix_initial=is_ascent, fix_final=not is_ascent) - phase.set_state_options('gam', fix_initial=False, fix_final=is_ascent) - phase.set_state_options('v', fix_initial=False, fix_final=False) - phase.add_parameter('S', units='m**2', static_target=True, val=0.005) - phase.add_parameter('m', units='kg', static_target=True, val=1.0) - phase.add_parameter('price', units='USD', static_target=True, val=10) - phase.add_parameter('CD', units=None, static_target=True, val=0.5) - - # descent.add_objective('r', loc='final', scaler=-1.0) # negative means to maximize - for param in ('CD', 'm', 'S', 'price'): - traj.add_parameter(param, static_target=True) - - # Link Phases (link time and all state variables) - traj.link_phases(phases=['ascent', 'descent'], vars=['*']) - # have to set muzzle energy here before setup for sim to run properly - ascent.add_boundary_constraint('ke', loc='initial', - upper=ke_max, lower=0, ref=100000) - return traj, ascent, descent - - -p = om.Problem(model=om.Group()) - -p.driver = om.ScipyOptimizeDriver() -p.driver.options['optimizer'] = 'SLSQP' -p.driver.declare_coloring() - -kes = [4e5, 5e5] -# 2:1 ratio (or 1:2) causes results that essentially don't optimize the 1 mission, -# 1.01 works, 1.009 doesn't -# 2:1:1 works?! - may be related some normalization/bounds issue -weights = [1, 1] -num_trajs = len(kes) - -p.model.add_subsystem(f"sizing_comp", CannonballSizing(), - promotes_inputs=['radius', 'dens']) - -p.model.set_input_defaults('dens', val=7.87, units='g/cm**3') -p.model.add_design_var('radius', lower=0.01, upper=0.10, - ref0=0.01, ref=0.10, units='m') - -trajs, ascents, descents = [], [], [] -for i, ke in enumerate(kes): - traj, ascent, descent = createTrajectory(ke) - p.model.add_subsystem(f"traj_{i}", traj) - - # Issue Connections - p.model.connect(f"sizing_comp.mass", f"traj_{i}.parameters:m") - p.model.connect(f"sizing_comp.S", f"traj_{i}.parameters:S") - p.model.connect(f"sizing_comp.price", f"traj_{i}.parameters:price") - trajs.append(traj) - ascents.append(ascent) - descents.append(descent) - -ranges = [f"r{i}" for i in range(num_trajs)] -weighted_sum_str = "+".join([f"{weight}*{r}" for r, weight in zip(ranges, weights)]) -p.model.add_subsystem('compoundComp', om.ExecComp("compound_range="+weighted_sum_str), - promotes=['compound_range', *ranges]) -for i in range(num_trajs): - p.model.connect(f"traj_{i}.descent.states:r", f'r{i}', src_indices=-1) -# p.model.add_subsystem('compoundComp', -# om.ExecComp("compound_range=dot(ranges,weights)", -# weights={'val': weights}, -# ranges={'val': np.ones(num_trajs), 'units': 'm'}), -# promotes=['compound_range', 'ranges', 'weights']) - -# gg = [f'traj_{i}.descent.states:r' for i in range(num_trajs)] -# p.model.connect(gg, 'ranges', src_indices=-1) -# for i in range(num_trajs): -# p.model.connect(f"traj_{i}.descent.states:r", f'ranges[{i}]', src_indices=-1) - -p.model.add_objective('compound_range', scaler=-1) - - -# A linear solver at the top level can improve performance. -p.model.linear_solver = om.DirectSolver() -p.setup() - -p.set_val('radius', 0.05, units='m') -p.set_val('dens', 7.87, units='g/cm**3') - -for i, (ascent, descent) in enumerate(zip(ascents, descents)): - p.set_val(f"traj_{i}.parameters:CD", 0.5) - - p.set_val(f"traj_{i}.ascent.t_initial", 0.0) - p.set_val(f"traj_{i}.ascent.t_duration", 10.0) - # list is initial and final, based on phase info some are fixed others are not - p.set_val(f"traj_{i}.ascent.states:r", ascent.interp('r', [0, 100])) - p.set_val(f'traj_{i}.ascent.states:h', ascent.interp('h', [0, 100])) - p.set_val(f'traj_{i}.ascent.states:v', ascent.interp('v', [200, 150])) - p.set_val(f'traj_{i}.ascent.states:gam', ascent.interp('gam', [25, 0]), units='deg') - - p.set_val(f'traj_{i}.descent.t_initial', 10.0) - p.set_val(f'traj_{i}.descent.t_duration', 10.0) - - p.set_val(f'traj_{i}.descent.states:r', descent.interp('r', [100, 200])) - p.set_val(f'traj_{i}.descent.states:h', descent.interp('h', [100, 0])) - p.set_val(f'traj_{i}.descent.states:v', descent.interp('v', [150, 200])) - p.set_val(f'traj_{i}.descent.states:gam', - descent.interp('gam', [0, -45]), units='deg') - - -dm.run_problem(p, simulate=True) -sol = om.CaseReader('dymos_solution.db').get_case('final') -sim = om.CaseReader('dymos_simulation.db').get_case('final') - - -def plotstuff(): - print("\n\n=================================================") - print( - f"Optimized {num_trajs} trajectories with weights: {', '.join(map(str,weights))}") - rad = p.get_val('radius', units='cm')[0] - mass = p.get_val('sizing_comp.mass', units='kg')[0] - price = p.get_val('sizing_comp.price', units='USD')[0] - area = p.get_val('sizing_comp.S', units='cm**2')[0] - print("\nOptimal Cannonball Description:") - print( - f"\tRadius: {rad:.2f} cm, Mass: {mass:.2f} kg, Price: ${price:.2f}, Area: {area:.2f} sqcm") - - print("\nOptimal Trajectory Descriptions:") - for i, ke in enumerate(kes): - angle = p.get_val(f'traj_{i}.ascent.timeseries.gam', units='deg')[0, 0] - max_range = p.get_val(f'traj_{i}.descent.timeseries.r')[-1, 0] - - print( - f"\tKE: {ke/1e3:.2f} KJ, Launch Angle: {angle:.2f} deg, Max Range: {max_range:.2f} m") - - # fig, axes = plt.subplots(nrows=1, ncols=1, figsize=(10, 6)) - # time_imp = {'ascent': p.get_val('traj_0.ascent.timeseries.time'), - # 'descent': p.get_val('traj_0.descent.timeseries.time')} - # time_exp = {'ascent': sim.get_val('traj_0.ascent.timeseries.time'), - # 'descent': sim.get_val('traj_0.descent.timeseries.time')} - # r_imp = {'ascent': p.get_val('traj_0.ascent.timeseries.r'), - # 'descent': p.get_val('traj_0.descent.timeseries.r')} - # r_exp = {'ascent': sim.get_val('traj_0.ascent.timeseries.r'), - # 'descent': sim.get_val('traj_0.descent.timeseries.r')} - # h_imp = {'ascent': p.get_val('traj_0.ascent.timeseries.h'), - # 'descent': p.get_val('traj_0.descent.timeseries.h')} - # h_exp = {'ascent': sim.get_val('traj_0.ascent.timeseries.h'), - # 'descent': sim.get_val('traj_0.descent.timeseries.h')} - - # axes.plot(r_imp['ascent'], h_imp['ascent'], 'bo') - # axes.plot(r_imp['descent'], h_imp['descent'], 'ro') - # axes.plot(r_exp['ascent'], h_exp['ascent'], 'b--') - # axes.plot(r_exp['descent'], h_exp['descent'], 'r--') - - # axes.set_xlabel('range (m)') - # axes.set_ylabel('altitude (m)') - # axes.grid(True) - - # fig, axes = plt.subplots(nrows=4, ncols=1, figsize=(10, 6)) - # states = ['r', 'h', 'v', 'gam'] - # for i, state in enumerate(states): - # x_imp = {'ascent': sol.get_val(f'traj_0.ascent.timeseries.{state}'), - # 'descent': sol.get_val(f'traj_0.descent.timeseries.{state}')} - - # x_exp = {'ascent': sim.get_val(f'traj_0.ascent.timeseries.{state}'), - # 'descent': sim.get_val(f'traj_0.descent.timeseries.{state}')} - - # axes[i].set_ylabel(state) - # axes[i].grid(True) - - # axes[i].plot(time_imp['ascent'], x_imp['ascent'], 'bo') - # axes[i].plot(time_imp['descent'], x_imp['descent'], 'ro') - # axes[i].plot(time_exp['ascent'], x_exp['ascent'], 'b--') - # axes[i].plot(time_exp['descent'], x_exp['descent'], 'r--') - - # plt.show() - - -plotstuff() diff --git a/cannonball_models/multi_cannonball_copymodel.py b/cannonball_models/multi_cannonball_copymodel.py deleted file mode 100644 index 06effc571..000000000 --- a/cannonball_models/multi_cannonball_copymodel.py +++ /dev/null @@ -1,409 +0,0 @@ -# Cannonball Multi Mission Example with Aviary-esque setup -# Each mission is defined as a "CannonballProblem", akin to AviaryProblem -from dymos.models.atmosphere.atmos_1976 import USatm1976Data -from scipy.interpolate import interp1d -import matplotlib.pyplot as plt -import openmdao.api as om -import dymos as dm -import numpy as np -import sys - - -class CannonballProblem(om.Problem): - def __init__(self): - super().__init__() - self.model = CannonballGroup() - self.pre_mission = PreMissionGroup() - self.post_mission = PostMissionGroup() - self.traj = None - self.model.add_subsystem('pre_mission', self.pre_mission, - promotes=['*']) - self.model.add_subsystem('post_mission', self.post_mission) - - def add_trajectory(self, ke_max=1e2): - traj = dm.Trajectory() - transcription = dm.Radau(num_segments=5, order=3, compressed=True) - ascent = dm.Phase(ode_class=CannonballODE, transcription=transcription) - traj.add_phase('ascent', ascent) - - transcription = dm.GaussLobatto(num_segments=5, order=3, compressed=True) - descent = dm.Phase(ode_class=CannonballODE, transcription=transcription) - traj.add_phase('descent', descent) - - for phase in (ascent, descent): - is_ascent = phase.name == "ascent" - phase.set_time_options(fix_initial=True if is_ascent else False, - duration_bounds=(1, 100), duration_ref=100, units='s') - phase.set_state_options('r', fix_initial=is_ascent, fix_final=False) - phase.set_state_options('h', fix_initial=is_ascent, fix_final=not is_ascent) - phase.set_state_options('gam', fix_initial=False, fix_final=is_ascent) - phase.set_state_options('v', fix_initial=False, fix_final=False) - phase.add_parameter('S', units='m**2', static_target=True, val=0.005) - phase.add_parameter('m', units='kg', static_target=True, val=1.0) - phase.add_parameter('price', units='USD', static_target=True, val=10) - phase.add_parameter('CD', units=None, static_target=True, val=0.5) - - # descent.add_objective('r', loc='final', scaler=-1.0) # negative means to maximize - for param in ('CD', 'm', 'S', 'price'): - traj.add_parameter(param, static_target=True) - - # Link Phases (link time and all state variables) - traj.link_phases(phases=['ascent', 'descent'], vars=['*']) - # have to set muzzle energy here before setup for sim to run properly - ascent.add_boundary_constraint('ke', loc='initial', - upper=ke_max, lower=0, ref=100000) - self.traj = traj - self.model.add_subsystem('traj', traj) - self.phases = [ascent, descent] - - def setDefaults(self): - self.model.set_input_defaults('density', val=7.87, units='g/cm**3') - - def addDesVar(self): - self.model.add_design_var('radius', lower=0.01, upper=0.10, - ref0=0.01, ref=0.10, units='m') - - def connectPreTraj(self): - self.model.connect('mass', 'traj.parameters:m') - self.model.connect('S', 'traj.parameters:S') - self.model.connect('price', 'traj.parameters:price') - - def setInitialVals(self, super_problem=None, prefix=""): - ref = self - if super_problem is not None and prefix != "": - ref = super_problem - - ref.set_val(prefix+'radius', 0.05, units='m') - ref.set_val(prefix+'density', 7.87, units='g/cm**3') - - ref.set_val(prefix+"traj.parameters:CD", 0.5) - ref.set_val(prefix+"traj.ascent.t_initial", 0.0) - ref.set_val(prefix+"traj.ascent.t_duration", 10.0) - - # list is initial and final, based on phase info some are fixed others are not - ascent, descent = self.phases - ref.set_val(prefix+"traj.ascent.states:r", ascent.interp('r', [0, 100])) - ref.set_val(prefix+'traj.ascent.states:h', ascent.interp('h', [0, 100])) - ref.set_val(prefix+'traj.ascent.states:v', ascent.interp('v', [200, 150])) - ref.set_val(prefix+'traj.ascent.states:gam', - ascent.interp('gam', [25, 0]), units='deg') - - ref.set_val(prefix+'traj.descent.t_initial', 10.0) - ref.set_val(prefix+'traj.descent.t_duration', 10.0) - ref.set_val(prefix+'traj.descent.states:r', descent.interp('r', [100, 200])) - ref.set_val(prefix+'traj.descent.states:h', descent.interp('h', [100, 0])) - ref.set_val(prefix+'traj.descent.states:v', descent.interp('v', [150, 200])) - ref.set_val(prefix+'traj.descent.states:gam', - descent.interp('gam', [0, -45]), units='deg') - - -class CannonballGroup(om.Group): - def __init__(self): - super().__init__() - - -class PreMissionGroup(om.Group): - def __init__(self): - super().__init__() - self.sizingcomp = CannonballSizing() - self.add_subsystem('sizing_comp', self.sizingcomp, - promotes=['*']) - - -class PostMissionGroup(om.Group): - pass - - -class CannonballODE(om.ExplicitComponent): - def initialize(self): - self.options.declare('num_nodes', types=int) - - def setup(self): - nn = self.options['num_nodes'] - # static params - self.add_input('m', units='kg') - self.add_input('S', units='m**2') - self.add_input('CD', 0.5) - - # time varying inputs - self.add_input('h', units='m', shape=nn) - self.add_input('v', units='m/s', shape=nn) - self.add_input('gam', units='rad', shape=nn) - - # state rates - self.add_output('v_dot', shape=nn, units='m/s**2', - tags=['dymos.state_rate_source:v']) - self.add_output('gam_dot', shape=nn, units='rad/s', - tags=['dymos.state_rate_source:gam']) - self.add_output('h_dot', shape=nn, units='m/s', - tags=['dymos.state_rate_source:h']) - self.add_output('r_dot', shape=nn, units='m/s', - tags=['dymos.state_rate_source:r']) - self.add_output('ke', shape=nn, units='J') - - # Ask OpenMDAO to compute the partial derivatives using complex-step - # with a partial coloring algorithm for improved performance, and use - # a graph coloring algorithm to automatically detect the sparsity pattern. - self.declare_coloring(wrt='*', method='cs') - - alt_data = USatm1976Data.alt * om.unit_conversion('ft', 'm')[0] - rho_data = USatm1976Data.rho * om.unit_conversion('slug/ft**3', 'kg/m**3')[0] - self.rho_interp = interp1d(np.array(alt_data, dtype=complex), - np.array(rho_data, dtype=complex), - kind='linear') - - def compute(self, inputs, outputs): - - gam = inputs['gam'] - v = inputs['v'] - h = inputs['h'] - m = inputs['m'] - S = inputs['S'] - CD = inputs['CD'] - - GRAVITY = 9.80665 # m/s**2 - - # handle complex-step gracefully from the interpolant - if np.iscomplexobj(h): - rho = self.rho_interp(inputs['h']) - else: - rho = self.rho_interp(inputs['h']).real - - q = 0.5*rho*inputs['v']**2 - qS = q * S - D = qS * CD - cgam = np.cos(gam) - sgam = np.sin(gam) - outputs['v_dot'] = - D/m-GRAVITY*sgam - outputs['gam_dot'] = -(GRAVITY/v)*cgam - outputs['h_dot'] = v*sgam - outputs['r_dot'] = v*cgam - outputs['ke'] = 0.5*m*v**2 - - -class CannonballSizing(om.ExplicitComponent): - def setup(self): - self.add_input(name='radius', val=1.0, units='m') - self.add_input(name='density', val=7870., units='kg/m**3') - - self.add_output(name='mass', shape=(1,), units='kg') - self.add_output(name='S', shape=(1,), units='m**2') - self.add_output(name='price', shape=(1,), units='USD') - - self.declare_partials(of='mass', wrt='density') - self.declare_partials(of='mass', wrt='radius') - self.declare_partials(of='S', wrt='radius') - self.declare_partials(of='price', wrt='radius') - self.declare_partials(of='price', wrt='density') - - def compute(self, inputs, outputs): - radius = inputs['radius'] - density = inputs['density'] - outputs['mass'] = (4/3.) * density * np.pi * radius ** 3 - outputs['S'] = np.pi * radius ** 2 - outputs['price'] = (4/3.) * density * np.pi * radius ** 3 * 10 # $10 per kg - - def compute_partials(self, inputs, partials): - radius = inputs['radius'] - density = inputs['density'] - partials['mass', 'density'] = (4/3.) * np.pi * radius ** 3 - partials['mass', 'radius'] = 4. * density * np.pi * radius ** 2 - partials['S', 'radius'] = 2 * np.pi * radius - partials['price', 'density'] = (4/3.) * np.pi * radius ** 3 * 10 - partials['price', 'radius'] = 4. * density * np.pi * radius ** 2 * 10 - - -def runAvCannonball(kes=[4e3], weights=[1], makeN2=False): - # handling of multiple KEs - # if fewer weights present than KEs, use same weight - if len(kes) > len(weights): - weights = [1]*len(kes) - elif len(kes) < len(weights): - raise Exception("Cannot have more weights than cannons!") - num_trajs = len(kes) - - probs = [] - super_prob = om.Problem() - - # create sub problems and add them to super in a group - # group prevents spillage of promoted vars into super - prefix = "group" # prefix for each om.Group - for i, ke in enumerate(kes): - prob = CannonballProblem() - prob.add_trajectory(ke_max=ke) - prob.setDefaults() - prob.addDesVar() # doesn't seem to do anything - prob.connectPreTraj() - - super_prob.model.add_subsystem(prefix+f'_{i}', prob.model, - promotes_inputs=['radius', 'density']) - probs.append(prob) - - # create an execComp with a compound range function to maximize range - # for all cannons with a weighted function - ranges = [f"r{i}" for i in range(num_trajs)] # looks like: [r0, r1, ...] - # weighted_sum_str looks like: 1*r0+1*r1+... - weighted_sum_str = "+".join([f"{weight}*{r}" for r, weight in zip(ranges, weights)]) - super_prob.model.add_subsystem('compoundComp', om.ExecComp( - "compound_range=" + weighted_sum_str), - promotes=['compound_range', *ranges]) - - # controlling radius to affect mass/ballistic coeff - super_prob.model.add_design_var('radius', lower=0.01, upper=0.10, - ref0=0.01, ref=0.10, units='m') - - for i in range(num_trajs): - # connect end of trajectory range to compound range input - super_prob.model.connect( - prefix+f'_{i}.traj.descent.states:r', ranges[i], - src_indices=-1) - - super_prob.model.add_objective('compound_range', scaler=-1) # maximize range - - super_prob.driver = om.ScipyOptimizeDriver() - super_prob.driver.options['optimizer'] = 'SLSQP' - super_prob.driver.declare_coloring() - super_prob.model.linear_solver = om.DirectSolver() - super_prob.setup() - - for i, prob in enumerate(probs): - subprefix = prefix+f"_{i}." - prob.setInitialVals(super_prob, subprefix) - - if makeN2: - sys.path.append('../') - from createN2 import createN2 - createN2(__file__, super_prob) - - dm.run_problem(super_prob) - return super_prob, prefix, num_trajs, kes, weights - - -def printOutput(super_prob, prefix, num_trajs, kes, weights): - # formatted output - print("\n\n=================================================") - print( - f"Optimized {num_trajs} trajectories with weights: {', '.join(map(str,weights))}") - rad = super_prob.get_val('radius', units='cm')[0] - - mass0 = super_prob.get_val(prefix+'_0.mass', units='kg')[0] - price0 = super_prob.get_val(prefix+'_0.price', units='USD')[0] - area0 = super_prob.get_val(prefix+'_0.S', units='cm**2')[0] - - # mass, price, S are outputs from sizing. These should be common amongst all - # trajectories, however since they're outputs they cannot be promoted upto - # super problem without unique names. This loop checks their values with - # value of the first trajectory to ensure they are the same. - if num_trajs > 1: - for i in range(num_trajs-1): - mass = super_prob.get_val(prefix+f'_{i+1}.mass', units='kg')[0] - price = super_prob.get_val(prefix+f'_{i+1}.price', units='USD')[0] - area = super_prob.get_val(prefix+f'_{i+1}.S', units='cm**2')[0] - if mass != mass0 or price != price0 or area != area0: - raise Exception( - "Masses, Prices, and/or Areas are not equivalent between trajectories.") - - print("\nOptimal Cannonball Description:") - print( - f"\tRadius: {rad:.2f} cm, Mass: {mass0:.2f} kg, Price: ${price0:.2f}, Area: {area0:.2f} sqcm") - - print("\nOptimal Trajectory Descriptions:") - ranges = 0 - for i, ke in enumerate(kes): - angle = super_prob.get_val( - prefix+f'_{i}.traj.ascent.timeseries.gam', units='deg')[0, 0] - max_range = super_prob.get_val( - prefix+f'_{i}.traj.descent.timeseries.r')[-1, 0] - - print( - f"\tKE: {ke/1e3:.2f} KJ, Launch Angle: {angle:.2f} deg, Max Range: {max_range:.2f} m") - ranges += weights[i]*max_range - print(f"System range: {ranges}") - - -def plotOutput(super_prob, prefix, num_trajs, kes, weights, show=True): - if show: - _, ax = plt.subplots() - timevals = [] - hvals = [] - rvals = [] - for i in range(num_trajs): - tv = [] - hv = [] - rv = [] - for phase in ('ascent', 'descent'): - tv.append(super_prob.get_val( - prefix+f'_{i}.traj.{phase}.timeseries.time')) - hv.append(super_prob.get_val( - prefix+f'_{i}.traj.{phase}.timeseries.h')) - rv.append(super_prob.get_val( - prefix+f'_{i}.traj.{phase}.timeseries.r')) - - timevals.append(np.vstack(tv)) - hvals.append(np.vstack(hv)) - rvals.append(np.vstack(rv)) - if show: - ax.plot(rvals[-1], hvals[-1]) - - if show: - plt.grid() - plt.legend([f"Weights = {weight}" for weight in weights]) - plt.title(f"Cannonballs With KEs: {kes} J") - plt.show() - return timevals, rvals, hvals - - -def multiTestCase(makeN2=False): - testing_weights = [[2, 1.2], [1.2, 2], [1, 1]] - kes = [1e5, 6e5] - legendlst = [] - rs, hs = [], [] - for weighting in testing_weights: - super_prob, prefix, num_trajs, kes, weights = runAvCannonball( - kes=kes, weights=weighting, makeN2=makeN2) - printOutput(super_prob, prefix, num_trajs, kes, weights) - tvals, rvals, hvals = plotOutput( - super_prob, prefix, num_trajs, kes, weights, show=False) - - for r, h, weight, ke in zip(rvals, hvals, weighting, kes): - rs.append(r) - hs.append(h) - legendlst.append(f"KE: {ke/1e3} kJ, Weight: {weight} of {weighting}") - - _, ax = plt.subplots() - colors = ['r--', 'r-', 'b--', 'b-', 'g--', 'g-'] # same color for each cannonball - for r, h, col in zip(rs, hs, colors): - ax.plot(r, h, col) - plt.grid() - plt.legend(legendlst, loc='upper left') - titlestr = ", ".join([str(ke/1e3) for ke in kes]) - plt.title(f"Cannonballs With KEs: {titlestr} kJ") - plt.show() - - -if __name__ == '__main__': - # if run as python avcannonball.py n2, it will create an N2 - makeN2 = False - singlerun = True - if len(sys.argv) > 1: - if "n2" in sys.argv: - makeN2 = True - if "multi" in sys.argv: - # runs multiple weightings to see what impact system optimization makes - multiTestCase(makeN2) - singlerun = False - - if singlerun: - # singular weighting run - super_prob, prefix, num_trajs, kes, weights = runAvCannonball( - kes=[4e5, 6e5], weights=[2, 1.5], makeN2=makeN2) - printOutput(super_prob, prefix, num_trajs, kes, weights) - plotOutput(super_prob, prefix, num_trajs, kes, weights) - - -""" -Findings: -- importing prob.model solves the issue of connecting traj to pre/post mission (at least in cannonball) -- initial values can be set with the internal function as long as set_val gets called on the super problem instance - and as such the variable name passed in contains the unique reference - """ diff --git a/cannonball_models/multi_cannonball_copyparts.py b/cannonball_models/multi_cannonball_copyparts.py deleted file mode 100644 index 327b983d2..000000000 --- a/cannonball_models/multi_cannonball_copyparts.py +++ /dev/null @@ -1,484 +0,0 @@ -# Cannonball Multi Mission Example with Aviary-esque setup -# Each mission is defined as a "CannonballProblem", akin to AviaryProblem -from dymos.models.atmosphere.atmos_1976 import USatm1976Data -from scipy.interpolate import interp1d -import matplotlib.pyplot as plt -import openmdao.api as om -import dymos as dm -import numpy as np -import sys - - -class CannonballProblem(om.Problem): - def __init__(self): - super().__init__() - self.model = CannonballGroup() - self.pre_mission = PreMissionGroup() - self.post_mission = PostMissionGroup() - self.traj = None - self.model.add_subsystem('pre_mission', self.pre_mission, - promotes=['*']) - self.model.add_subsystem('post_mission', self.post_mission) - - def add_trajectory(self, ke_max=1e2): - traj = dm.Trajectory() - transcription = dm.Radau(num_segments=5, order=3, compressed=True) - ascent = dm.Phase(ode_class=CannonballODE, transcription=transcription) - traj.add_phase('ascent', ascent) - - transcription = dm.GaussLobatto(num_segments=5, order=3, compressed=True) - descent = dm.Phase(ode_class=CannonballODE, transcription=transcription) - traj.add_phase('descent', descent) - - for phase in (ascent, descent): - is_ascent = phase.name == "ascent" - phase.set_time_options(fix_initial=True if is_ascent else False, - duration_bounds=(1, 100), duration_ref=100, units='s') - phase.set_state_options('r', fix_initial=is_ascent, fix_final=False) - phase.set_state_options('h', fix_initial=is_ascent, fix_final=not is_ascent) - phase.set_state_options('gam', fix_initial=False, fix_final=is_ascent) - phase.set_state_options('v', fix_initial=False, fix_final=False) - phase.add_parameter('S', units='m**2', static_target=True, val=0.005) - phase.add_parameter('m', units='kg', static_target=True, val=1.0) - phase.add_parameter('price', units='USD', static_target=True, val=10) - phase.add_parameter('CD', units=None, static_target=True, val=0.5) - - # descent.add_objective('r', loc='final', scaler=-1.0) # negative means to maximize - for param in ('CD', 'm', 'S', 'price'): - traj.add_parameter(param, static_target=True) - - # Link Phases (link time and all state variables) - traj.link_phases(phases=['ascent', 'descent'], vars=['*']) - # have to set muzzle energy here before setup for sim to run properly - ascent.add_boundary_constraint('ke', loc='initial', - upper=ke_max, lower=0, ref=100000) - self.traj = traj - self.model.add_subsystem('traj', traj) - self.phases = [ascent, descent] - - def setDefaults(self): - self.model.set_input_defaults('density', val=7.87, units='g/cm**3') - - def addDesVar(self): - self.model.add_design_var('radius', lower=0.01, upper=0.10, - ref0=0.01, ref=0.10, units='m') - - def connectPreTraj(self): - self.model.connect('mass', 'traj.parameters:m') - self.model.connect('S', 'traj.parameters:S') - self.model.connect('price', 'traj.parameters:price') - - def setInitialVals(self): - self.set_val('radius', 0.05, units='m') - self.set_val('density', 7.87, units='g/cm**3') - - self.set_val("traj.parameters:CD", 0.5) - - self.set_val("traj.ascent.t_initial", 0.0) - self.set_val("traj.ascent.t_duration", 10.0) - # list is initial and final, based on phase info some are fixed others are not - ascent, descent = self.phases - self.set_val("traj.ascent.states:r", ascent.interp('r', [0, 100])) - self.set_val('traj.ascent.states:h', ascent.interp('h', [0, 100])) - self.set_val('traj.ascent.states:v', ascent.interp('v', [200, 150])) - self.set_val('traj.ascent.states:gam', - ascent.interp('gam', [25, 0]), units='deg') - - self.set_val('traj.descent.t_initial', 10.0) - self.set_val('traj.descent.t_duration', 10.0) - - self.set_val('traj.descent.states:r', descent.interp('r', [100, 200])) - self.set_val('traj.descent.states:h', descent.interp('h', [100, 0])) - self.set_val('traj.descent.states:v', descent.interp('v', [150, 200])) - self.set_val('traj.descent.states:gam', - descent.interp('gam', [0, -45]), units='deg') - - -class CannonballGroup(om.Group): - def __init__(self): - super().__init__() - - -class PreMissionGroup(om.Group): - def __init__(self): - super().__init__() - self.sizingcomp = CannonballSizing() - self.add_subsystem('sizing_comp', self.sizingcomp, - promotes=['*']) - - -class PostMissionGroup(om.Group): - pass - - -class CannonballODE(om.ExplicitComponent): - def initialize(self): - self.options.declare('num_nodes', types=int) - - def setup(self): - nn = self.options['num_nodes'] - # static params - self.add_input('m', units='kg') - self.add_input('S', units='m**2') - self.add_input('CD', 0.5) - - # time varying inputs - self.add_input('h', units='m', shape=nn) - self.add_input('v', units='m/s', shape=nn) - self.add_input('gam', units='rad', shape=nn) - - # state rates - self.add_output('v_dot', shape=nn, units='m/s**2', - tags=['dymos.state_rate_source:v']) - self.add_output('gam_dot', shape=nn, units='rad/s', - tags=['dymos.state_rate_source:gam']) - self.add_output('h_dot', shape=nn, units='m/s', - tags=['dymos.state_rate_source:h']) - self.add_output('r_dot', shape=nn, units='m/s', - tags=['dymos.state_rate_source:r']) - self.add_output('ke', shape=nn, units='J') - - # Ask OpenMDAO to compute the partial derivatives using complex-step - # with a partial coloring algorithm for improved performance, and use - # a graph coloring algorithm to automatically detect the sparsity pattern. - self.declare_coloring(wrt='*', method='cs') - - alt_data = USatm1976Data.alt * om.unit_conversion('ft', 'm')[0] - rho_data = USatm1976Data.rho * om.unit_conversion('slug/ft**3', 'kg/m**3')[0] - self.rho_interp = interp1d(np.array(alt_data, dtype=complex), - np.array(rho_data, dtype=complex), - kind='linear') - - def compute(self, inputs, outputs): - - gam = inputs['gam'] - v = inputs['v'] - h = inputs['h'] - m = inputs['m'] - S = inputs['S'] - CD = inputs['CD'] - - GRAVITY = 9.80665 # m/s**2 - - # handle complex-step gracefully from the interpolant - if np.iscomplexobj(h): - rho = self.rho_interp(inputs['h']) - else: - rho = self.rho_interp(inputs['h']).real - - q = 0.5*rho*inputs['v']**2 - qS = q * S - D = qS * CD - cgam = np.cos(gam) - sgam = np.sin(gam) - outputs['v_dot'] = - D/m-GRAVITY*sgam - outputs['gam_dot'] = -(GRAVITY/v)*cgam - outputs['h_dot'] = v*sgam - outputs['r_dot'] = v*cgam - outputs['ke'] = 0.5*m*v**2 - - -class CannonballSizing(om.ExplicitComponent): - def setup(self): - self.add_input(name='radius', val=1.0, units='m') - self.add_input(name='density', val=7870., units='kg/m**3') - - self.add_output(name='mass', shape=(1,), units='kg') - self.add_output(name='S', shape=(1,), units='m**2') - self.add_output(name='price', shape=(1,), units='USD') - - self.declare_partials(of='mass', wrt='density') - self.declare_partials(of='mass', wrt='radius') - self.declare_partials(of='S', wrt='radius') - self.declare_partials(of='price', wrt='radius') - self.declare_partials(of='price', wrt='density') - - def compute(self, inputs, outputs): - radius = inputs['radius'] - density = inputs['density'] - outputs['mass'] = (4/3.) * density * np.pi * radius ** 3 - outputs['S'] = np.pi * radius ** 2 - outputs['price'] = (4/3.) * density * np.pi * radius ** 3 * 10 # $10 per kg - - def compute_partials(self, inputs, partials): - radius = inputs['radius'] - density = inputs['density'] - partials['mass', 'density'] = (4/3.) * np.pi * radius ** 3 - partials['mass', 'radius'] = 4. * density * np.pi * radius ** 2 - partials['S', 'radius'] = 2 * np.pi * radius - partials['price', 'density'] = (4/3.) * np.pi * radius ** 3 * 10 - partials['price', 'radius'] = 4. * density * np.pi * radius ** 2 * 10 - - -def runAvCannonball(kes=[4e3], weights=[1], makeN2=False): - # handling of multiple KEs - # if fewer weights present than KEs, use same weight - if len(kes) > len(weights): - weights = [1]*len(kes) - elif len(kes) < len(weights): - raise Exception("Cannot have more weights than cannons!") - num_trajs = len(kes) - - probs = [] - super_prob = om.Problem() - - # create sub problems and add them to super in a group - # group prevents spillage of promoted vars into super - prefix = "group" # prefix for each om.Group - for i, ke in enumerate(kes): - prob = CannonballProblem() - prob.add_trajectory(ke_max=ke) - prob.setDefaults() - prob.addDesVar() # doesn't seem to do anything - prob.connectPreTraj() # doesn't seem to actually do anything - - group = om.Group() - group.add_subsystem('pre_mission', prob.pre_mission) - group.add_subsystem('traj', prob.traj) - group.add_subsystem('post_mission', prob.post_mission) - # promoting radius and density keeps it constant for all missions - super_prob.model.add_subsystem(prefix+f'_{i}', group, - promotes_inputs=['radius', 'density']) - probs.append(prob) - - # create an execComp with a compound range function to maximize range - # for all cannons with a weighted function - ranges = [f"r{i}" for i in range(num_trajs)] # looks like: [r0, r1, ...] - # weighted_sum_str looks like: 1*r0+1*r1+... - weighted_sum_str = "+".join([f"{weight}*{r}" for r, weight in zip(ranges, weights)]) - super_prob.model.add_subsystem('compoundComp', om.ExecComp( - "compound_range=" + weighted_sum_str), - promotes=['compound_range', *ranges]) - - # controlling radius to affect mass/ballistic coeff - super_prob.model.add_design_var('radius', lower=0.01, upper=0.10, - ref0=0.01, ref=0.10, units='m') - - for i in range(num_trajs): - # connect end of trajectory range to compound range input - super_prob.model.connect( - prefix+f'_{i}.traj.descent.states:r', ranges[i], - src_indices=-1) - - # connect pre-mission parameters to trajectory counter parts - # this connection would happen within each problem's internal function, - # but since we're extracting the components into a larger problem, - # these connections have to be made at the super problem level - super_prob.model.connect( - prefix+f'_{i}.mass', prefix+f'_{i}.traj.parameters:m') - super_prob.model.connect( - prefix+f'_{i}.S', prefix+f'_{i}.traj.parameters:S') - super_prob.model.connect( - prefix+f'_{i}.price', prefix+f'_{i}.traj.parameters:price') - - super_prob.model.add_objective('compound_range', scaler=-1) # maximize range - - super_prob.driver = om.ScipyOptimizeDriver() - super_prob.driver.options['optimizer'] = 'SLSQP' - super_prob.driver.declare_coloring() - super_prob.model.linear_solver = om.DirectSolver() - super_prob.setup() - - for i, prob in enumerate(probs): - reference = prefix+f"_{i}" - super_prob.set_val(reference+'.radius', 0.05, units='m') - super_prob.set_val(reference+'.density', 7.87, units='g/cm**3') - - super_prob.set_val(reference+".traj.parameters:CD", 0.5) - - super_prob.set_val(reference+".traj.ascent.t_initial", 0.0) - super_prob.set_val(reference+".traj.ascent.t_duration", 10.0) - # list is initial and final, based on phase info some are fixed others are not - ascent, descent = prob.phases - super_prob.set_val(reference+".traj.ascent.states:r", - ascent.interp('r', [0, 100])) - super_prob.set_val(reference+'.traj.ascent.states:h', - ascent.interp('h', [0, 100])) - super_prob.set_val(reference+'.traj.ascent.states:v', - ascent.interp('v', [200, 150])) - super_prob.set_val(reference+'.traj.ascent.states:gam', - ascent.interp('gam', [25, 0]), units='deg') - - super_prob.set_val(reference+'.traj.descent.t_initial', 10.0) - super_prob.set_val(reference+'.traj.descent.t_duration', 10.0) - - super_prob.set_val(reference+'.traj.descent.states:r', - descent.interp('r', [100, 200])) - super_prob.set_val(reference+'.traj.descent.states:h', - descent.interp('h', [100, 0])) - super_prob.set_val(reference+'.traj.descent.states:v', - descent.interp('v', [150, 200])) - super_prob.set_val(reference+'.traj.descent.states:gam', - descent.interp('gam', [0, -45]), units='deg') - - if makeN2: - sys.path.append('../') - from createN2 import createN2 - createN2(__file__, super_prob) - - dm.run_problem(super_prob) - return super_prob, prefix, num_trajs, kes, weights - - -def printOutput(super_prob, prefix, num_trajs, kes, weights): - # formatted output - print("\n\n=================================================") - print( - f"Optimized {num_trajs} trajectories with weights: {', '.join(map(str,weights))}") - rad = super_prob.get_val('radius', units='cm')[0] - - mass0 = super_prob.get_val(prefix+'_0.mass', units='kg')[0] - price0 = super_prob.get_val(prefix+'_0.price', units='USD')[0] - area0 = super_prob.get_val(prefix+'_0.S', units='cm**2')[0] - - # mass, price, S are outputs from sizing. These should be common amongst all - # trajectories, however since they're outputs they cannot be promoted upto - # super problem without unique names. This loop checks their values with - # value of the first trajectory to ensure they are the same. - if num_trajs > 1: - for i in range(num_trajs-1): - mass = super_prob.get_val(prefix+f'_{i+1}.mass', units='kg')[0] - price = super_prob.get_val(prefix+f'_{i+1}.price', units='USD')[0] - area = super_prob.get_val(prefix+f'_{i+1}.S', units='cm**2')[0] - if mass != mass0 or price != price0 or area != area0: - raise Exception( - "Masses, Prices, and/or Areas are not equivalent between trajectories.") - - print("\nOptimal Cannonball Description:") - print( - f"\tRadius: {rad:.2f} cm, Mass: {mass0:.2f} kg, Price: ${price0:.2f}, Area: {area0:.2f} sqcm") - - print("\nOptimal Trajectory Descriptions:") - ranges = 0 - for i, ke in enumerate(kes): - angle = super_prob.get_val( - prefix+f'_{i}.traj.ascent.timeseries.gam', units='deg')[0, 0] - max_range = super_prob.get_val( - prefix+f'_{i}.traj.descent.timeseries.r')[-1, 0] - - print( - f"\tKE: {ke/1e3:.2f} KJ, Launch Angle: {angle:.2f} deg, Max Range: {max_range:.2f} m") - ranges += weights[i]*max_range - print(f"System range: {ranges}") - - -def plotOutput(super_prob, prefix, num_trajs, kes, weights, show=True): - if show: - _, ax = plt.subplots() - timevals = [] - hvals = [] - rvals = [] - for i in range(num_trajs): - tv = [] - hv = [] - rv = [] - for phase in ('ascent', 'descent'): - tv.append(super_prob.get_val( - prefix+f'_{i}.traj.{phase}.timeseries.time')) - hv.append(super_prob.get_val( - prefix+f'_{i}.traj.{phase}.timeseries.h')) - rv.append(super_prob.get_val( - prefix+f'_{i}.traj.{phase}.timeseries.r')) - - timevals.append(np.vstack(tv)) - hvals.append(np.vstack(hv)) - rvals.append(np.vstack(rv)) - if show: - ax.plot(rvals[-1], hvals[-1]) - - if show: - plt.grid() - plt.legend([f"Weights = {weight}" for weight in weights]) - plt.title(f"Cannonballs With KEs: {kes} J") - plt.show() - return timevals, rvals, hvals - - -def multiTestCase(makeN2=False): - testing_weights = [[2, 1.2], [1.2, 2], [1, 1]] - kes = [1e5, 6e5] - legendlst = [] - rs, hs = [], [] - for weighting in testing_weights: - super_prob, prefix, num_trajs, kes, weights = runAvCannonball( - kes=kes, weights=weighting, makeN2=makeN2) - printOutput(super_prob, prefix, num_trajs, kes, weights) - tvals, rvals, hvals = plotOutput( - super_prob, prefix, num_trajs, kes, weights, show=False) - - for r, h, weight, ke in zip(rvals, hvals, weighting, kes): - rs.append(r) - hs.append(h) - legendlst.append(f"KE: {ke/1e3} kJ, Weight: {weight} of {weighting}") - - _, ax = plt.subplots() - colors = ['r--', 'r-', 'b--', 'b-', 'g--', 'g-'] # same color for each cannonball - for r, h, col in zip(rs, hs, colors): - ax.plot(r, h, col) - plt.grid() - plt.legend(legendlst, loc='upper left') - titlestr = ", ".join([str(ke/1e3) for ke in kes]) - plt.title(f"Cannonballs With KEs: {titlestr} kJ") - plt.show() - - -if __name__ == '__main__': - # if run as python multi_cannonball_copyparts.py n2, it will create an N2 - makeN2 = False - singlerun = True - if len(sys.argv) > 1: - if "n2" in sys.argv: - makeN2 = True - if "multi" in sys.argv: - # runs multiple weightings to see what impact system optimization makes - multiTestCase(makeN2) - singlerun = False - - if singlerun: - # singular weighting run - super_prob, prefix, num_trajs, kes, weights = runAvCannonball( - kes=[4e5, 6e5], weights=[2, 1.5], makeN2=makeN2) - printOutput(super_prob, prefix, num_trajs, kes, weights) - plotOutput(super_prob, prefix, num_trajs, kes, weights) - - -""" -Findings: -- connections between trajectory parameters and pre-mission parameters (and post-mission for aviary) - have to be made at super problem level, running the cannonballproblem method to form those connections - has seemingly no effect, causing divide by zero errors b/c the trajectory value is not set - -- design var has to be set in super problem, cannonballproblem design var is not manipulated by optimizer, - giving a result with the default value for ball radius - -- initial values have to be set at super problem level, running cannonballproblem's initial value function - throws error that setval cannot run before setup (even though superproblem setup was run). - -What works: -- copying instances of pre, traj, and post mission subsystems and adding to a super problem -- internal linkages between trajectory phases works without super problem references -- compound objective between multiple trajectories works -- connections between 2 problems to maintain same physical size of cannonball (i.e. airplane) -- optimization runs, gives sensible results - -To apply to Aviary: -- link_phases (includes connections to post/pre and traj) -- add_design_vars - sizing components, subsystem level variables - (aviary currently adds aero, prop des vars along with any external subsystem) -- set_initial_guesses - -Next setps: -- multi_mission specific add des var that adds them at super prob level - - aviary's design var can still be run at the aviaryProblem level it just won't have any effect - -- multi_mission link phases that does post/pre to traj connection - - aviary's link phases can still be run it just won't create trajectory to pre mission var connections - - be careful with connections vs. promotions - -- initial guesses, what's the best solution? - - possible ideas: - - use aviary's existing functions to create initial values, but use set val outside on super prob - - would require minimal mods to aviary to not run set val when a flag is passed - - write a fully seperate initial guesses function - - would be problematic to maintain with changes/new additions - """ diff --git a/easy_phase_info_inter.py b/easy_phase_info_inter.py deleted file mode 100644 index 6589101a8..000000000 --- a/easy_phase_info_inter.py +++ /dev/null @@ -1,83 +0,0 @@ -phase_info = { - "pre_mission": {"include_takeoff": False, "optimize_mass": True}, - "climb_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.3, "unitless"), - "final_mach": (0.7, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.72), "unitless"), - "initial_altitude": (0.0, "ft"), - "final_altitude": (24500.0, "ft"), - "altitude_bounds": ((0.0, 25000.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": True, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((0.0, 0.0), "min"), - "duration_bounds": ((35.0, 105.0), "min"), - }, - "initial_guesses": {"time": ([0.0, 70.0], "min")}, - }, - "climb_2": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.7, "unitless"), - "final_mach": (0.7, "unitless"), - "mach_bounds": ((0.6799999999999999, 0.72), "unitless"), - "initial_altitude": (24500.0, "ft"), - "final_altitude": (25000.0, "ft"), - "altitude_bounds": ((24000.0, 25500.0), "ft"), - "throttle_enforcement": "boundary_constraint", - "fix_initial": False, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((35.0, 105.0), "min"), - "duration_bounds": ((245.0, 735.0), "min"), - }, - "initial_guesses": {"time": ([70.0, 490.0], "min")}, - }, - "descent_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.7, "unitless"), - "final_mach": (0.3, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.72), "unitless"), - "initial_altitude": (25000.0, "ft"), - "final_altitude": (0.0, "ft"), - "altitude_bounds": ((0.0, 25500.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": False, - "constrain_final": True, - "fix_duration": False, - "initial_bounds": ((280.0, 840.0), "min"), - "duration_bounds": ((15.0, 45.0), "min"), - }, - "initial_guesses": {"time": ([560.0, 30.0], "min")}, - }, - "post_mission": { - "include_landing": False, - "constrain_range": True, - "target_range": (4367.14, "nmi"), - }, -} diff --git a/easy_phase_info_max.py b/easy_phase_info_max.py deleted file mode 100644 index 1f7df7f8e..000000000 --- a/easy_phase_info_max.py +++ /dev/null @@ -1,83 +0,0 @@ -phase_info = { - "pre_mission": {"include_takeoff": False, "optimize_mass": True}, - "climb_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.3, "unitless"), - "final_mach": (0.7, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.72), "unitless"), - "initial_altitude": (0.0, "ft"), - "final_altitude": (24500.0, "ft"), - "altitude_bounds": ((0.0, 25000.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": True, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((0.0, 0.0), "min"), - "duration_bounds": ((35.0, 105.0), "min"), - }, - "initial_guesses": {"time": ([0.0, 70.0], "min")}, - }, - "climb_2": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.7, "unitless"), - "final_mach": (0.7, "unitless"), - "mach_bounds": ((0.6799999999999999, 0.72), "unitless"), - "initial_altitude": (24500.0, "ft"), - "final_altitude": (25000.0, "ft"), - "altitude_bounds": ((24000.0, 25500.0), "ft"), - "throttle_enforcement": "boundary_constraint", - "fix_initial": False, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((35.0, 105.0), "min"), - "duration_bounds": ((95.0, 285.0), "min"), - }, - "initial_guesses": {"time": ([70.0, 190.0], "min")}, - }, - "descent_1": { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "use_polynomial_control": True, - "num_segments": 3, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.7, "unitless"), - "final_mach": (0.3, "unitless"), - "mach_bounds": ((0.27999999999999997, 0.72), "unitless"), - "initial_altitude": (25000.0, "ft"), - "final_altitude": (0.0, "ft"), - "altitude_bounds": ((0.0, 25500.0), "ft"), - "throttle_enforcement": "path_constraint", - "fix_initial": False, - "constrain_final": True, - "fix_duration": False, - "initial_bounds": ((130.0, 390.0), "min"), - "duration_bounds": ((10.0, 30.0), "min"), - }, - "initial_guesses": {"time": ([260.0, 20.0], "min")}, - }, - "post_mission": { - "include_landing": False, - "constrain_range": True, - "target_range": (1977.99, "nmi"), - }, -} diff --git a/min_time_climb_models/min_time_climb.py b/min_time_climb_models/min_time_climb.py deleted file mode 100644 index b4b9dcd67..000000000 --- a/min_time_climb_models/min_time_climb.py +++ /dev/null @@ -1,301 +0,0 @@ -import openmdao.api as om -import dymos as dm -from dymos.examples.min_time_climb.min_time_climb_ode import MinTimeClimbODE -from plot_helper import make_min_time_climb_plot -import matplotlib.pyplot as plt -import numpy as np -import sys - - -class MinTimeClimbProblem(om.Problem): - def __init__( - self, target_height=20e3, - modelinfo={'m_initial': 16e3, 'S': 49.24, 'v_initial': 150, 'h_initial': 10, - 'mach_final': 1.0}): - super().__init__() - defaults = {'m_initial': 16e3, 'S': 49.24, 'v_initial': 150, 'h_initial': 10, - 'mach_final': 1.0} - for key in defaults.keys(): - if key not in modelinfo.keys(): - modelinfo[key] = defaults[key] - - self.model = om.Group() - self.target_height = target_height - self.modelinfo = modelinfo - - def setOptimizer(self, driver='scipy', optimizer='SLSQP'): - self.driver = om.pyOptSparseDriver() if driver == "pyoptsparse" else om.ScipyOptimizeDriver() - self.driver.options['optimizer'] = optimizer - self.driver.declare_coloring() - if optimizer == 'SNOPT': - self.driver.opt_settings['Major iterations limit'] = 1000 - self.driver.opt_settings['iSumm'] = 6 - self.driver.opt_settings['Major feasibility tolerance'] = 1.0E-6 - self.driver.opt_settings['Major optimality tolerance'] = 1.0E-6 - self.driver.opt_settings['Function precision'] = 1.0E-12 - self.driver.opt_settings['Linesearch tolerance'] = 0.1 - self.driver.opt_settings['Major step limit'] = 0.5 - elif optimizer == 'IPOPT': - self.driver.opt_settings['tol'] = 1.0E-5 - self.driver.opt_settings['print_level'] = 0 - self.driver.opt_settings['mu_strategy'] = 'monotone' - self.driver.opt_settings['bound_mult_init_method'] = 'mu-based' - self.driver.opt_settings['mu_init'] = 0.01 - - self.model.linear_solver = om.DirectSolver() - - def addTrajectory(self, num_seg=15, transcription='gauss-lobatto', - transcription_order=3, optWing=False): - t = {'gauss-lobatto': dm.GaussLobatto( - num_segments=num_seg, order=transcription_order), - 'radau-ps': dm.Radau(num_segments=num_seg, order=transcription_order)} - - traj = dm.Trajectory() - phase = dm.Phase(ode_class=MinTimeClimbODE, transcription=t[transcription]) - traj.add_phase('phase0', phase) - - height = self.target_height - time_name = 'time' - add_rate = False - phase.set_time_options(fix_initial=True, duration_bounds=(50, 600), - duration_ref=100.0, name=time_name) - - phase.add_state('r', fix_initial=True, lower=0, upper=1.0E6, - ref=1.0E3, defect_ref=1.0E3, units='m', - rate_source='flight_dynamics.r_dot') - - phase.add_state('h', fix_initial=True, lower=0, upper=height, - ref=height, defect_ref=height, units='m', - rate_source='flight_dynamics.h_dot', targets=['h']) - - phase.add_state('v', fix_initial=True, lower=10.0, - ref=1.0E2, defect_ref=1.0E2, units='m/s', - rate_source='flight_dynamics.v_dot', targets=['v']) - - phase.add_state('gam', fix_initial=True, lower=-1.5, upper=1.5, - ref=1.0, defect_ref=1.0, units='rad', - rate_source='flight_dynamics.gam_dot', targets=['gam']) - - phase.add_state('m', fix_initial=True, lower=10.0, upper=1.0E5, - ref=10_000, defect_ref=10_000, units='kg', - rate_source='prop.m_dot', targets=['m']) - - phase.add_control('alpha', units='deg', lower=-8.0, upper=8.0, scaler=1.0, - rate_continuity=True, rate_continuity_scaler=100.0, - rate2_continuity=False, targets=['alpha']) - - phase.add_parameter('S', val=self.modelinfo['S'], units='m**2', - opt=optWing, targets=['S']) - phase.add_parameter('Isp', val=1600.0, units='s', opt=False, targets=['Isp']) - phase.add_parameter('throttle', val=1.0, opt=False, targets=['throttle']) - - phase.add_boundary_constraint( - 'h', loc='final', equals=height) # , scaler=1.0E-3) - phase.add_boundary_constraint( - 'aero.mach', loc='final', equals=self.modelinfo['mach_final']) - phase.add_boundary_constraint('gam', loc='final', equals=0.0) - - phase.add_path_constraint(name='h', lower=100.0, upper=height, ref=height) - phase.add_path_constraint(name='aero.mach', lower=0.1, upper=1.8) - # phase.add_path_constraint(name='gam', lower=-23, upper=23, units='deg') - - # Unnecessary but included to test capability - phase.add_path_constraint(name='alpha', lower=-8, upper=8) - phase.add_path_constraint(name=f'{time_name}', lower=0, upper=600) - phase.add_path_constraint(name=f'{time_name}_phase', lower=0, upper=600) - - # test mixing wildcard ODE variable expansion and unit overrides - phase.add_timeseries_output(['aero.*', 'prop.thrust', 'prop.m_dot'], - units={'aero.f_lift': 'lbf', 'prop.thrust': 'lbf'}) - - # test adding rate as timeseries output - if add_rate: - phase.add_timeseries_rate_output('aero.mach') - - self.phase = phase - self.model.add_subsystem('traj', traj, promotes=['*']) - - def setInitialConditions(self, super_prob=None, prefix=""): - ref = self - if super_prob is not None and prefix != "": - ref = super_prob - phase = self.phase - ref.set_val(prefix+'traj.phase0.t_initial', 0.0) - ref.set_val(prefix+'traj.phase0.t_duration', 350.0) - - ref.set_val(prefix+'traj.phase0.states:r', phase.interp('r', [0.0, 100e3])) - ref.set_val(prefix+'traj.phase0.states:h', phase.interp( - 'h', [self.modelinfo['h_initial'], self.target_height])) - ref.set_val(prefix+'traj.phase0.states:v', - phase.interp('v', [self.modelinfo['v_initial'], 280])) - ref.set_val(prefix+'traj.phase0.states:gam', phase.interp('gam', [0.0, 0.0])) - ref.set_val(prefix+'traj.phase0.states:m', - phase.interp('m', [self.modelinfo['m_initial'], 16e3])) - ref.set_val(prefix+'traj.phase0.controls:alpha', - phase.interp('alpha', [0.0, 0.0])) - - def addObjective(self): - # Minimize time at the end of the phase - self.phase.add_objective('time', loc='final', ref=1.0) - - -def checkDeviation(filenum=0): - """Function to run min time climb problem multiple times for the same height and report any deviation in results. - Made to check for random results in outputs, fixed 7/31, seems to be caused by transcription order being 5 not 3""" - heights = [10e3]*2 - times_to_climb = [] - timeseries_pts = {'h': [], 'r': [], 'thrust': [], 'v': []} - prefix = 'traj.phase0.timeseries.' - - for height in heights: - p = MinTimeClimbProblem(target_height=height) - p.addTrajectory() - p.addObjective() - p.setOptimizer(driver='pyoptsparse') - p.setup() - p.setInitialConditions() - dm.run_problem(p, simulate=True) - sol = om.CaseReader('dymos_solution.db').get_case('final') - sim = om.CaseReader('dymos_simulation.db').get_case('final') - times_to_climb.append(p.get_val('traj.phase0.timeseries.time', - units='s')[-1][0]) - for var, varlst in timeseries_pts.items(): - varlst.append(sol.get_val(prefix+var)) - - print("\n\n=======================================") - with open(f'checkdiff_{filenum}.txt', 'w') as fp: - fp.write(f'time to climb: {times_to_climb[0]: .4f}\n\n') - fp.write(str(timeseries_pts)) - - for key in timeseries_pts.keys(): - timeseries_pts[key] = np.array( - timeseries_pts[key][1:]) - timeseries_pts[key][0] - print(f"Max difference in {key}: {np.max(timeseries_pts[key]):.2f}") - - print(f"Time to climb: {times_to_climb[0]:.2f}") - print(f"Standard deviation of time to climb in {len(heights)}" + - f" cases: {np.std(times_to_climb):.2f}") - for key in timeseries_pts.keys(): - print(f"Standard deviation of {key} in {len(heights)} cases:" + - f" {np.std(timeseries_pts[key]):.2f}") - - -def multiHeightTest(printResults=True): - heights = [6e3, 18e3] - times = [] - areas = [] - outfiles = {'sol': [], 'sim': []} - - for j, height in enumerate(heights): - solfile = f'single_solution_{j}.db' - simfile = f'single_simulation_{j}.db' - outfiles['sim'].append(simfile) - outfiles['sol'].append(solfile) - p = MinTimeClimbProblem(target_height=height) - p.addTrajectory(optWing=True) - p.addObjective() - p.setOptimizer(driver='pyoptsparse') - p.setup() - p.setInitialConditions() - dm.run_problem( - p, simulate=True, solution_record_file=solfile, - simulation_record_file=simfile) - areas.append(p.get_val('phase0.parameters:S', units='m**2')[0]) - times.append(p.get_val('phase0.timeseries.time', units='s')[-1][0]) - - if printResults: - print("\n\n=======================================") - for time, area, height in zip(times, areas, heights): - print(f"Time to climb {height/1e3} km: " + - f"{time:.2f}" + - f" s with wing area: {area} sqm") - - make_min_time_climb_plot( - solfile=outfiles['sol'], - simfile=outfiles['sim'], - omitpromote='traj') - - return outfiles - - -if __name__ == '__main__': - if 'filenum' in sys.argv: - checkDeviation(filenum=sys.argv[1].split('filenum=')[1]) - else: - multiHeightTest() - - -""" -var names - 'traj.phase0.controls:alpha' - 'traj.phase0.t_initial' - 'traj.phase0.t_duration' - 'traj.phase0.parameters:S' - 'traj.phase0.parameters:Isp' - 'traj.phase0.parameters:throttle' - 'traj.phase0.collocation_constraint.defects:gam' - 'traj.phase0.control_rates:alpha_rate' - 'traj.phase0.control_rates:alpha_rate2' - 'traj.phase0.control_values:alpha' - 'traj.phase0.states:gam' - 'traj.phase0.states:h' - 'traj.phase0.states:m' - 'traj.phase0.states:r' - 'traj.phase0.states:v' - 'traj.phase0.interleave_comp.all_values:CD' - 'traj.phase0.parameter_vals:Isp' - 'traj.phase0.parameter_vals:S' - 'traj.phase0.parameter_vals:throttle' - 'traj.phase0.t_duration_val' - 'traj.phase0.t_initial_val' - 'traj.phase0.rhs_col.aero.CD' - 'traj.phase0.rhs_disc.aero.CL' - 'traj.phase0.rhs_disc.aero.CD0' - 'traj.phase0.rhs_disc.aero.CLa' - 'traj.phase0.rhs_disc.aero.kappa' - 'traj.phase0.rhs_disc.aero.f_drag' - 'traj.phase0.rhs_disc.aero.f_lift' - 'traj.phase0.rhs_disc.aero.mach' - 'traj.phase0.rhs_disc.aero.q' - 'traj.phase0.rhs_disc.atmos.drhos_dh' - 'traj.phase0.rhs_disc.atmos.pres' - 'traj.phase0.rhs_disc.atmos.rho' - 'traj.phase0.rhs_disc.atmos.sos' - 'traj.phase0.rhs_disc.atmos.temp' - 'traj.phase0.rhs_disc.atmos.viscosity' - 'traj.phase0.rhs_disc.flight_dynamics.gam_dot' - 'traj.phase0.rhs_disc.flight_dynamics.h_dot' - 'traj.phase0.rhs_disc.flight_dynamics.r_dot' - 'traj.phase0.rhs_disc.flight_dynamics.v_dot' - 'traj.phase0.rhs_disc.prop.max_thrust' - 'traj.phase0.rhs_disc.prop.m_dot' - 'traj.phase0.rhs_disc.prop.thrust' - 'traj.phase0.state_interp.state_col:gam': array([[ 0.0702449 ], - 'traj.phase0.state_interp.state_col:h' - 'traj.phase0.state_interp.state_col:m' - 'traj.phase0.state_interp.state_col:r' - 'traj.phase0.state_interp.state_col:v' - 'traj.phase0.dt_dstau' - 'traj.phase0.t' - 'traj.phase0.t_phase' - 'traj.phase0.timeseries.CD': array([[0.0195346 ], - 'traj.phase0.timeseries.CD0' - 'traj.phase0.timeseries.CL' - 'traj.phase0.timeseries.CLa' - 'traj.phase0.timeseries.alpha' - 'traj.phase0.timeseries.f_drag' - 'traj.phase0.timeseries.f_lift' - 'traj.phase0.timeseries.gam' - 'traj.phase0.timeseries.h' - 'traj.phase0.timeseries.kappa' - 'traj.phase0.timeseries.m' - 'traj.phase0.timeseries.m_dot' - 'traj.phase0.timeseries.mach' - 'traj.phase0.timeseries.q' - 'traj.phase0.timeseries.r' - 'traj.phase0.timeseries.thrust' - 'traj.phase0.timeseries.time' - 'traj.phase0.timeseries.time_phase' - 'traj.phase0.timeseries.v' - - """ diff --git a/min_time_climb_models/multi_min_time_to_climb.py b/min_time_climb_models/multi_min_time_to_climb.py deleted file mode 100644 index 99b467850..000000000 --- a/min_time_climb_models/multi_min_time_to_climb.py +++ /dev/null @@ -1,173 +0,0 @@ -import openmdao.api as om -import dymos as dm -from plot_helper import make_min_time_climb_plot -from min_time_climb import MinTimeClimbProblem -import matplotlib.pyplot as plt -import sys - - -class MultiMinTime(om.Problem): - def __init__( - self, heights, weights, optWing=False, modelinfo={}): - super().__init__() - if len(weights) > len(heights): - raise Exception("Can't have more weights than heights!") - elif len(weights) < len(heights): - weights = [1]*len(heights) - - self.weights = weights - self.num_missions = len(heights) - self.probs = [] - - for i, height in enumerate(heights): - prob = MinTimeClimbProblem( - target_height=height, modelinfo=modelinfo) - prob.addTrajectory(optWing=optWing) - self.model.add_subsystem( - f"group_{i}", prob.model, promotes=[('phase0.parameters:S', 'S')]) - self.probs.append(prob) - if optWing: - self.model.add_design_var('S', lower=1, upper=100, units='m**2') - - def addCompoundObj(self): - num_missions = self.num_missions - weights = [float(weight/sum(self.weights)) for weight in self.weights] - times = [f"time_{i}" for i in range(num_missions)] - weighted_sum_str = "+".join([f"{time}*{weight}" for time, - weight in zip(times, weights)]) - self.model.add_subsystem('compoundComp', om.ExecComp( - "compound_time=" + weighted_sum_str), - promotes=['compound_time', *times]) - - for i in range(num_missions): - self.model.connect( - f"group_{i}.phase0.t", times[i], - src_indices=-1) - self.model.add_objective('compound_time') - - def addDriver(self, driver='pyoptsparse', optimizer='SLSQP'): - self.driver = om.pyOptSparseDriver() \ - if driver == 'pyoptsparse' else \ - om.ScipyOptimizeDriver() - self.driver.options['optimizer'] = optimizer # 'IPOPT' - self.driver.declare_coloring() - self.model.linear_solver = om.DirectSolver() - - def setICs(self): - for i, prob in enumerate(self.probs): - prob.setInitialConditions(self, f"group_{i}.") - - -def multiExample(): - """Example of multi mission min time to climb problem.""" - makeN2 = True if "n2" in sys.argv else False - super_prob = MultiMinTime(heights=[10e3, 15e3], weights=[1, 1], - optWing=True, modelinfo={'m_initial': 23e3}) - super_prob.addCompoundObj() - super_prob.addDriver() - super_prob.setup() - super_prob.setICs() - if makeN2: - sys.path.append('../') - from createN2 import createN2 - createN2(__file__, super_prob) - dm.run_problem(super_prob, simulate=True) - - wing_area = super_prob.get_val('S', units='m**2')[0] - print("\n\n=====================================") - for i in range(super_prob.num_missions): - timetoclimb = super_prob.get_val(f'group_{i}.phase0.t', units='s')[-1] - print(f"TtoC: {timetoclimb}, S: {wing_area}") - - make_min_time_climb_plot( - solfile='dymos_solution.db', - simfile=['dymos_simulation.db', 'dymos_simulation_1.db'], - solprefix='group', omitpromote='traj') - - -def weightCompare(): - """Runs the multi mission min time to climb problem for different weights. Shows - impact of changing weights on 1 figure.""" - heights = [10e3, 15e3] - weights_to_test = [[1, 3], [3, 1]] - modelinfo = {'m_initial': 18e3, 'S': 49.24, 'v_initial': 104, 'h_initial': 100, - 'mach_final': 1.0} - solfiles, simfiles = [], [] - for i, weights in enumerate(weights_to_test): - super_prob = MultiMinTime(heights=heights, weights=weights, - optWing=True, modelinfo=modelinfo) - super_prob.addCompoundObj() - super_prob.addDriver(driver='scipy') - super_prob.setup() - super_prob.setICs() - solfiles.append(f'weightsSol_{i}.db') - simfiles.append(f'weightsSim_{i}.db') - dm.run_problem(super_prob, simulate=True, - solution_record_file=solfiles[-1], - simulation_record_file=simfiles[-1]) - - fig = plt.figure() - colores = [['r', 'b'], ['g', 'm']] - for i, (solfile, simfile, colors) in enumerate(zip(solfiles, simfiles, colores)): - make_min_time_climb_plot( - solfile=solfile, - simfile=[simfile, simfile.replace(".db", "_1.db")], - solprefix='group', omitpromote='traj', show=False, fig=fig, - extratitle=", ".join([str(w) for w in weights_to_test[i]]), - colors=colors) - - plt.show() - - -def comparison(): - """Runs min time to climb problem for 2 heights individually, as well as with the - multi mission approach. Creates 2 figures showing the differences between the 2.""" - heights = [10e3, 15e3] - weights = [1, 1] - optimize_wing = True - m_0 = 23e3 - modelinfo = {'m_initial': m_0, 'S': 49.24, 'v_initial': 104, 'h_initial': 100, - 'mach_final': 1.0} - - solfiles, simfiles = [], [] - for i, height in enumerate(heights): - p = MinTimeClimbProblem(target_height=height, modelinfo=modelinfo) - p.addTrajectory(optWing=optimize_wing) - p.addObjective() - p.setOptimizer(driver='pyoptsparse') - p.setup() - p.setInitialConditions() - solfile, simfile = f'Sol_Comp_{i}.db', f'Sim_Comp_{i}.db' - solfiles.append(solfile) - simfiles.append(simfile) - dm.run_problem( - p, simulate=True, solution_record_file=solfile, - simulation_record_file=simfile) - - super_prob = MultiMinTime(heights=heights, weights=weights, - optWing=optimize_wing, modelinfo=modelinfo) - super_prob.addCompoundObj() - super_prob.addDriver() - super_prob.setup() - super_prob.setICs() - dm.run_problem(super_prob, simulate=True) - - fig1, fig2 = plt.figure(1), plt.figure(2) - make_min_time_climb_plot( - solfile=solfiles, simfile=simfiles, omitpromote='traj', show=False, fig=fig1, - extratitle=f"{m_0} kg") - make_min_time_climb_plot( - solfile='dymos_solution.db', - simfile=['dymos_simulation.db', 'dymos_simulation_1.db'], - solprefix='group', omitpromote='traj', show=False, fig=fig2, - extratitle=f"{m_0} kg") - plt.show() - - -if __name__ == '__main__': - if "comparison" in sys.argv: - comparison() - elif "weights" in sys.argv: - weightCompare() - else: - multiExample() diff --git a/min_time_climb_models/plot_helper.py b/min_time_climb_models/plot_helper.py deleted file mode 100644 index e8acc460e..000000000 --- a/min_time_climb_models/plot_helper.py +++ /dev/null @@ -1,98 +0,0 @@ -import matplotlib.pyplot as plt -from openmdao.api import CaseReader - - -def make_min_time_climb_plot( - solfile='dymos_solution.db', simfile='dymos_simulation.db', solprefix='', - omitpromote=None, show=True, fig=None, extratitle='', colors=['r', 'b', 'g', 'm']): - - singleprob, multiprob, multitraj = True, False, False - if isinstance(solfile, list) and isinstance(simfile, list): - multiprob, singleprob = True, False - if len(solfile) != len(simfile): - raise Exception( - "Must provide same number of solution and simulation files with separate problems") - - elif isinstance(simfile, list) and isinstance(solfile, str): - multitraj, singleprob = True, False - solfile = [solfile]*len(simfile) - if solprefix == '': - raise Exception( - "When plotting multiple trajectories, must provide prefix to access solutions!") - - if singleprob: - solfile, simfile = [solfile], [simfile] - - if fig is None: - fig = plt.figure() - plotvars = [('r', 'h'), - ('time', 'h'), - ('time', 'v'), - ('time', 'thrust'), - ('time', 'gam'), - ('time', 'alpha')] - plotunits = [ - ('km', 'km'), - ('s', 'km'), - ('s', 'm/s'), - ('s', 'kN'), - ('s', 'deg'), - ('s', 'deg')] - - numplots = len(plotvars) - axes = fig.axes - if len(axes) == 0: - axes = [None]*len(plotvars) - tsprefix = 'traj.phase0.timeseries.' - - sols = [CaseReader(file).get_case('final') for file in solfile] - sims = [CaseReader(file).get_case('final') for file in simfile] - - legend = [] - areas = [] - heights = [None]*len(simfile) - - for i, (solf, simf) in enumerate(zip(sols, sims)): - for j, ((xvar, yvar), (xunit, yunit)) in enumerate(zip(plotvars, plotunits)): - if axes[j] is None: - ax = fig.add_subplot(2, int(numplots/2), j+1, - xlabel=f"{xvar} ({xunit})", - ylabel=f"{yvar} ({yunit})") - axes[j] = ax - else: - ax = axes[j] - xname, yname = addPrefix(tsprefix, (xvar, yvar)) - xsim = simf.get_val(xname, units=xunit) - ysim = simf.get_val(yname, units=yunit) - if omitpromote is not None: - xname = xname.replace(omitpromote+".", "") - yname = yname.replace(omitpromote+".", "") - if multitraj: - xname, yname = addPrefix(f"{solprefix}_{i}.", (xname, yname)) - xsol = solf.get_val(xname, units=xunit) - ysol = solf.get_val(yname, units=yunit) - if yvar == "h" and not heights[i]: - heights[i] = round(ysol[-1][0]) - ax.plot(xsol, ysol, f"{colors[i]}o", fillstyle='none') - ax.plot(xsim, ysim, colors[i]) - ax.grid(visible=True) - legend.append(f"{heights[i]} {plotunits[0][1]} solution") - legend.append(f"{heights[i]} {plotunits[0][1]} simulation") - try: - areas.append(round(solf.get_val('S')[0], 2)) - except KeyError: - areas.append(round(solf.get_val('phase0.parameters:S')[0], 2)) - fig.legend(legend, ncols=len(simfile), loc='lower center') - fig.suptitle(f"Min Time to Climb, wing areas: {areas}, {extratitle}") - fig.tight_layout(pad=1) - if show: - plt.show() - - -def addPrefix(prefix, iterable): - return [prefix+item for item in iterable] - - -if __name__ == '__main__': - make_min_time_climb_plot(solfile=['dymos_solution_0.db', 'dymos_solution_1.db'], - simfile=['dymos_simulation_0.db', 'dymos_simulation_1.db']) diff --git a/multi_aviary_submodel.py b/multi_aviary_submodel.py deleted file mode 100644 index c1a640c72..000000000 --- a/multi_aviary_submodel.py +++ /dev/null @@ -1,125 +0,0 @@ -""" -Goal: use single aircraft description but optimize it for multiple missions simultaneously, -i.e. all missions are on the range-payload line instead of having excess performance -Aircraft csv: defines plane, but also defines payload (passengers, cargo) which can vary with mission - These will have to be specified in some alternate way such as a list correspond to mission # -Phase info: defines a particular mission, will have multiple phase infos -""" -import sys -import aviary.api as av -import openmdao.api as om -import dymos as dm -from c5_models.c5_ferry_phase_info import phase_info as c5_ferry_phase_info -from c5_models.c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info -from c5_models.c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info - -planes = ['c5_models/c5_maxpayload.csv', 'c5_models/c5_intermediate.csv'] -phase_infos = [c5_maxpayload_phase_info, c5_intermediate_phase_info] -weights = [1, 1] -num_missions = len(weights) - -if __name__ == '__main__': - makeN2 = True if len(sys.argv) > 1 and sys.argv[1] == "n2" else False - super_prob = om.Problem() - probs = [] - - # define individual aviary problems - for i, (plane, phase_info) in enumerate(zip(planes, phase_infos)): - prob = av.AviaryProblem() - prob.load_inputs(plane, phase_info) - prob.check_and_preprocess_inputs() - prob.add_pre_mission_systems() - prob.add_phases() - prob.add_post_mission_systems() - prob.link_phases() - probs.append(prob) - - subcomp = om.SubmodelComp( - problem=prob, inputs=['mission:design:gross_mass', 'aircraft:wing:span'], - outputs=['mission:summary:fuel_burned']) - # promoting gross mass to be used as a design var - # all problems have same name for gross mass so they are connected - super_prob.model.add_subsystem(f'subcomp_{i}', subcomp, promotes_inputs=[ - 'mission:design:gross_mass', 'aircraft:wing:span']) - - # creating variable strings that will represent fuel burn from each mission - fuel_burned_vars = [f"fuel_{i}" for i in range(num_missions)] - weighted_str = "+".join([f"{fuel}*{weight}" - for fuel, weight in zip(fuel_burned_vars, weights)]) - # weighted_str looks like: fuel_0 * weight[0] + fuel_1 * weight[1] - - # adding compound execComp to super problem - super_prob.model.add_subsystem('compound', om.ExecComp( - "compound = "+weighted_str), promotes=["compound", *fuel_burned_vars]) - - # connecting each subcomponent's fuel burn to super problem's unique fuel variables - # fuel_0, fuel_1, ... don't have units assigned, #TODO find a solution to specify units - for i in range(num_missions): - super_prob.model.connect(f"subcomp_{i}.mission:summary:fuel_burned", f"fuel_{i}") - - # specify gross mass as a design var - super_prob.model.add_design_var( - 'mission:design:gross_mass', lower=100e3, upper=1000e3, units='lbm') - - # this throws error: output not found for this design var - # super_prob.model.add_design_var( - # 'aircraft:design:span', lower=100., upper=300., units='ft') - - super_prob.driver = om.ScipyOptimizeDriver() - super_prob.driver.options['optimizer'] = 'SLSQP' - - super_prob.model.add_objective('compound') # output from execcomp goes here - - super_prob.setup() - - # set initial guesses for each aviary problem - for prob in probs: - prob.set_initial_guesses() - - if makeN2: - from createN2 import createN2 - createN2(__file__, super_prob) - - dm.run_problem(super_prob) - print(super_prob.check_partials()) - - -""" -Ferry mission phase info: -Times (min): 0, 50, 812, 843 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 7001 nmi -Notes: 32k in 30 mins too fast for aviary, climb to low alt then slow rise through cruise - -Intermediate mission phase info: -Times (min): 0, 50, 560, 590 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 4839 nmi - -Max Payload mission phase info: -Times (min): 0, 50, 260, 290 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 2272 nmi - -Hard to find multiple payload/range values for FwFm (737), so use C-5 instead -Based on: - https://en.wikipedia.org/wiki/Lockheed_C-5_Galaxy#Specifications_(C-5M), - https://www.af.mil/About-Us/Fact-Sheets/Display/Article/1529718/c-5-abc-galaxy-and-c-5m-super-galaxy/ - -MTOW: 840,000 lb -Max Payload: 281,000 lb -Max Fuel: 341,446 lb -Empty Weight: 380,000 lb -> leaves 460,000 lb for fuel+payload (max fuel + max payload = 622,446 lb) - -Payload/range: - 281,000 lb payload -> 2,150 nmi range (AF.mil) [max payload case] - 120,000 lb payload -> 4,800 nmi range (AF.mil) [intermediate case] - 0 lb payload -> 7,000 nmi range (AF.mil) [ferry case] - -Flight characteristics: - Cruise at M0.77 at 33k ft - Max rate of climb: 2100 ft/min -""" diff --git a/single_aviary.py b/single_aviary.py deleted file mode 100644 index 5966b37d6..000000000 --- a/single_aviary.py +++ /dev/null @@ -1,129 +0,0 @@ -from c5_models.c5_ferry_phase_info import phase_info as c5_ferry_phase_info -from c5_models.c5_intermediate_phase_info import phase_info as c5_intermediate_phase_info -from c5_models.c5_maxpayload_phase_info import phase_info as c5_maxpayload_phase_info -import aviary.api as av -import openmdao.api as om -import sys - - -def modify_plane(orig_filename, payloads, ranges): - if len(sys.argv) > 1: - plane_name = orig_filename.split(".csv")[0] - mission = sys.argv[1].lower() - temp_filename = f"{plane_name}_{mission}.csv" - with open(orig_filename, "r") as orig_plane: - orig_lines = orig_plane.readlines() - with open(temp_filename, "w") as temp_plane: - try: - payload, misrange = payloads[mission], ranges[mission] - except KeyError: - payload, misrange = "", "" - for line in orig_lines: - if "aircraft:crew_and_payload:cargo_mass" in line and payload != "": - line = ",".join( - [line.split(",")[0], - str(payload), - line.split(",")[2]]) - - elif "mission:design:range" in line and misrange != "": - line = ",".join( - [line.split(",")[0], - str(misrange), - line.split(",")[2]]) - - temp_plane.write(line) - else: - return orig_filename - return temp_filename, mission - - -if __name__ == '__main__': - makeN2 = True if len(sys.argv) > 2 and "n2" in sys.argv else False - prob = av.AviaryProblem() - plane_file = 'c5.csv' - payloads = {"ferry": 0, "intermediate": 120e3, "maxpayload": 281e3} - ranges = {"ferry": 7e3, "intermediate": 4.8e3, "maxpayload": 2.15e3} - plane_file, mission_name = modify_plane(plane_file, payloads, ranges) - phase_info = c5_maxpayload_phase_info - if mission_name == "intermediate": - phase_info = c5_intermediate_phase_info - elif mission_name == "ferry": - phase_info = c5_ferry_phase_info - - # Load aircraft and options data from user - # Allow for user overrides here - prob.load_inputs(plane_file, phase_info) - - # Preprocess inputs - prob.check_and_preprocess_inputs() - - prob.add_pre_mission_systems() - - prob.add_phases() - - prob.add_post_mission_systems() - - # Link phases and variables - prob.link_phases() - - prob.add_driver("SLSQP", max_iter=50) - - prob.add_design_variables() - - # Load optimization problem formulation - # Detail which variables the optimizer can control - prob.add_objective() # output from execcomp goes here) - - prob.setup() - - if makeN2: - om.n2(prob, outfile='single_aviary.html') - - prob.set_initial_guesses() - - # remove all plots and extras - prob.run_aviary_problem( - record_filename=f'{plane_file.split(".csv")[0]}.db', suppress_solver_print=True) - # prob.get_val() # look at final fuel burn - print( - f"Fuel burned: {prob.get_val(av.Mission.Summary.FUEL_BURNED,units='lbm')[0]:.3f} lbm") - -""" -Ferry mission phase info: -Times (min): 0, 50, 812, 843 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 7001 nmi -Notes: 32k in 30 mins too fast for aviary, climb to low alt then slow rise - -Intermediate mission phase info: -Times (min): 0, 50, 560, 590 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 4839 nmi - -Max Payload mission phase info: -Times (min): 0, 50, 260, 290 - Alt (ft): 0, 29500, 32000, 0 - Mach: 0.3, 0.77, 0.77, 0.3 -Est. Range: 2272 nmi - -Hard to find multiple payload/range values for FwFm (737), so use C-5 instead -Based on: - https://en.wikipedia.org/wiki/Lockheed_C-5_Galaxy#Specifications_(C-5M), - https://www.af.mil/About-Us/Fact-Sheets/Display/Article/1529718/c-5-abc-galaxy-and-c-5m-super-galaxy/ - -MTOW: 840,000 lb -Max Payload: 281,000 lb -Max Fuel: 341,446 lb -Empty Weight: 380,000 lb -> leaves 460,000 lb for fuel+payload (max fuel + max payload = 622,446 lb) - -Payload/range: - 281,000 lb payload -> 2,150 nmi range (AF.mil) [max payload case] - 120,000 lb payload -> 4,800 nmi range (AF.mil) [intermediate case] - 0 lb payload -> 7,000 nmi range (AF.mil) [ferry case] - -Flight characteristics: - Cruise at M0.77 at 33k ft - Max rate of climb: 2100 ft/min -""" From 052acc99a9cc1f59966274f3265775d21a1cee26 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Wed, 11 Sep 2024 15:34:40 -0400 Subject: [PATCH 062/113] moved createN2 into run_multimission example temporarily --- N2s/n2_multi_aviary_copymodel.html | 14840 ---------------- N2s/n2_multi_aviary_submodel.html | 14840 ---------------- N2s/n2_multi_cannonball_copymodel.html | 14840 ---------------- N2s/n2_multi_cannonball_copyparts.html | 14840 ---------------- N2s/n2_multi_min_time_to_climb.html | 14840 ---------------- ...multimission_example_large_single_aisle.py | 9 +- createN2.py | 8 - 7 files changed, 8 insertions(+), 74209 deletions(-) delete mode 100644 N2s/n2_multi_aviary_copymodel.html delete mode 100644 N2s/n2_multi_aviary_submodel.html delete mode 100644 N2s/n2_multi_cannonball_copymodel.html delete mode 100644 N2s/n2_multi_cannonball_copyparts.html delete mode 100644 N2s/n2_multi_min_time_to_climb.html delete mode 100644 createN2.py diff --git a/N2s/n2_multi_aviary_copymodel.html b/N2s/n2_multi_aviary_copymodel.html deleted file mode 100644 index e1f80b09c..000000000 --- a/N2s/n2_multi_aviary_copymodel.html +++ /dev/null @@ -1,14840 +0,0 @@ - - - -OpenMDAO Model Hierarchy and N2 diagram - - - - - - - - - - - - - - - - - -
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- - - - - - - diff --git a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py index ef49b1c77..6bb3a2968 100644 --- a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py @@ -265,7 +265,14 @@ def large_single_aisle_example(makeN2=False): prob.set_initial_guesses(super_prob, super_prob.group_prefix+f"_{i}.") if makeN2: - from createN2 import createN2 + # TODO: Not sure we need this at all. + from openmdao.api import n2 + from os.path import basename, dirname, join, abspath + def createN2(fileref, prob): + n2folder = join(dirname(abspath(__file__)), "N2s") + n2(prob, outfile=join(n2folder, + f"n2_{basename(fileref).split('.')[0]}.html")) + createN2(__file__, super_prob) super_prob.run() diff --git a/createN2.py b/createN2.py deleted file mode 100644 index a41f99de6..000000000 --- a/createN2.py +++ /dev/null @@ -1,8 +0,0 @@ -from openmdao.api import n2 -from os.path import basename, dirname, join, abspath - - -def createN2(fileref, prob): - n2folder = join(dirname(abspath(__file__)), "N2s") - n2(prob, outfile=join(n2folder, - f"n2_{basename(fileref).split('.')[0]}.html")) From 2c77bf0ff837df30f5ae02094250ba6a612ee7c6 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Wed, 11 Sep 2024 15:35:52 -0400 Subject: [PATCH 063/113] removed deck obsoluted since c5 examples were also removed --- aviary/models/engines/CF6.deck | 623 --------------------------------- 1 file changed, 623 deletions(-) delete mode 100644 aviary/models/engines/CF6.deck diff --git a/aviary/models/engines/CF6.deck b/aviary/models/engines/CF6.deck deleted file mode 100644 index 2d4b0f42a..000000000 --- a/aviary/models/engines/CF6.deck +++ /dev/null @@ -1,623 +0,0 @@ -Mach_Number (unitless), Altitude (ft), Throttle (unitless), Gross_Thrust (lbf), Ram_Drag (lbf), Fuel_Flow (lb/h), NOx_Rate (lb/h) -0, 0, 50, 51463, 0, 22544.2, 0.438066 -0, 0, 47, 46316.7, 0, 19554.2, 0.422184 -0, 0, 44, 41168.9, 0, 16706.8, 0.405811 -0, 0, 41, 36024.5, 0, 13993.4, 0.388441 -0, 0, 38, 30878.2, 0, 11478.9, 0.371747 -0, 0, 35, 25731.7, 0, 9223.64, 0.358454 -0, 0, 32, 20585, 0, 7189.32, 0.34925 -0, 0, 29, 15438.9, 0, 5352.09, 0.346662 -0, 0, 26, 10292.6, 0, 3719.21, 0.361348 -0.1, 0, 50, 54023, 5123.45, 23900.4, 0.488765 -0.1, 0, 47, 48904.4, 4894.93, 20792.4, 0.472452 -0.1, 0, 44, 43772.3, 4652.35, 17907.1, 0.457748 -0.1, 0, 41, 38628.8, 4399.32, 15117.4, 0.441647 -0.1, 0, 38, 33471.3, 4130.98, 12495.1, 0.425866 -0.1, 0, 35, 28290.4, 3840.72, 10110.9, 0.413537 -0.1, 0, 32, 23067.1, 3507.29, 7960.7, 0.406992 -0.1, 0, 29, 17780.3, 3110.29, 5995.71, 0.408705 -0.1, 0, 26, 12400.2, 2620.36, 4197.43, 0.429192 -0.2, 0, 50, 57647.3, 10603.3, 25425.5, 0.540462 -0.2, 0, 47, 52504, 10164.3, 22162.3, 0.523439 -0.2, 0, 44, 47327.3, 9692.14, 19180.2, 0.509636 -0.2, 0, 41, 42129, 9198.28, 16310.9, 0.495309 -0.2, 0, 38, 36905.1, 8679.85, 13562.1, 0.480496 -0.2, 0, 35, 31649.4, 8127.32, 10997.6, 0.467541 -0.2, 0, 32, 26321.7, 7503.92, 8696.87, 0.462162 -0.2, 0, 29, 20873.9, 6760.73, 6578.5, 0.466124 -0.2, 0, 26, 15253.2, 5844.67, 4620.23, 0.491067 -0.25, 0, 50, 59887.9, 13531.2, 26264, 0.566562 -0.25, 0, 47, 54709.5, 12988.4, 22946.7, 0.550002 -0.25, 0, 44, 49496.2, 12410.9, 19864.2, 0.535636 -0.25, 0, 41, 44250, 11801.1, 16940.8, 0.522076 -0.25, 0, 38, 38975.5, 11161.9, 14130.5, 0.508044 -0.25, 0, 35, 33661.3, 10482.8, 11491.3, 0.495772 -0.25, 0, 32, 28276.6, 9734.59, 9078.89, 0.48964 -0.25, 0, 29, 22745.7, 8838.64, 6880.2, 0.494728 -0.25, 0, 26, 17001.5, 7730.26, 4863.81, 0.524611 -0.3, 0, 50, 61345.2, 16480.9, 26442.8, 0.589397 -0.3, 0, 47, 56222.3, 15844.4, 23161.1, 0.573608 -0.3, 0, 44, 51062.6, 15171.4, 20084, 0.55958 -0.3, 0, 41, 45863.4, 14458.8, 17172.1, 0.546804 -0.3, 0, 38, 40630.7, 13712.8, 14371.1, 0.533887 -0.3, 0, 35, 35354.9, 12921.9, 11733, 0.523024 -0.3, 0, 32, 30003.3, 12058.2, 9305.99, 0.518583 -0.3, 0, 29, 24490.1, 11030.8, 7081.42, 0.526135 -0.3, 0, 26, 18737.7, 9764.8, 5027.29, 0.560277 -0.4, 0, 50, 65109.9, 22791, 26900.6, 0.635663 -0.4, 0, 47, 60065.1, 21978.5, 23682.1, 0.621795 -0.4, 0, 44, 54979.7, 21124.2, 20632.6, 0.609431 -0.4, 0, 41, 49860.8, 20237.6, 17672.8, 0.596586 -0.4, 0, 38, 44688.5, 19298.1, 14871.6, 0.585718 -0.4, 0, 35, 39465.8, 18305.4, 12227, 0.577823 -0.4, 0, 32, 34166.3, 17239.4, 9767.5, 0.57704 -0.4, 0, 29, 28693.9, 15998.2, 7482.36, 0.589363 -0.4, 0, 26, 22941.7, 14477.9, 5359.4, 0.633215 -0.5, 0, 50, 70055, 29779.2, 27487, 0.68247 -0.5, 0, 47, 65050.3, 28802.7, 24313.7, 0.670767 -0.5, 0, 44, 60006.3, 27785.4, 21267.7, 0.660061 -0.5, 0, 41, 54933.8, 26740.6, 18278.4, 0.648327 -0.5, 0, 38, 49804.8, 25639.6, 15438, 0.638853 -0.5, 0, 35, 44613.5, 24475.6, 12761.1, 0.633688 -0.5, 0, 32, 39346.5, 23236.6, 10261.2, 0.636952 -0.5, 0, 29, 33908.7, 21826, 7940.59, 0.657184 -0.5, 0, 26, 28159.8, 20104.6, 5792.28, 0.719078 -0, 2000, 50, 49123, 0, 21568.5, 0.439072 -0, 2000, 47, 44210.8, 0, 18665, 0.422182 -0, 2000, 44, 39298.6, 0, 15951.1, 0.405896 -0, 2000, 41, 34385.7, 0, 13349.7, 0.388235 -0, 2000, 38, 29474, 0, 10936.3, 0.371051 -0, 2000, 35, 24561.4, 0, 8769.85, 0.357058 -0, 2000, 32, 19649.5, 0, 6824.42, 0.347308 -0, 2000, 29, 14737, 0, 5070.39, 0.34406 -0, 2000, 26, 9824.59, 0, 3510.74, 0.357342 -0.1, 2000, 50, 51538.6, 4821.09, 22855.7, 0.489231 -0.1, 2000, 47, 46652.4, 4606.79, 19839.4, 0.471855 -0.1, 2000, 44, 41751.7, 4377.35, 17079.5, 0.456984 -0.1, 2000, 41, 36839.9, 4137.67, 14421.4, 0.440991 -0.1, 2000, 38, 31915.2, 3884.26, 11907.2, 0.424786 -0.1, 2000, 35, 26969.6, 3610.79, 9613.12, 0.411541 -0.1, 2000, 32, 21985.2, 3298.23, 7554.94, 0.404289 -0.1, 2000, 29, 16940.5, 2925.36, 5678.88, 0.405195 -0.1, 2000, 26, 11808.4, 2464.95, 3961.86, 0.424026 -0.2, 2000, 50, 54856.9, 9965.33, 24261, 0.540436 -0.2, 2000, 47, 49954, 9551.35, 21122.7, 0.522806 -0.2, 2000, 44, 45021.5, 9108.3, 18243.8, 0.507997 -0.2, 2000, 41, 40063.8, 8640.77, 15515.3, 0.493757 -0.2, 2000, 38, 35085.2, 8150.44, 12894.4, 0.478727 -0.2, 2000, 35, 30074.3, 7628.41, 10439.8, 0.46511 -0.2, 2000, 32, 25000.6, 7044.03, 8236.45, 0.458687 -0.2, 2000, 29, 19814, 6346.56, 6218.85, 0.461769 -0.2, 2000, 26, 14463.4, 5485.34, 4356.44, 0.485233 -0.25, 2000, 50, 56889.7, 12706.1, 25024.5, 0.566374 -0.25, 2000, 47, 51961.3, 12195.5, 21825, 0.54884 -0.25, 2000, 44, 47000.7, 11653.7, 18858.8, 0.533533 -0.25, 2000, 41, 42003.8, 11076.7, 16083.3, 0.520042 -0.25, 2000, 38, 36983.1, 10472.6, 13408.8, 0.505793 -0.25, 2000, 35, 31923.6, 9831.26, 10889.6, 0.492914 -0.25, 2000, 32, 26801.1, 9128.33, 8586.63, 0.485867 -0.25, 2000, 29, 21543.1, 8287.86, 6496.23, 0.490086 -0.25, 2000, 26, 16082.8, 7246.19, 4580.78, 0.518386 -0.3, 2000, 50, 58331.4, 15483.3, 25230.6, 0.588838 -0.3, 2000, 47, 53446.2, 14882.7, 22072.7, 0.572374 -0.3, 2000, 44, 48527.8, 14249.2, 19112.4, 0.557561 -0.3, 2000, 41, 43569.4, 13575.4, 16334.7, 0.544599 -0.3, 2000, 38, 38578.2, 12869, 13661.2, 0.531375 -0.3, 2000, 35, 33545.5, 12120.8, 11136.9, 0.519816 -0.3, 2000, 32, 28446.2, 11307.5, 8816.1, 0.514398 -0.3, 2000, 29, 23197.6, 10343, 6696.12, 0.520911 -0.3, 2000, 26, 17721.2, 9151.59, 4740.96, 0.553229 -0.4, 2000, 50, 61981.9, 21423.2, 25729.2, 0.634369 -0.4, 2000, 47, 57158, 20655.1, 22625.3, 0.619823 -0.4, 2000, 44, 52291.4, 19844.4, 19699.7, 0.607135 -0.4, 2000, 41, 47394.8, 19004.4, 16860.6, 0.593884 -0.4, 2000, 38, 42447.5, 18112.3, 14179, 0.582652 -0.4, 2000, 35, 37450.7, 17170.6, 11636.7, 0.573801 -0.4, 2000, 32, 32383.3, 16160.4, 9278.77, 0.571955 -0.4, 2000, 29, 27160.9, 14993.3, 7092.66, 0.582913 -0.4, 2000, 26, 21672.9, 13561.2, 5059.77, 0.623759 -0.5, 2000, 50, 66628.7, 27978.1, 26303.5, 0.680546 -0.5, 2000, 47, 61841, 27055.7, 23234, 0.667925 -0.5, 2000, 44, 57008, 26087.2, 20316.8, 0.657059 -0.5, 2000, 41, 52146.2, 25090.8, 17461.2, 0.645387 -0.5, 2000, 38, 47235.5, 24046.9, 14725.1, 0.635014 -0.5, 2000, 35, 42266.2, 22940.8, 12151.8, 0.6288 -0.5, 2000, 32, 37223.4, 21763.6, 9748.24, 0.630555 -0.5, 2000, 29, 32029.4, 20434.2, 7526.35, 0.649094 -0.5, 2000, 26, 26539.5, 18809.4, 5468.06, 0.707372 -0, 5000, 50, 45729, 0, 20147.1, 0.440576 -0, 5000, 47, 41156.2, 0, 17375.5, 0.422184 -0, 5000, 44, 36583.5, 0, 14847.5, 0.405853 -0, 5000, 41, 32010.2, 0, 12420.3, 0.38801 -0, 5000, 38, 27437.9, 0, 10162.2, 0.370371 -0, 5000, 35, 22864.4, 0, 8117.71, 0.355037 -0, 5000, 32, 18291.6, 0, 6302.05, 0.344532 -0, 5000, 29, 13718.8, 0, 4668.69, 0.340313 -0, 5000, 26, 9145.66, 0, 3214.88, 0.35152 -0.1, 5000, 50, 47774.7, 4385.2, 21260.7, 0.489997 -0.1, 5000, 47, 43241.8, 4191.27, 18388.1, 0.47088 -0.1, 5000, 44, 38693.5, 3981.83, 15806.6, 0.455369 -0.1, 5000, 41, 34133.4, 3761.8, 13349.8, 0.43955 -0.1, 5000, 38, 29564.2, 3530.12, 11008.2, 0.422838 -0.1, 5000, 35, 24975.1, 3280.19, 8864.57, 0.408602 -0.1, 5000, 32, 20353.4, 2997.61, 6944.72, 0.400139 -0.1, 5000, 29, 15676.3, 2659.48, 5205.59, 0.399912 -0.1, 5000, 26, 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39000, 41, 17297, 10770.5, 4339.18, 0.664853 -0.8, 39000, 38, 15984.2, 10389.5, 3688.43, 0.659273 -0.8, 39000, 35, 14656.3, 9994.34, 3071.77, 0.658897 -0.8, 39000, 32, 13313.7, 9584.24, 2492.36, 0.668286 -0.8, 39000, 29, 11947.1, 9149.87, 1945.97, 0.695682 -0.8, 39000, 26, 10548, 8683.19, 1430.95, 0.767342 -0.8, 39000, 21, 8190.5, 7724.31, 760.273, 1.63079 -0.85, 39000, 50, 22776.9, 13178.4, 6831.86, 0.711759 -0.85, 39000, 47, 21427.2, 12788.4, 6050.07, 0.700335 -0.85, 39000, 44, 20054.6, 12375.9, 5317.72, 0.692527 -0.85, 39000, 41, 18673.5, 11954.8, 4610.27, 0.686188 -0.85, 39000, 38, 17291.5, 11532.1, 3917.84, 0.680249 -0.85, 39000, 35, 15892.6, 11093.4, 3261.28, 0.679541 -0.85, 39000, 32, 14478.4, 10639.1, 2644.13, 0.688709 -0.85, 39000, 29, 13048.3, 10168.7, 2062.72, 0.716329 -0.85, 39000, 26, 11591.2, 9671.47, 1515.86, 0.789631 -0.85, 39000, 21, 9153.9, 8673.97, 804.814, 1.67696 -0.9, 39000, 50, 24515.6, 14604, 7280.33, 0.734532 -0.9, 39000, 47, 23092.9, 14172.5, 6447.04, 0.722732 -0.9, 39000, 44, 21644.4, 13715.3, 5665.61, 0.714534 -0.9, 39000, 41, 20186.2, 13248.5, 4910.43, 0.707788 -0.9, 39000, 38, 18727.1, 12779.9, 4171.32, 0.701389 -0.9, 39000, 35, 17248.8, 12293.1, 3469.88, 0.700175 -0.9, 39000, 32, 15753.1, 11788.7, 2810.11, 0.708831 -0.9, 39000, 29, 14239.3, 11265.8, 2188.44, 0.735991 -0.9, 39000, 26, 12704.3, 10722, 1604.97, 0.809645 -0.9, 39000, 21, 10180.1, 9684.56, 847.502, 1.71014 -0.7, 43000, 50, 15244.9, 7905.28, 4755.01, 0.647856 -0.7, 43000, 47, 14274.5, 7668.89, 4210.44, 0.637402 -0.7, 43000, 44, 13291.4, 7419.82, 3701.44, 0.630396 -0.7, 43000, 41, 12303.3, 7165.8, 3209.77, 0.62477 -0.7, 43000, 38, 11310, 6906.06, 2728.9, 0.619649 -0.7, 43000, 35, 10299.7, 6629.95, 2274.38, 0.619764 -0.7, 43000, 32, 9272.51, 6336.76, 1848.37, 0.629609 -0.7, 43000, 29, 8226.51, 6024.62, 1446.77, 0.657061 -0.7, 43000, 26, 7144.26, 5676.34, 1066.63, 0.726629 -0.7, 43000, 21, 5312.51, 4945.53, 567.524, 1.54646 -0.75, 43000, 50, 16312.2, 8810.25, 5021.42, 0.66935 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1.66448 -0.85, 43000, 50, 18795.8, 10872.5, 5651.78, 0.713312 -0.85, 43000, 47, 17681.5, 10550.6, 5006.32, 0.702055 -0.85, 43000, 44, 16548.3, 10209.7, 4402.05, 0.69449 -0.85, 43000, 41, 15408.2, 9862.12, 3817.82, 0.688385 -0.85, 43000, 38, 14267.3, 9513.05, 3246.11, 0.682786 -0.85, 43000, 35, 13112.2, 9150.58, 2704.26, 0.682616 -0.85, 43000, 32, 11944.3, 8775.09, 2195.24, 0.692682 -0.85, 43000, 29, 10763.4, 8386.44, 1715.16, 0.721569 -0.85, 43000, 26, 9560.52, 7975.87, 1263.34, 0.797234 -0.85, 43000, 21, 7545.89, 7149.73, 677.138, 1.70923 -0.9, 43000, 50, 20230.2, 12048.8, 6021.6, 0.736009 -0.9, 43000, 47, 19055.7, 11692.4, 5333.92, 0.724392 -0.9, 43000, 44, 17859.8, 11314.8, 4689.04, 0.716427 -0.9, 43000, 41, 16656.1, 10929.4, 4065.39, 0.7099 -0.9, 43000, 38, 15451.5, 10542.4, 3455.17, 0.70383 -0.9, 43000, 35, 14230.9, 10140.3, 2876.26, 0.703126 -0.9, 43000, 32, 12995.8, 9723.33, 2332.1, 0.71265 -0.9, 43000, 29, 11745.8, 9291.37, 1818.79, 0.741025 -0.9, 43000, 26, 10478.6, 8842.36, 1336.74, 0.816939 -0.9, 43000, 21, 8392.24, 7983.17, 712.209, 1.74104 From 8aa0938f3c5de65d6117646200ee1ad10b7e2e72 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Wed, 18 Sep 2024 13:12:21 -0400 Subject: [PATCH 064/113] updates to preprocessor to ensure that proper checks are being run on num_passengers and design_num_passengers, some pep8 updates --- ...multimission_example_large_single_aisle.py | 42 ++++++---- aviary/interface/methods_for_level2.py | 6 +- aviary/utils/preprocessors.py | 81 +++++++++++++------ 3 files changed, 85 insertions(+), 44 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py index 6bb3a2968..cb6fdc058 100644 --- a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py @@ -8,6 +8,7 @@ aircraft:crew_and_payload:num_first_class,0,unitless """ +from aviary.validation_cases.validation_tests import get_flops_inputs from aviary.api import SubsystemBuilderBase from aviary.subsystems.mass.flops_based.furnishings import TransportFurnishingsGroupMass import sys @@ -29,24 +30,32 @@ # fly the same mission twice with two different passenger loads phase_info_primary = copy.deepcopy(phase_info) phase_info_deadhead = copy.deepcopy(phase_info) +# phase_info_deadhead['post_mission']['target_range'] = [500, "nmi"] # get large single aisle values -from aviary.validation_cases.validation_tests import get_flops_inputs aviary_inputs_primary = get_flops_inputs('LargeSingleAisle2FLOPS') -aviary_inputs_primary.set_val('aircraft:crew_and_payload:design:num_passengers', 162, 'unitless') -aviary_inputs_primary.set_val('aircraft:crew_and_payload:design:num_tourist_class', 150, 'unitless') -aviary_inputs_primary.set_val('aircraft:crew_and_payload:design:num_business_class', 0, 'unitless') -aviary_inputs_primary.set_val('aircraft:crew_and_payload:design:num_first_class', 12, 'unitless') +aviary_inputs_primary.set_val( + 'aircraft:crew_and_payload:design:num_passengers', 162, 'unitless') +aviary_inputs_primary.set_val( + 'aircraft:crew_and_payload:design:num_tourist_class', 150, 'unitless') +aviary_inputs_primary.set_val( + 'aircraft:crew_and_payload:design:num_business_class', 0, 'unitless') +aviary_inputs_primary.set_val( + 'aircraft:crew_and_payload:design:num_first_class', 12, 'unitless') aviary_inputs_deadhead = copy.deepcopy(aviary_inputs_primary) aviary_inputs_deadhead.set_val('aircraft:crew_and_payload:num_passengers', 0, 'unitless') -aviary_inputs_deadhead.set_val('aircraft:crew_and_payload:num_tourist_class', 0, 'unitless') -aviary_inputs_deadhead.set_val('aircraft:crew_and_payload:num_business_class', 0, 'unitless') -aviary_inputs_deadhead.set_val('aircraft:crew_and_payload:num_first_class', 0, 'unitless') +aviary_inputs_deadhead.set_val( + 'aircraft:crew_and_payload:num_tourist_class', 0, 'unitless') +aviary_inputs_deadhead.set_val( + 'aircraft:crew_and_payload:num_business_class', 0, 'unitless') +aviary_inputs_deadhead.set_val( + 'aircraft:crew_and_payload:num_first_class', 0, 'unitless') aviary_inputs_deadhead.set_val(Aircraft.CrewPayload.MISC_CARGO, 0.0, 'lbm') -#phase_info_deadhead['post_mission']['target_range'] = [1500, "nmi"] +# phase_info_deadhead['post_mission']['target_range'] = [1500, "nmi"] + class MultiMissionProblem(om.Problem): def __init__(self, aviary_values, phase_infos, weights): @@ -159,7 +168,7 @@ def get_design_range(self): ['target_range'][0]) # TBD add units design_range_min = np.min(design_range) design_range_max = np.max(design_range) - return design_range_max, design_range_min # design_range_min + return design_range_max, design_range_min # design_range_min def create_timeseries_plots(self, plotvars=[], show=True): """ @@ -228,7 +237,7 @@ def print_vars(self, vars=[]): print(f"{name:^30}", end='| ') print() for var, unit in vars: - varname = f"Variable: {var.replace(':','.').upper()}" + varname = f"Variable: {var.replace(':', '.').upper()}" print(f"{varname:40}", end=": ") for i in range(self.num_missions): val = self.get_val(f'group_{i}.{var}', units=unit)[0] @@ -238,8 +247,8 @@ def print_vars(self, vars=[]): def large_single_aisle_example(makeN2=False): - aviary_values=[aviary_inputs_primary, - aviary_inputs_deadhead] + aviary_values = [aviary_inputs_primary, + aviary_inputs_deadhead] phase_infos = [phase_info_primary, phase_info_deadhead] optalt, optmach = False, False @@ -268,11 +277,12 @@ def large_single_aisle_example(makeN2=False): # TODO: Not sure we need this at all. from openmdao.api import n2 from os.path import basename, dirname, join, abspath + def createN2(fileref, prob): n2folder = join(dirname(abspath(__file__)), "N2s") n2(prob, outfile=join(n2folder, - f"n2_{basename(fileref).split('.')[0]}.html")) - + f"n2_{basename(fileref).split('.')[0]}.html")) + createN2(__file__, super_prob) super_prob.run() @@ -311,6 +321,6 @@ def createN2(fileref, prob): makeN2 = True if (len(sys.argv) > 1 and "n2" in sys.argv[1]) else False super_prob = large_single_aisle_example(makeN2=makeN2) - + # super_prob.model.group_1.list_vars(val=True, units=True, print_arrays=False) # https://openmdao.org/newdocs/versions/latest/features/debugging/listing_variables.html?highlight=list_driver_vars diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index f463b79fb..5bd2e1d69 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -474,7 +474,8 @@ def check_and_preprocess_inputs(self): "target_duration"] if target_duration[0] <= 0: raise ValueError( - f"Invalid target_duration in phase_info[{phase_name}][user_options]. " + f"Invalid target_duration in phase_info" + f"[{phase_name}][user_options]. " f"Current (value: {target_duration[0]}), (units: {target_duration[1]}) <= 0") # Only applies to non-analytic phases (all HE and most 2DOF) @@ -2187,7 +2188,8 @@ def _add_guesses(self, phase_name, phase, guesses, setvalprob, parent_prefix): units=units) except KeyError: setvalprob.set_val(parent_prefix + - f'traj.{phase_name}.bspline_controls:{guess_key}', + f'traj.{phase_name}.bspline_controls:', + {guess_key}, self._process_guess_var( val, guess_key, phase), units=units) diff --git a/aviary/utils/preprocessors.py b/aviary/utils/preprocessors.py index fb5dd26ff..5d9e8fa0c 100644 --- a/aviary/utils/preprocessors.py +++ b/aviary/utils/preprocessors.py @@ -35,35 +35,64 @@ def preprocess_crewpayload(aviary_options: AviaryValues): returns the modified collection. """ - if Aircraft.CrewPayload.NUM_PASSENGERS not in aviary_options: - if Aircraft.CrewPayload.Design.NUM_PASSENGERS in aviary_options: - # Set the num_passengers to the designed number of passengers - passenger_count = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) - else: - # sum up the number of passengers - passenger_count = 0 - for key in (Aircraft.CrewPayload.NUM_FIRST_CLASS, - Aircraft.CrewPayload.NUM_BUSINESS_CLASS, - Aircraft.CrewPayload.NUM_TOURIST_CLASS): - if key in aviary_options: - passenger_count += aviary_options.get_val(key) - if passenger_count == 0: - passenger_count = 1 - + # If Design.Num_Passenger values are left blank (as they are in all pre- 9/18/2024 examples), + # then set Design.Num_Passenger to Num_Passenger + + # If individual passenger numbers are set but not totals, sum them up to find the total + + # CHeck if total = individual passenger counts + + # If Design.Num_Passengers < Num_Passengers warn and exit? + + # sum up the number of passengers if they were defined individually + passenger_count = 0 + design_passenger_count = 0 + for key in (Aircraft.CrewPayload.NUM_FIRST_CLASS, + Aircraft.CrewPayload.NUM_BUSINESS_CLASS, + Aircraft.CrewPayload.NUM_TOURIST_CLASS): + if key in aviary_options: + passenger_count += aviary_options.get_val(key) + for key in (Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, + Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, + Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS): + if key in aviary_options: + design_passenger_count += aviary_options.get_val(key) + + # check if passenger_count = num_passengers, otherwise set num_passengers + if Aircraft.CrewPayload.NUM_PASSENGERS in aviary_options: + if passenger_count != aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS): + raise om.AnalysisError( + f"ERROR: In preprocesssors.py: NUM_PASSENGERS ({Aircraft.CrewPayload.NUM_PASSENGERS}) does not equal the sum of first class + business class + tourist class passengers (total of {passenger_count}).") + else: aviary_options.set_val( Aircraft.CrewPayload.NUM_PASSENGERS, passenger_count) - else: - passenger_count = aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS) - # check in here to ensure that in this case passenger count is the sum of the first class, business class, and tourist class counts. - passenger_check = aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS) - passenger_check += aviary_options.get_val( - Aircraft.CrewPayload.NUM_BUSINESS_CLASS) - passenger_check += aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS) - # only perform check if at least one passenger class is entered - if passenger_check > 0 and passenger_count != passenger_check: + + # check if design_passenger_count = design.num_passengers, otherwise set design.num_passengers + if Aircraft.CrewPayload.Design.NUM_PASSENGERS in aviary_options: + if design_passenger_count != aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS): raise om.AnalysisError( - f"ERROR: In preprocesssors.py: passenger_count ({passenger_count}) does not equal the sum of first class + business class + tourist class passengers (total of {passenger_check}).") + f"ERROR: In preprocesssors.py: Design.NUM_PASSENGERS ({Aircraft.CrewPayload.Design.NUM_PASSENGERS}) does not equal the sum of Design [first class + business class + tourist class] passengers (total of {design_passenger_count}).") + else: + # Design.NUM_PASSENGERS has not been set + if design_passenger_count > 0: + # a design passenger number for business / tourist / first class was set + aviary_options.set_val( + Aircraft.CrewPayload.Design.NUM_PASSENGERS, design_passenger_count) + else: + # no design passenger values were set, assume design is same as num_passengers + aviary_options.set_val( + Aircraft.CrewPayload.Design.NUM_PASSENGERS, aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)) + aviary_options.set_val( + Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS)) + aviary_options.set_val( + Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, aviary_options.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS)) + aviary_options.set_val( + Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS)) + + # check if NUM_PASSENGERS > DESIGN.NUM_PASSENGERS + if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS): + raise om.AnalysisError( + f"ERROR: In preprocesssors.py: Design.NUM_PASSENGERS ({Aircraft.CrewPayload.Design.NUM_PASSENGERS}) is less than NUM_PASSENGERS ({Aircraft.CrewPayload.NUM_PASSENGERS}).") if Aircraft.CrewPayload.NUM_FLIGHT_ATTENDANTS not in aviary_options: flight_attendants_count = 0 # assume no passengers From 6664fdafbc45a4f28ea020dd1b9dbe8c88d4d233 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Fri, 20 Sep 2024 15:10:01 -0400 Subject: [PATCH 065/113] big updates to preprocessor, but checks there still failing because Design.NUM_PASSENGERS is being set even when it should be set --- ...multimission_example_large_single_aisle.py | 35 ++- aviary/utils/preprocessors.py | 238 ++++++++++++++---- .../flops_data/FLOPS_Test_Data.py | 1 + aviary/variable_info/variable_meta_data.py | 2 +- 4 files changed, 213 insertions(+), 63 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py index cb6fdc058..689bac204 100644 --- a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py @@ -8,24 +8,21 @@ aircraft:crew_and_payload:num_first_class,0,unitless """ -from aviary.validation_cases.validation_tests import get_flops_inputs -from aviary.api import SubsystemBuilderBase -from aviary.subsystems.mass.flops_based.furnishings import TransportFurnishingsGroupMass -import sys -import warnings -import dymos as dm -import numpy as np -from os.path import join -import matplotlib.pyplot as plt - -import openmdao.api as om -import aviary.api as av -from aviary.variable_info.enums import ProblemType -from aviary.variable_info.variables import Mission, Aircraft - - -from aviary.examples.example_phase_info import phase_info import copy as copy +from aviary.examples.example_phase_info import phase_info +from aviary.variable_info.variables import Mission, Aircraft +from aviary.variable_info.enums import ProblemType +import aviary.api as av +import openmdao.api as om +import matplotlib.pyplot as plt +from os.path import join +import numpy as np +import dymos as dm +import warnings +import sys +from aviary.subsystems.mass.flops_based.furnishings import TransportFurnishingsGroupMass +from aviary.api import SubsystemBuilderBase +from aviary.validation_cases.validation_tests import get_flops_inputs # fly the same mission twice with two different passenger loads phase_info_primary = copy.deepcopy(phase_info) @@ -35,7 +32,7 @@ # get large single aisle values aviary_inputs_primary = get_flops_inputs('LargeSingleAisle2FLOPS') aviary_inputs_primary.set_val( - 'aircraft:crew_and_payload:design:num_passengers', 162, 'unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, 162, 'unitless') aviary_inputs_primary.set_val( 'aircraft:crew_and_payload:design:num_tourist_class', 150, 'unitless') aviary_inputs_primary.set_val( @@ -43,7 +40,6 @@ aviary_inputs_primary.set_val( 'aircraft:crew_and_payload:design:num_first_class', 12, 'unitless') - aviary_inputs_deadhead = copy.deepcopy(aviary_inputs_primary) aviary_inputs_deadhead.set_val('aircraft:crew_and_payload:num_passengers', 0, 'unitless') aviary_inputs_deadhead.set_val( @@ -54,6 +50,7 @@ 'aircraft:crew_and_payload:num_first_class', 0, 'unitless') aviary_inputs_deadhead.set_val(Aircraft.CrewPayload.MISC_CARGO, 0.0, 'lbm') + # phase_info_deadhead['post_mission']['target_range'] = [1500, "nmi"] diff --git a/aviary/utils/preprocessors.py b/aviary/utils/preprocessors.py index 5d9e8fa0c..de43c09cf 100644 --- a/aviary/utils/preprocessors.py +++ b/aviary/utils/preprocessors.py @@ -8,6 +8,7 @@ from aviary.variable_info.variable_meta_data import _MetaData from aviary.variable_info.variables import Aircraft, Mission from aviary.utils.test_utils.variable_test import get_names_from_hierarchy +from aviary.variable_info.variable_meta_data import _MetaData as BaseMetaData def preprocess_options(aviary_options: AviaryValues, **kwargs): @@ -35,64 +36,215 @@ def preprocess_crewpayload(aviary_options: AviaryValues): returns the modified collection. """ - # If Design.Num_Passenger values are left blank (as they are in all pre- 9/18/2024 examples), - # then set Design.Num_Passenger to Num_Passenger + # Check which values were received from user input + user_input_num_pax = False + user_input_design_num_pax = False + user_input_1TB = False + user_input_design_1TB = False - # If individual passenger numbers are set but not totals, sum them up to find the total - - # CHeck if total = individual passenger counts - - # If Design.Num_Passengers < Num_Passengers warn and exit? - - # sum up the number of passengers if they were defined individually + if Aircraft.CrewPayload.NUM_PASSENGERS in aviary_options: + user_input_num_pax = True + print('NUM_PASSENGERS', aviary_options.get_val( + Aircraft.CrewPayload.NUM_PASSENGERS)) + if Aircraft.CrewPayload.Design.NUM_PASSENGERS in aviary_options: + user_input_design_num_pax = True + print('Design.NUM_PASSENGERS', aviary_options.get_val( + Aircraft.CrewPayload.Design.NUM_PASSENGERS)) + if Aircraft.CrewPayload.NUM_FIRST_CLASS in aviary_options or \ + Aircraft.CrewPayload.NUM_BUSINESS_CLASS in aviary_options or \ + Aircraft.CrewPayload.NUM_TOURIST_CLASS in aviary_options: + user_input_1TB = True + if Aircraft.CrewPayload.Design.NUM_FIRST_CLASS in aviary_options or \ + Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS in aviary_options or \ + Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS in aviary_options: + user_input_design_1TB = True + + print('user_input_num_pax', user_input_num_pax) + print('user_input_design_num_pax', user_input_design_num_pax) + print('user_input_1TB', user_input_1TB) + print('user_input_design_1TB', user_input_design_1TB) + + # Grab Default values for 1TB (1st class, Tourist Class, Business Class Passengers) to make + # sure they are accessible so we don't have to run checks if they exist again + if user_input_1TB: + if Aircraft.CrewPayload.NUM_FIRST_CLASS not in aviary_options: + aviary_options.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, + BaseMetaData[Aircraft.CrewPayload.NUM_FIRST_CLASS]['default_value']) + if Aircraft.CrewPayload.NUM_BUSINESS_CLASS not in aviary_options: + aviary_options.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, + BaseMetaData[Aircraft.CrewPayload.NUM_BUSINESS_CLASS]['default_value']) + if Aircraft.CrewPayload.NUM_TOURIST_CLASS not in aviary_options: + aviary_options.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, + BaseMetaData[Aircraft.CrewPayload.NUM_TOURIST_CLASS]['default_value']) + if user_input_design_1TB: + if Aircraft.CrewPayload.Design.NUM_FIRST_CLASS not in aviary_options: + aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, + BaseMetaData[Aircraft.CrewPayload.Design.NUM_FIRST_CLASS]['default_value']) + if Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS not in aviary_options: + aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, + BaseMetaData[Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS]['default_value']) + if Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS not in aviary_options: + aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, + BaseMetaData[Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS]['default_value']) + + # Sum passenger Counts for later checks and assignments passenger_count = 0 - design_passenger_count = 0 for key in (Aircraft.CrewPayload.NUM_FIRST_CLASS, Aircraft.CrewPayload.NUM_BUSINESS_CLASS, Aircraft.CrewPayload.NUM_TOURIST_CLASS): if key in aviary_options: passenger_count += aviary_options.get_val(key) + design_passenger_count = 0 for key in (Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS): if key in aviary_options: design_passenger_count += aviary_options.get_val(key) - # check if passenger_count = num_passengers, otherwise set num_passengers - if Aircraft.CrewPayload.NUM_PASSENGERS in aviary_options: - if passenger_count != aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS): - raise om.AnalysisError( - f"ERROR: In preprocesssors.py: NUM_PASSENGERS ({Aircraft.CrewPayload.NUM_PASSENGERS}) does not equal the sum of first class + business class + tourist class passengers (total of {passenger_count}).") - else: + # Create summary data if it was not assigned by the user originally + if user_input_num_pax is False and user_input_1TB is True: + aviary_options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, passenger_count) + user_input_num_pax = True + if user_input_design_1TB and not user_input_design_num_pax: + print('setting Design.NUM_PASSENGERS') aviary_options.set_val( - Aircraft.CrewPayload.NUM_PASSENGERS, passenger_count) + Aircraft.CrewPayload.Design.NUM_PASSENGERS, design_passenger_count) + user_input_design_num_pax = True - # check if design_passenger_count = design.num_passengers, otherwise set design.num_passengers - if Aircraft.CrewPayload.Design.NUM_PASSENGERS in aviary_options: - if design_passenger_count != aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS): - raise om.AnalysisError( - f"ERROR: In preprocesssors.py: Design.NUM_PASSENGERS ({Aircraft.CrewPayload.Design.NUM_PASSENGERS}) does not equal the sum of Design [first class + business class + tourist class] passengers (total of {design_passenger_count}).") - else: - # Design.NUM_PASSENGERS has not been set - if design_passenger_count > 0: - # a design passenger number for business / tourist / first class was set - aviary_options.set_val( - Aircraft.CrewPayload.Design.NUM_PASSENGERS, design_passenger_count) - else: - # no design passenger values were set, assume design is same as num_passengers - aviary_options.set_val( - Aircraft.CrewPayload.Design.NUM_PASSENGERS, aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)) - aviary_options.set_val( - Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS)) - aviary_options.set_val( - Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, aviary_options.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS)) - aviary_options.set_val( - Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS)) - - # check if NUM_PASSENGERS > DESIGN.NUM_PASSENGERS - if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS): + # Fail if incorrect data sets were provided: + if user_input_num_pax and user_input_design_1TB and not user_input_1TB: + raise om.AnalysisError( + f"ERROR: In preprocessor.py: User must specify CrewPayload.FIRST_CLASS, CrewPayload.NUM_BUSINESS_CLASS, Design.NUM_TOURIST_CLASS in aviary_values.") + if user_input_design_num_pax and user_input_1TB and not user_input_design_1TB: + raise om.AnalysisError( + f"ERROR: In preprocessor.py: User must specify Design.FIRST_CLASS, Design.NUM_BUSINESS_CLASS, Design.NUM_TOURIST_CLASS in aviary_values.") + + # Check summary data against individual data if individual data was entered + if user_input_1TB is True and aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) != passenger_count: raise om.AnalysisError( - f"ERROR: In preprocesssors.py: Design.NUM_PASSENGERS ({Aircraft.CrewPayload.Design.NUM_PASSENGERS}) is less than NUM_PASSENGERS ({Aircraft.CrewPayload.NUM_PASSENGERS}).") + f"ERROR: In preprocesssors.py: NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)}) does not equal the sum of first class + business class + tourist class passengers (total of {passenger_count}).") + if user_input_design_1TB is True and aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) != design_passenger_count: + raise om.AnalysisError( + f"ERROR: In preprocesssors.py: Design.NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS)}) does not equal the sum of design first class + business class + tourist class passengers (total of {design_passenger_count}).") + + # Copy data over if only one set of data exists + if user_input_1TB and not (user_input_design_num_pax and user_input_design_1TB): + aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, + aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS)) + aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, + aviary_options.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS)) + aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, + aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS)) + user_input_design_1TB = True + if user_input_num_pax and not user_input_design_num_pax: + aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)) + user_input_design_num_pax = True + if user_input_design_1TB and not (user_input_num_pax and user_input_1TB): + aviary_options.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, aviary_options.get_val( + Aircraft.CrewPayload.Design.NUM_FIRST_CLASS)) + aviary_options.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, aviary_options.get_val( + Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS)) + aviary_options.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, aviary_options.get_val( + Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS)) + user_input_1TB = True + if user_input_design_num_pax and not user_input_num_pax: + aviary_options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, aviary_options.get_val( + Aircraft.CrewPayload.Design.NUM_PASSENGERS)) + user_input_num_pax = True + + # Performe checks on the final data tables to ensure data is accurate + if user_input_design_num_pax and user_input_num_pax: + if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS): + raise om.AnalysisError( + f"ERROR: In preprocesssors.py: NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)}) is larger than the number of seats set by Design.NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS)}) .") + if user_input_1TB and user_input_design_1TB: + if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS): + raise om.AnalysisError( + f"ERROR: In preprocesssors.py: NUM_FIRST_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS)}) is larger than the number of seats set by Design.NUM_FIRST_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS)}) .") + if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS): + raise om.AnalysisError( + f"ERROR: In preprocesssors.py: NUM_BUSINESS_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS)}) is larger than the number of seats set by Design.NUM_BUSINESS_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS)}) .") + if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS): + raise om.AnalysisError( + f"ERROR: In preprocesssors.py: NUM_TOURIST_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS)}) is larger than the number of seats set by Design.NUM_TOURIST_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS)}) .") + + # fail + + # # Assign NUM_Passengers if it's not assigned + # if Aircraft.CrewPayload.NUM_PASSENGERS not in aviary_options: + # aviary_options.set_val( + # Aircraft.CrewPayload.NUM_PASSENGERS, passenger_count) + # else: + # # we only do this if the values don't match AND at least one of the first/buisness/tourist passenger counts has been set + # if passenger_count > 0 and aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) != passenger_count: + # raise om.AnalysisError( + # f"ERROR: In preprocesssors.py: NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)}) does not equal the sum of first class + business class + tourist class passengers (total of {passenger_count}).") + + # # Check if any Design.NUM_ values exist, if non of them exist, assign all values + # # if any of them do exist, don't over-write anything + # if Aircraft.CrewPayload.Design.NUM_PASSENGERS not in aviary_options and \ + # Aircraft.CrewPayload.Design.NUM_FIRST_CLASS not in aviary_options and \ + # Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS not in aviary_options and \ + # Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS not in aviary_options: + # for key in ([Aircraft.CrewPayload.NUM_PASSENGERS, Aircraft.CrewPayload.Design.NUM_PASSENGERS], + # [Aircraft.CrewPayload.NUM_FIRST_CLASS, + # Aircraft.CrewPayload.Design.NUM_FIRST_CLASS], + # [Aircraft.CrewPayload.NUM_BUSINESS_CLASS, + # Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS], + # [Aircraft.CrewPayload.NUM_TOURIST_CLASS, Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS]): + # if key[0] in aviary_options: + # aviary_options.set_val( + # key[1], aviary_options.get_val(key[0])) + + # # if the user has specified Design.NUM_ + # if Aircraft.CrewPayload.NUM_PASSENGERS not in aviary_options and \ + # Aircraft.CrewPayload.NUM_FIRST_CLASS not in aviary_options and \ + # Aircraft.CrewPayload.NUM_BUSINESS_CLASS not in aviary_options and \ + # Aircraft.CrewPayload.NUM_TOURIST_CLASS not in aviary_options: + # for key in ([Aircraft.CrewPayload.NUM_PASSENGERS, Aircraft.CrewPayload.Design.NUM_PASSENGERS], + # [Aircraft.CrewPayload.NUM_FIRST_CLASS, + # Aircraft.CrewPayload.Design.NUM_FIRST_CLASS], + # [Aircraft.CrewPayload.NUM_BUSINESS_CLASS, + # Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS], + # [Aircraft.CrewPayload.NUM_TOURIST_CLASS, Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS]): + # if key[1] in aviary_options: + # aviary_options.set_val( + # key[0], aviary_options.get_val(key[1])) + + # # Assign Design.NUM_Passengers if it hasn't been set yet + # if Aircraft.CrewPayload.Design.NUM_PASSENGERS not in aviary_options: + # aviary_options.set_val( + # Aircraft.CrewPayload.NUM_PASSENGERS, design_passenger_count) + # else: + # # we only do this if the values don't match AND at least one of the first/buisness/tourist passenger counts has been set + # if design_passenger_count > 0 and aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) != design_passenger_count: + # raise om.AnalysisError( + # f"ERROR: In preprocesssors.py: Design.NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS)}) does not equal the sum of design first class + business class + tourist class passengers (total of {design_passenger_count}).") + + # # Check the individual seat assignments if they exist and error if more passengers have been assigned to that group than seats: + # if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS): + # raise om.AnalysisError( + # f"ERROR: In preprocessor.py: More passengers assigned to aircraft than seats. Design.NUM_PASSENGERS < NUM_PASSENGERS." + # ) + + # if Aircraft.CrewPayload.Design.NUM_FIRST_CLASS in aviary_options and Aircraft.CrewPayload.NUM_FIRST_CLASS in aviary_options: + # if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS): + # raise om.AnalysisError( + # f"ERROR: In preprocessor.py: More passengers assigned to first class than seats. Design.NUM_FIRST_CLASS < NUM_FIRST_CLASS." + # ) + + # if Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS in aviary_options and Aircraft.CrewPayload.NUM_BUSINESS_CLASS in aviary_options: + # if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS): + # raise om.AnalysisError( + # f"ERROR: In preprocessor.py: More passengers assigned to business class than seats. Design.NUM_BUSINESS_CLASS < NUM_BUSINESS_CLASS." + # ) + + # if Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS in aviary_options and Aircraft.CrewPayload.NUM_TOURIST_CLASS in aviary_options: + # if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS): + # raise om.AnalysisError( + # f"ERROR: In preprocessor.py: More passengers assigned to tourist class than seats. Design.NUM_TOURIST_CLASS < NUM_TOURIST_CLASS." + # ) if Aircraft.CrewPayload.NUM_FLIGHT_ATTENDANTS not in aviary_options: flight_attendants_count = 0 # assume no passengers @@ -154,7 +306,7 @@ def preprocess_propulsion(aviary_options: AviaryValues, engine_models: list = No Performs basic sanity checks on inputs that are universal to all EngineModels. !!! WARNING !!! - Values in aviary_options can be overwritten with corresponding values from + Values in aviary_options can be overwritten with corresponding values from engine_models! Parameters diff --git a/aviary/validation_cases/validation_data/flops_data/FLOPS_Test_Data.py b/aviary/validation_cases/validation_data/flops_data/FLOPS_Test_Data.py index 94e0388e6..fc2c906b5 100644 --- a/aviary/validation_cases/validation_data/flops_data/FLOPS_Test_Data.py +++ b/aviary/validation_cases/validation_data/flops_data/FLOPS_Test_Data.py @@ -16,6 +16,7 @@ FLOPS_Test_Data['LargeSingleAisle2FLOPS'] = LargeSingleAisle2FLOPS FLOPS_Test_Data['LargeSingleAisle2FLOPSdw'] = LargeSingleAisle2FLOPSdw FLOPS_Test_Data['LargeSingleAisle2FLOPSalt'] = LargeSingleAisle2FLOPSalt +# when importing get_flops_inputs(), this is the data file that is loaded as the default aviary_values FLOPS_Test_Data['N3CC'] = N3CC # We don't have full date for this yet, but might still want to run one in a single unit test. diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index c7bf11128..30bd3ad02 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -632,7 +632,7 @@ desc='number of business class passengers that the aircraft is designed to accommodate', types=int, option=True, - default_value=0, #AviaryValues.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS), + default_value=0, # AviaryValues.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS), ) add_meta_data( From dcbab17be410c9581fb1448412073c42d30e8a35 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Fri, 20 Sep 2024 16:21:40 -0400 Subject: [PATCH 066/113] preprocessor.py modified to work even if user inputs 0 value for num_pax and design.num_pax but the uder inputs values for num_businesclass/first/tourist or num_design(business/first/tourist). we assume the the zero on num_pax was set by default as we cant tell the difference between that and user input someimtes --- aviary/utils/preprocessors.py | 13 +++++-------- 1 file changed, 5 insertions(+), 8 deletions(-) diff --git a/aviary/utils/preprocessors.py b/aviary/utils/preprocessors.py index de43c09cf..e74b94744 100644 --- a/aviary/utils/preprocessors.py +++ b/aviary/utils/preprocessors.py @@ -59,11 +59,6 @@ def preprocess_crewpayload(aviary_options: AviaryValues): Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS in aviary_options: user_input_design_1TB = True - print('user_input_num_pax', user_input_num_pax) - print('user_input_design_num_pax', user_input_design_num_pax) - print('user_input_1TB', user_input_1TB) - print('user_input_design_1TB', user_input_design_1TB) - # Grab Default values for 1TB (1st class, Tourist Class, Business Class Passengers) to make # sure they are accessible so we don't have to run checks if they exist again if user_input_1TB: @@ -102,11 +97,13 @@ def preprocess_crewpayload(aviary_options: AviaryValues): design_passenger_count += aviary_options.get_val(key) # Create summary data if it was not assigned by the user originally - if user_input_num_pax is False and user_input_1TB is True: + # or if it was left or set to it's default value of zero + if user_input_num_pax is False and user_input_1TB is True or \ + user_input_num_pax and aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) == 0: aviary_options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, passenger_count) user_input_num_pax = True - if user_input_design_1TB and not user_input_design_num_pax: - print('setting Design.NUM_PASSENGERS') + if user_input_design_1TB and not user_input_design_num_pax or \ + user_input_design_num_pax and aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) == 0: aviary_options.set_val( Aircraft.CrewPayload.Design.NUM_PASSENGERS, design_passenger_count) user_input_design_num_pax = True From c031abaa7c639ca72233b8ddcd9120299b5b33ea Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Mon, 23 Sep 2024 17:09:03 -0400 Subject: [PATCH 067/113] Modified pre processor with Chris Bennett to correctly capture and report all error cases and give user input as to what data was being filled in from as-flow vs. design --- ...multimission_example_large_single_aisle.py | 2 +- aviary/utils/preprocessors.py | 251 ++++++------------ 2 files changed, 76 insertions(+), 177 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py index 689bac204..5cc253dbb 100644 --- a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py @@ -23,7 +23,7 @@ from aviary.subsystems.mass.flops_based.furnishings import TransportFurnishingsGroupMass from aviary.api import SubsystemBuilderBase from aviary.validation_cases.validation_tests import get_flops_inputs - +print("========== Starting Run ===============") # fly the same mission twice with two different passenger loads phase_info_primary = copy.deepcopy(phase_info) phase_info_deadhead = copy.deepcopy(phase_info) diff --git a/aviary/utils/preprocessors.py b/aviary/utils/preprocessors.py index e74b94744..0bbb03281 100644 --- a/aviary/utils/preprocessors.py +++ b/aviary/utils/preprocessors.py @@ -36,212 +36,111 @@ def preprocess_crewpayload(aviary_options: AviaryValues): returns the modified collection. """ - # Check which values were received from user input - user_input_num_pax = False - user_input_design_num_pax = False - user_input_1TB = False - user_input_design_1TB = False - - if Aircraft.CrewPayload.NUM_PASSENGERS in aviary_options: - user_input_num_pax = True - print('NUM_PASSENGERS', aviary_options.get_val( - Aircraft.CrewPayload.NUM_PASSENGERS)) - if Aircraft.CrewPayload.Design.NUM_PASSENGERS in aviary_options: - user_input_design_num_pax = True - print('Design.NUM_PASSENGERS', aviary_options.get_val( - Aircraft.CrewPayload.Design.NUM_PASSENGERS)) - if Aircraft.CrewPayload.NUM_FIRST_CLASS in aviary_options or \ - Aircraft.CrewPayload.NUM_BUSINESS_CLASS in aviary_options or \ - Aircraft.CrewPayload.NUM_TOURIST_CLASS in aviary_options: - user_input_1TB = True - if Aircraft.CrewPayload.Design.NUM_FIRST_CLASS in aviary_options or \ - Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS in aviary_options or \ - Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS in aviary_options: - user_input_design_1TB = True - - # Grab Default values for 1TB (1st class, Tourist Class, Business Class Passengers) to make + # Grab Default all values for num_pax and 1TB (1st class, Tourist Class, Business Class Passengers) to make # sure they are accessible so we don't have to run checks if they exist again - if user_input_1TB: - if Aircraft.CrewPayload.NUM_FIRST_CLASS not in aviary_options: - aviary_options.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, - BaseMetaData[Aircraft.CrewPayload.NUM_FIRST_CLASS]['default_value']) - if Aircraft.CrewPayload.NUM_BUSINESS_CLASS not in aviary_options: - aviary_options.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, - BaseMetaData[Aircraft.CrewPayload.NUM_BUSINESS_CLASS]['default_value']) - if Aircraft.CrewPayload.NUM_TOURIST_CLASS not in aviary_options: - aviary_options.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, - BaseMetaData[Aircraft.CrewPayload.NUM_TOURIST_CLASS]['default_value']) - if user_input_design_1TB: - if Aircraft.CrewPayload.Design.NUM_FIRST_CLASS not in aviary_options: - aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, - BaseMetaData[Aircraft.CrewPayload.Design.NUM_FIRST_CLASS]['default_value']) - if Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS not in aviary_options: - aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, - BaseMetaData[Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS]['default_value']) - if Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS not in aviary_options: - aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, - BaseMetaData[Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS]['default_value']) + for key in ( + Aircraft.CrewPayload.NUM_PASSENGERS, + Aircraft.CrewPayload.NUM_FIRST_CLASS, + Aircraft.CrewPayload.NUM_BUSINESS_CLASS, + Aircraft.CrewPayload.NUM_TOURIST_CLASS, + Aircraft.CrewPayload.Design.NUM_PASSENGERS, + Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, + Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, + Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS,): + if key not in aviary_options: + aviary_options.set_val(key, BaseMetaData[key]['default_value']) # Sum passenger Counts for later checks and assignments passenger_count = 0 for key in (Aircraft.CrewPayload.NUM_FIRST_CLASS, Aircraft.CrewPayload.NUM_BUSINESS_CLASS, Aircraft.CrewPayload.NUM_TOURIST_CLASS): - if key in aviary_options: - passenger_count += aviary_options.get_val(key) + passenger_count += aviary_options.get_val(key) design_passenger_count = 0 for key in (Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS): - if key in aviary_options: - design_passenger_count += aviary_options.get_val(key) + design_passenger_count += aviary_options.get_val(key) - # Create summary data if it was not assigned by the user originally - # or if it was left or set to it's default value of zero - if user_input_num_pax is False and user_input_1TB is True or \ - user_input_num_pax and aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) == 0: + # Create summary value (num_pax) if it was not assigned by the user + # or if it was set to it's default value of zero + if passenger_count != 0 and aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) == 0: aviary_options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, passenger_count) - user_input_num_pax = True - if user_input_design_1TB and not user_input_design_num_pax or \ - user_input_design_num_pax and aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) == 0: + print("User has specified supporting values for num_pax but has left num_pax blank or zero. Replacing num_pax with passenger_count.") + if design_passenger_count != 0 and aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) == 0: aviary_options.set_val( Aircraft.CrewPayload.Design.NUM_PASSENGERS, design_passenger_count) - user_input_design_num_pax = True + print("User has specified supporting values for design.num_pax but has left design.num_pax blank or zero. Replacing design.num_pax with design_passenger_count.") - # Fail if incorrect data sets were provided: - if user_input_num_pax and user_input_design_1TB and not user_input_1TB: - raise om.AnalysisError( - f"ERROR: In preprocessor.py: User must specify CrewPayload.FIRST_CLASS, CrewPayload.NUM_BUSINESS_CLASS, Design.NUM_TOURIST_CLASS in aviary_values.") - if user_input_design_num_pax and user_input_1TB and not user_input_design_1TB: - raise om.AnalysisError( - f"ERROR: In preprocessor.py: User must specify Design.FIRST_CLASS, Design.NUM_BUSINESS_CLASS, Design.NUM_TOURIST_CLASS in aviary_values.") + num_pax = aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) + design_num_pax = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) # Check summary data against individual data if individual data was entered - if user_input_1TB is True and aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) != passenger_count: + if num_pax != passenger_count: raise om.AnalysisError( f"ERROR: In preprocesssors.py: NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)}) does not equal the sum of first class + business class + tourist class passengers (total of {passenger_count}).") - if user_input_design_1TB is True and aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) != design_passenger_count: + if design_num_pax != design_passenger_count: raise om.AnalysisError( f"ERROR: In preprocesssors.py: Design.NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS)}) does not equal the sum of design first class + business class + tourist class passengers (total of {design_passenger_count}).") + # Fail if incorrect data sets were provided: + # have you give us enough info to determine where people were sitting vs. designed seats + if num_pax != 0 and design_passenger_count != 0 and passenger_count == 0: + raise om.AnalysisError( + f"ERROR: In preprocessor.py: User must specify CrewPayload.FIRST_CLASS, CrewPayload.NUM_BUSINESS_CLASS, Design.NUM_TOURIST_CLASS in aviary_values.") + # where are the people sitting? is first class full? We know how many seats are in each class. + if design_num_pax != 0 and passenger_count != 0 and design_passenger_count == 0: + raise om.AnalysisError( + f"ERROR: In preprocessor.py: User must specify Design.FIRST_CLASS, Design.NUM_BUSINESS_CLASS, Design.NUM_TOURIST_CLASS in aviary_values.") + # we don't know which classes this aircraft has been design for. How many 1st class seats are there? + # Copy data over if only one set of data exists - if user_input_1TB and not (user_input_design_num_pax and user_input_design_1TB): + # User has given detailed values for 1TB as flow and NO design values at all + if passenger_count != 0 and design_num_pax == 0 and design_passenger_count == 0: + print("User has not input design data. Assume design data is equal to as-flow data user has already input") + aviary_options.set_val( + Aircraft.CrewPayload.Design.NUM_PASSENGERS, passenger_count) aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS)) aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, aviary_options.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS)) aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS)) - user_input_design_1TB = True - if user_input_num_pax and not user_input_design_num_pax: - aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, - aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)) - user_input_design_num_pax = True - if user_input_design_1TB and not (user_input_num_pax and user_input_1TB): - aviary_options.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, aviary_options.get_val( - Aircraft.CrewPayload.Design.NUM_FIRST_CLASS)) - aviary_options.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, aviary_options.get_val( - Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS)) - aviary_options.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, aviary_options.get_val( - Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS)) - user_input_1TB = True - if user_input_design_num_pax and not user_input_num_pax: - aviary_options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, aviary_options.get_val( - Aircraft.CrewPayload.Design.NUM_PASSENGERS)) - user_input_num_pax = True - - # Performe checks on the final data tables to ensure data is accurate - if user_input_design_num_pax and user_input_num_pax: - if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS): - raise om.AnalysisError( - f"ERROR: In preprocesssors.py: NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)}) is larger than the number of seats set by Design.NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS)}) .") - if user_input_1TB and user_input_design_1TB: - if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS): - raise om.AnalysisError( - f"ERROR: In preprocesssors.py: NUM_FIRST_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS)}) is larger than the number of seats set by Design.NUM_FIRST_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS)}) .") - if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS): - raise om.AnalysisError( - f"ERROR: In preprocesssors.py: NUM_BUSINESS_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS)}) is larger than the number of seats set by Design.NUM_BUSINESS_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS)}) .") - if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS): - raise om.AnalysisError( - f"ERROR: In preprocesssors.py: NUM_TOURIST_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS)}) is larger than the number of seats set by Design.NUM_TOURIST_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS)}) .") - - # fail - - # # Assign NUM_Passengers if it's not assigned - # if Aircraft.CrewPayload.NUM_PASSENGERS not in aviary_options: - # aviary_options.set_val( - # Aircraft.CrewPayload.NUM_PASSENGERS, passenger_count) - # else: - # # we only do this if the values don't match AND at least one of the first/buisness/tourist passenger counts has been set - # if passenger_count > 0 and aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) != passenger_count: - # raise om.AnalysisError( - # f"ERROR: In preprocesssors.py: NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)}) does not equal the sum of first class + business class + tourist class passengers (total of {passenger_count}).") - - # # Check if any Design.NUM_ values exist, if non of them exist, assign all values - # # if any of them do exist, don't over-write anything - # if Aircraft.CrewPayload.Design.NUM_PASSENGERS not in aviary_options and \ - # Aircraft.CrewPayload.Design.NUM_FIRST_CLASS not in aviary_options and \ - # Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS not in aviary_options and \ - # Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS not in aviary_options: - # for key in ([Aircraft.CrewPayload.NUM_PASSENGERS, Aircraft.CrewPayload.Design.NUM_PASSENGERS], - # [Aircraft.CrewPayload.NUM_FIRST_CLASS, - # Aircraft.CrewPayload.Design.NUM_FIRST_CLASS], - # [Aircraft.CrewPayload.NUM_BUSINESS_CLASS, - # Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS], - # [Aircraft.CrewPayload.NUM_TOURIST_CLASS, Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS]): - # if key[0] in aviary_options: - # aviary_options.set_val( - # key[1], aviary_options.get_val(key[0])) - - # # if the user has specified Design.NUM_ - # if Aircraft.CrewPayload.NUM_PASSENGERS not in aviary_options and \ - # Aircraft.CrewPayload.NUM_FIRST_CLASS not in aviary_options and \ - # Aircraft.CrewPayload.NUM_BUSINESS_CLASS not in aviary_options and \ - # Aircraft.CrewPayload.NUM_TOURIST_CLASS not in aviary_options: - # for key in ([Aircraft.CrewPayload.NUM_PASSENGERS, Aircraft.CrewPayload.Design.NUM_PASSENGERS], - # [Aircraft.CrewPayload.NUM_FIRST_CLASS, - # Aircraft.CrewPayload.Design.NUM_FIRST_CLASS], - # [Aircraft.CrewPayload.NUM_BUSINESS_CLASS, - # Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS], - # [Aircraft.CrewPayload.NUM_TOURIST_CLASS, Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS]): - # if key[1] in aviary_options: - # aviary_options.set_val( - # key[0], aviary_options.get_val(key[1])) - - # # Assign Design.NUM_Passengers if it hasn't been set yet - # if Aircraft.CrewPayload.Design.NUM_PASSENGERS not in aviary_options: - # aviary_options.set_val( - # Aircraft.CrewPayload.NUM_PASSENGERS, design_passenger_count) - # else: - # # we only do this if the values don't match AND at least one of the first/buisness/tourist passenger counts has been set - # if design_passenger_count > 0 and aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) != design_passenger_count: - # raise om.AnalysisError( - # f"ERROR: In preprocesssors.py: Design.NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS)}) does not equal the sum of design first class + business class + tourist class passengers (total of {design_passenger_count}).") - - # # Check the individual seat assignments if they exist and error if more passengers have been assigned to that group than seats: - # if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS): - # raise om.AnalysisError( - # f"ERROR: In preprocessor.py: More passengers assigned to aircraft than seats. Design.NUM_PASSENGERS < NUM_PASSENGERS." - # ) - - # if Aircraft.CrewPayload.Design.NUM_FIRST_CLASS in aviary_options and Aircraft.CrewPayload.NUM_FIRST_CLASS in aviary_options: - # if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS): - # raise om.AnalysisError( - # f"ERROR: In preprocessor.py: More passengers assigned to first class than seats. Design.NUM_FIRST_CLASS < NUM_FIRST_CLASS." - # ) - - # if Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS in aviary_options and Aircraft.CrewPayload.NUM_BUSINESS_CLASS in aviary_options: - # if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS): - # raise om.AnalysisError( - # f"ERROR: In preprocessor.py: More passengers assigned to business class than seats. Design.NUM_BUSINESS_CLASS < NUM_BUSINESS_CLASS." - # ) - - # if Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS in aviary_options and Aircraft.CrewPayload.NUM_TOURIST_CLASS in aviary_options: - # if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS): - # raise om.AnalysisError( - # f"ERROR: In preprocessor.py: More passengers assigned to tourist class than seats. Design.NUM_TOURIST_CLASS < NUM_TOURIST_CLASS." - # ) + # user has not supplied detailed information on design but has supplied summary information on passengers + elif num_pax != 0 and design_num_pax == 0: + print("User has specified summary as-flow passenger data but has not specified how many passengers the arcraft was designed for.") + aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, num_pax) + elif design_passenger_count != 0 and num_pax == 0 and passenger_count == 0: + print("User has not input as-flow data. Assume as-flow data is equal to design seating data user has already input.") + aviary_options.set_val( + Aircraft.CrewPayload.NUM_PASSENGERS, design_passenger_count) + aviary_options.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, + aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS)) + aviary_options.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, + aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS)) + aviary_options.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, + aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS)) + # user has not supplied detailed information on design but has supplied summary information on passengers + elif design_num_pax != 0 and num_pax == 0: + print("User has specified summary design passenger data but has not specified how many passengers are on the aircraft as flow.") + aviary_options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, design_num_pax) + + # Performe checks on the final data tables to ensure Design is always large then As-Flow + if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS): + raise om.AnalysisError( + f"ERROR: In preprocesssors.py: NUM_FIRST_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_FIRST_CLASS)}) is larger than the number of seats set by Design.NUM_FIRST_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS)}) .") + if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS): + raise om.AnalysisError( + f"ERROR: In preprocesssors.py: NUM_BUSINESS_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS)}) is larger than the number of seats set by Design.NUM_BUSINESS_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS)}) .") + if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS): + raise om.AnalysisError( + f"ERROR: In preprocesssors.py: NUM_TOURIST_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS)}) is larger than the number of seats set by Design.NUM_TOURIST_CLASS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS)}) .") + if aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) < aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS): + raise om.AnalysisError( + f"ERROR: In preprocesssors.py: NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)}) is larger than the number of seats set by Design.NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS)}) .") + + design_num_pax = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) + print(f"Aircraft has been designed for {design_num_pax} passengers.") if Aircraft.CrewPayload.NUM_FLIGHT_ATTENDANTS not in aviary_options: flight_attendants_count = 0 # assume no passengers From 663dd108ca05102f98e2f7a9afde81c3b69c1d67 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Mon, 23 Sep 2024 17:14:12 -0400 Subject: [PATCH 068/113] added shortening of preprocessor call to methods for level 2 --- aviary/interface/methods_for_level2.py | 6 ++---- 1 file changed, 2 insertions(+), 4 deletions(-) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index 3a0dde773..4381880ac 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -41,7 +41,7 @@ from aviary.subsystems.premission import CorePreMission from aviary.utils.functions import create_opts2vals, add_opts2vals, promote_aircraft_and_mission_vars, wrapped_convert_units from aviary.utils.process_input_decks import create_vehicle, update_GASP_options, initialization_guessing -from aviary.utils.preprocessors import preprocess_crewpayload +from aviary.utils.preprocessors import preprocess_options from aviary.interface.utils.check_phase_info import check_phase_info from aviary.utils.aviary_values import AviaryValues from aviary.utils.functions import convert_strings_to_data, set_value @@ -56,7 +56,6 @@ from aviary.subsystems.geometry.geometry_builder import CoreGeometryBuilder from aviary.subsystems.mass.mass_builder import CoreMassBuilder from aviary.subsystems.aerodynamics.aerodynamics_builder import CoreAerodynamicsBuilder -from aviary.utils.preprocessors import preprocess_propulsion from aviary.utils.merge_variable_metadata import merge_meta_data from aviary.interface.default_phase_info.two_dof_fiti import add_default_sgm_args @@ -503,8 +502,7 @@ def check_and_preprocess_inputs(self): # PREPROCESSORS # # Fill in anything missing in the options with computed defaults. - preprocess_propulsion(aviary_inputs, self.engine_builders) - preprocess_crewpayload(aviary_inputs) + preprocess_options(aviary_inputs, engine_models=self.engine_builders) mission_method = aviary_inputs.get_val(Settings.EQUATIONS_OF_MOTION) mass_method = aviary_inputs.get_val(Settings.MASS_METHOD) From ec003b3b375e0adcbc639da296bb99380bb2e6d2 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Tue, 24 Sep 2024 11:18:55 -0400 Subject: [PATCH 069/113] upd preprocessor INFO messages, added design. values into all FLOPS tests, target_range tweaks to methods_for_level2 --- aviary/interface/methods_for_level2.py | 7 ++++--- aviary/models/N3CC/N3CC_data.py | 13 ++++++++---- .../large_single_aisle_1_FLOPS_data.py | 11 +++++++--- .../large_single_aisle_2_FLOPS_data.py | 14 ++++++++----- .../large_single_aisle_2_altwt_FLOPS_data.py | 14 ++++++++----- ...ge_single_aisle_2_detailwing_FLOPS_data.py | 9 ++++----- .../multi_engine_single_aisle_data.py | 14 ++++++++----- aviary/utils/preprocessors.py | 20 +++++++++---------- 8 files changed, 62 insertions(+), 40 deletions(-) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index 4381880ac..fde44c227 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -370,11 +370,12 @@ def load_inputs( aviary_inputs.set_val(Mission.Summary.RANGE, wrapped_convert_units( phase_info['post_mission']['target_range'], 'NM'), units='NM') self.require_range_residual = True + self.target_range = aviary_inputs.get_val( + Mission.Summary.RANGE, units='NM') else: self.require_range_residual = False - - self.target_range = aviary_inputs.get_val( - Mission.Summary.RANGE, units='NM') + # TODO: this maybe broken? + self.target_range = aviary_inputs.get_val(Mission.Design.RANGE, units='NM') return aviary_inputs diff --git a/aviary/models/N3CC/N3CC_data.py b/aviary/models/N3CC/N3CC_data.py index 4b4d66971..cfffe854e 100644 --- a/aviary/models/N3CC/N3CC_data.py +++ b/aviary/models/N3CC/N3CC_data.py @@ -62,15 +62,20 @@ # Crew and Payload # --------------------------- +inputs.set_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, 20) +inputs.set_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, 16) +inputs.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, 154, units='unitless') +inputs.set_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, 118) +inputs.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, 20) +inputs.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, 16) +inputs.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, 154, units='unitless') +inputs.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, 118) + inputs.set_val(Aircraft.CrewPayload.BAGGAGE_MASS_PER_PASSENGER, 35.0, 'lbm') inputs.set_val(Aircraft.CrewPayload.CARGO_CONTAINER_MASS_SCALER, 0.0) inputs.set_val(Aircraft.CrewPayload.FLIGHT_CREW_MASS_SCALER, 1.0) inputs.set_val(Aircraft.CrewPayload.NON_FLIGHT_CREW_MASS_SCALER, 1.0) -inputs.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, 20) -inputs.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, 16) inputs.set_val(Aircraft.CrewPayload.MISC_CARGO, 0., 'lbm') -inputs.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, 154, units='unitless') -inputs.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, 118) inputs.set_val(Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_SCALER, 1.) inputs.set_val(Aircraft.CrewPayload.MASS_PER_PASSENGER, 165., 'lbm') inputs.set_val(Aircraft.CrewPayload.WING_CARGO, 0., 'lbm') diff --git a/aviary/models/large_single_aisle_1/large_single_aisle_1_FLOPS_data.py b/aviary/models/large_single_aisle_1/large_single_aisle_1_FLOPS_data.py index c5fd70877..9c74cfbd5 100644 --- a/aviary/models/large_single_aisle_1/large_single_aisle_1_FLOPS_data.py +++ b/aviary/models/large_single_aisle_1/large_single_aisle_1_FLOPS_data.py @@ -45,18 +45,23 @@ # Crew and Payload # --------------------------- +inputs.set_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, 0) +inputs.set_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, 11) +inputs.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, 169, units='unitless') +inputs.set_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, 158) inputs.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, 0) -inputs.set_val(Aircraft.CrewPayload.CARGO_CONTAINER_MASS_SCALER, 1.0) inputs.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, 11) +inputs.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, 169, units='unitless') +inputs.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, 158) + +inputs.set_val(Aircraft.CrewPayload.CARGO_CONTAINER_MASS_SCALER, 1.0) inputs.set_val(Aircraft.CrewPayload.NUM_FLIGHT_ATTENDANTS, 3) inputs.set_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW, 2) inputs.set_val(Aircraft.CrewPayload.FLIGHT_CREW_MASS_SCALER, 1.0) inputs.set_val(Aircraft.CrewPayload.NUM_GALLEY_CREW, 0) inputs.set_val(Aircraft.CrewPayload.MISC_CARGO, 0., 'lbm') inputs.set_val(Aircraft.CrewPayload.NON_FLIGHT_CREW_MASS_SCALER, 1.0) -inputs.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, 169, units='unitless') inputs.set_val(Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_SCALER, 1.) -inputs.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, 158) inputs.set_val(Aircraft.CrewPayload.MASS_PER_PASSENGER, 180., 'lbm') inputs.set_val(Aircraft.CrewPayload.WING_CARGO, 0., 'lbm') diff --git a/aviary/models/large_single_aisle_2/large_single_aisle_2_FLOPS_data.py b/aviary/models/large_single_aisle_2/large_single_aisle_2_FLOPS_data.py index c6c0f8e34..3787f9ddc 100644 --- a/aviary/models/large_single_aisle_2/large_single_aisle_2_FLOPS_data.py +++ b/aviary/models/large_single_aisle_2/large_single_aisle_2_FLOPS_data.py @@ -50,19 +50,23 @@ # Crew and Payload # --------------------------- -inputs.set_val(Aircraft.CrewPayload.BAGGAGE_MASS_PER_PASSENGER, 35., 'lbm') +inputs.set_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, 0) +inputs.set_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, 12) +inputs.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, 162, units='unitless') +inputs.set_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, 150) inputs.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, 0) +inputs.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, 12) +inputs.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, 162, units='unitless') +inputs.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, 150) + +inputs.set_val(Aircraft.CrewPayload.BAGGAGE_MASS_PER_PASSENGER, 35., 'lbm') inputs.set_val(Aircraft.CrewPayload.CARGO_CONTAINER_MASS_SCALER, 1.0) inputs.set_val(Aircraft.CrewPayload.NUM_FLIGHT_ATTENDANTS, 5) inputs.set_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW, 2) inputs.set_val(Aircraft.CrewPayload.FLIGHT_CREW_MASS_SCALER, 1.0) -inputs.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, 12) inputs.set_val(Aircraft.CrewPayload.NUM_GALLEY_CREW, 1) -inputs.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, 0) inputs.set_val(Aircraft.CrewPayload.MISC_CARGO, 4077., 'lbm') inputs.set_val(Aircraft.CrewPayload.NON_FLIGHT_CREW_MASS_SCALER, 1.0) -inputs.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, 150) -inputs.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, 162, units='unitless') inputs.set_val(Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_SCALER, 1.) inputs.set_val(Aircraft.CrewPayload.MASS_PER_PASSENGER, 165., 'lbm') inputs.set_val(Aircraft.CrewPayload.WING_CARGO, 0., 'lbm') diff --git a/aviary/models/large_single_aisle_2/large_single_aisle_2_altwt_FLOPS_data.py b/aviary/models/large_single_aisle_2/large_single_aisle_2_altwt_FLOPS_data.py index c08f43020..454b605f4 100644 --- a/aviary/models/large_single_aisle_2/large_single_aisle_2_altwt_FLOPS_data.py +++ b/aviary/models/large_single_aisle_2/large_single_aisle_2_altwt_FLOPS_data.py @@ -50,19 +50,23 @@ # Crew and Payload # --------------------------- -inputs.set_val(Aircraft.CrewPayload.BAGGAGE_MASS_PER_PASSENGER, 35., 'lbm') +inputs.set_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, 0) +inputs.set_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, 12) +inputs.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, 162, units='unitless') +inputs.set_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, 150) inputs.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, 0) +inputs.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, 12) +inputs.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, 162, units='unitless') +inputs.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, 150) + +inputs.set_val(Aircraft.CrewPayload.BAGGAGE_MASS_PER_PASSENGER, 35., 'lbm') inputs.set_val(Aircraft.CrewPayload.CARGO_CONTAINER_MASS_SCALER, 1.0) inputs.set_val(Aircraft.CrewPayload.NUM_FLIGHT_ATTENDANTS, 5) inputs.set_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW, 2) inputs.set_val(Aircraft.CrewPayload.FLIGHT_CREW_MASS_SCALER, 1.0) -inputs.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, 12) inputs.set_val(Aircraft.CrewPayload.NUM_GALLEY_CREW, 1) -inputs.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, 0) inputs.set_val(Aircraft.CrewPayload.MISC_CARGO, 4077., 'lbm') inputs.set_val(Aircraft.CrewPayload.NON_FLIGHT_CREW_MASS_SCALER, 1.0) -inputs.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, 150) -inputs.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, 162, units='unitless') inputs.set_val(Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_SCALER, 1.) inputs.set_val(Aircraft.CrewPayload.MASS_PER_PASSENGER, 165., 'lbm') inputs.set_val(Aircraft.CrewPayload.WING_CARGO, 0., 'lbm') diff --git a/aviary/models/large_single_aisle_2/large_single_aisle_2_detailwing_FLOPS_data.py b/aviary/models/large_single_aisle_2/large_single_aisle_2_detailwing_FLOPS_data.py index 2aca006c4..63721e4a4 100644 --- a/aviary/models/large_single_aisle_2/large_single_aisle_2_detailwing_FLOPS_data.py +++ b/aviary/models/large_single_aisle_2/large_single_aisle_2_detailwing_FLOPS_data.py @@ -46,19 +46,18 @@ # Crew and Payload # --------------------------- inputs.set_val(Aircraft.CrewPayload.BAGGAGE_MASS_PER_PASSENGER, 35., 'lbm') -inputs.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, 0) +inputs.set_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, 0) inputs.set_val(Aircraft.CrewPayload.CARGO_CONTAINER_MASS_SCALER, 1.0) inputs.set_val(Aircraft.CrewPayload.NUM_FLIGHT_ATTENDANTS, 5) inputs.set_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW, 2) inputs.set_val(Aircraft.CrewPayload.FLIGHT_CREW_MASS_SCALER, 1.0) -inputs.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, 12) +inputs.set_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, 12) inputs.set_val(Aircraft.CrewPayload.NUM_GALLEY_CREW, 1) -inputs.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, 0) inputs.set_val(Aircraft.CrewPayload.MISC_CARGO, 4077., 'lbm') inputs.set_val(Aircraft.CrewPayload.NON_FLIGHT_CREW_MASS_SCALER, 1.0) -inputs.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, 162, units='unitless') +inputs.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, 162, units='unitless') inputs.set_val(Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_SCALER, 1.) -inputs.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, 150) +inputs.set_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, 150) inputs.set_val(Aircraft.CrewPayload.MASS_PER_PASSENGER, 165., 'lbm') inputs.set_val(Aircraft.CrewPayload.WING_CARGO, 0., 'lbm') diff --git a/aviary/models/multi_engine_single_aisle/multi_engine_single_aisle_data.py b/aviary/models/multi_engine_single_aisle/multi_engine_single_aisle_data.py index 000d8098e..0ff0dc67a 100644 --- a/aviary/models/multi_engine_single_aisle/multi_engine_single_aisle_data.py +++ b/aviary/models/multi_engine_single_aisle/multi_engine_single_aisle_data.py @@ -45,20 +45,24 @@ # Crew and Payload # --------------------------- -inputs.set_val(Aircraft.CrewPayload.BAGGAGE_MASS_PER_PASSENGER, 35., 'lbm') +inputs.set_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, 0) +inputs.set_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, 12) +inputs.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, 162, units='unitless') +inputs.set_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, 150) inputs.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, 0) +inputs.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, 12) +inputs.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, 162, units='unitless') +inputs.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, 150) + +inputs.set_val(Aircraft.CrewPayload.BAGGAGE_MASS_PER_PASSENGER, 35., 'lbm') inputs.set_val(Aircraft.CrewPayload.CARGO_CONTAINER_MASS_SCALER, 1.0) inputs.set_val(Aircraft.CrewPayload.NUM_FLIGHT_ATTENDANTS, 5) inputs.set_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW, 2) inputs.set_val(Aircraft.CrewPayload.FLIGHT_CREW_MASS_SCALER, 1.0) -inputs.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, 12) inputs.set_val(Aircraft.CrewPayload.NUM_GALLEY_CREW, 1) -inputs.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, 0) inputs.set_val(Aircraft.CrewPayload.MISC_CARGO, 4077., 'lbm') inputs.set_val(Aircraft.CrewPayload.NON_FLIGHT_CREW_MASS_SCALER, 1.0) -inputs.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, 162, units='unitless') inputs.set_val(Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_SCALER, 1.) -inputs.set_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS, 150) inputs.set_val(Aircraft.CrewPayload.MASS_PER_PASSENGER, 165., 'lbm') inputs.set_val(Aircraft.CrewPayload.WING_CARGO, 0., 'lbm') diff --git a/aviary/utils/preprocessors.py b/aviary/utils/preprocessors.py index 0bbb03281..3e6e1413c 100644 --- a/aviary/utils/preprocessors.py +++ b/aviary/utils/preprocessors.py @@ -66,20 +66,20 @@ def preprocess_crewpayload(aviary_options: AviaryValues): # or if it was set to it's default value of zero if passenger_count != 0 and aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) == 0: aviary_options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, passenger_count) - print("User has specified supporting values for num_pax but has left num_pax blank or zero. Replacing num_pax with passenger_count.") + print("INFO: In preprocessor.py: User has specified supporting values for NUM_PASSENGERS but has left NUM_PASSENGERS=0. Replacing NUM_PASSENGERS with passenger_count.") if design_passenger_count != 0 and aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) == 0: aviary_options.set_val( Aircraft.CrewPayload.Design.NUM_PASSENGERS, design_passenger_count) - print("User has specified supporting values for design.num_pax but has left design.num_pax blank or zero. Replacing design.num_pax with design_passenger_count.") + print("INFO: In preprocessor.py: User has specified supporting values for Design.NUM_PASSENGERS but has left Design.NUM_PASSENGERS=0. Replacing Design.NUM_PASSENGERS with design_passenger_count.") num_pax = aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) design_num_pax = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) # Check summary data against individual data if individual data was entered - if num_pax != passenger_count: + if passenger_count != 0 and num_pax != passenger_count: raise om.AnalysisError( f"ERROR: In preprocesssors.py: NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)}) does not equal the sum of first class + business class + tourist class passengers (total of {passenger_count}).") - if design_num_pax != design_passenger_count: + if design_passenger_count != 0 and design_num_pax != design_passenger_count: raise om.AnalysisError( f"ERROR: In preprocesssors.py: Design.NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS)}) does not equal the sum of design first class + business class + tourist class passengers (total of {design_passenger_count}).") @@ -97,7 +97,7 @@ def preprocess_crewpayload(aviary_options: AviaryValues): # Copy data over if only one set of data exists # User has given detailed values for 1TB as flow and NO design values at all if passenger_count != 0 and design_num_pax == 0 and design_passenger_count == 0: - print("User has not input design data. Assume design data is equal to as-flow data user has already input") + print("INFO: In preprocessor.py: User has not input design passengers data. Assuming design is equal to as-flow passenger data.") aviary_options.set_val( Aircraft.CrewPayload.Design.NUM_PASSENGERS, passenger_count) aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, @@ -108,10 +108,10 @@ def preprocess_crewpayload(aviary_options: AviaryValues): aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS)) # user has not supplied detailed information on design but has supplied summary information on passengers elif num_pax != 0 and design_num_pax == 0: - print("User has specified summary as-flow passenger data but has not specified how many passengers the arcraft was designed for.") + print("INFO: In preprocessor.py: User has specified as-flown NUM_PASSENGERS but not how many passengers the aircraft was designed for in Design.NUM_PASSENGERS. Assuming they are equal.") aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, num_pax) elif design_passenger_count != 0 and num_pax == 0 and passenger_count == 0: - print("User has not input as-flow data. Assume as-flow data is equal to design seating data user has already input.") + print("INFO: In preprocessor.py: User has not input as-flown passengers data. Assuming as-flow is equal to design passenger data.") aviary_options.set_val( Aircraft.CrewPayload.NUM_PASSENGERS, design_passenger_count) aviary_options.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, @@ -122,7 +122,7 @@ def preprocess_crewpayload(aviary_options: AviaryValues): aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS)) # user has not supplied detailed information on design but has supplied summary information on passengers elif design_num_pax != 0 and num_pax == 0: - print("User has specified summary design passenger data but has not specified how many passengers are on the aircraft as flow.") + print("INFO: In preprocessor.py: User has specified Design.NUM_PASSENGERS but not how many passengers are on the flight in NUM_PASSENGERS. Assuming they are equal.") aviary_options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, design_num_pax) # Performe checks on the final data tables to ensure Design is always large then As-Flow @@ -139,8 +139,8 @@ def preprocess_crewpayload(aviary_options: AviaryValues): raise om.AnalysisError( f"ERROR: In preprocesssors.py: NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)}) is larger than the number of seats set by Design.NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS)}) .") - design_num_pax = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) - print(f"Aircraft has been designed for {design_num_pax} passengers.") + dnp = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) + print(f"INFO: In preprocessor.py: Aircraft has been designed for {dnp} passengers.") if Aircraft.CrewPayload.NUM_FLIGHT_ATTENDANTS not in aviary_options: flight_attendants_count = 0 # assume no passengers From 61ceb38edd4a37f0ef32967ff2a78ae1de1e300a Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Tue, 24 Sep 2024 14:05:29 -0400 Subject: [PATCH 070/113] added warning messages to target_range selection, fixed errors in Test_fuselage referring to NUM_PAX instead of Design.NUM_PAX, upd range_resid in test_phase_info because it needs to use target_range not design.range --- aviary/interface/methods_for_level2.py | 18 +++++++++++++----- aviary/interface/test/test_phase_info.py | 4 ++-- .../geometry/gasp_based/fuselage.py | 4 ++-- .../geometry/gasp_based/test/test_fuselage.py | 19 ++++++++++++------- 4 files changed, 29 insertions(+), 16 deletions(-) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index fde44c227..faad9e9d7 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -357,6 +357,12 @@ def load_inputs( self.cruise_mass_final = aviary_inputs.get_val( Mission.Summary.CRUISE_MASS_FINAL, units='lbm') + + # if 'target_range' in self.post_mission_info: + # self.target_range = wrapped_convert_units( + # phase_info['post_mission']['target_range'], 'NM') + # else: + print('WARNING: In methods_for_level2: user has not specified target_range in phase_info. This will be required in future release.') self.target_range = aviary_inputs.get_val( Mission.Design.RANGE, units='NM') self.cruise_mach = aviary_inputs.get_val(Mission.Design.MACH) @@ -370,12 +376,14 @@ def load_inputs( aviary_inputs.set_val(Mission.Summary.RANGE, wrapped_convert_units( phase_info['post_mission']['target_range'], 'NM'), units='NM') self.require_range_residual = True - self.target_range = aviary_inputs.get_val( - Mission.Summary.RANGE, units='NM') + self.target_range = wrapped_convert_units( + phase_info['post_mission']['target_range'], 'NM') else: + print('WARNING: In methods_for_level2: user has not specified target_range in phase_info. This will be required in future release.') self.require_range_residual = False - # TODO: this maybe broken? - self.target_range = aviary_inputs.get_val(Mission.Design.RANGE, units='NM') + # still instantiate target_range because used for default guesses for phase comps + self.target_range = aviary_inputs.get_val( + Mission.Design.RANGE, units='NM') return aviary_inputs @@ -2671,7 +2679,7 @@ def _add_objectives(self): om.ExecComp( "range_resid = target_range - actual_range", target_range={"val": self.target_range, "units": "NM"}, - actual_range={"val": self.target_range - 25, "units": "NM"}, + actual_range={"val": self.target_range, "units": "NM"}, range_resid={"val": 30, "units": "NM"}, ), promotes_inputs=[ diff --git a/aviary/interface/test/test_phase_info.py b/aviary/interface/test/test_phase_info.py index dd3b8ac82..9d4c0aca9 100644 --- a/aviary/interface/test/test_phase_info.py +++ b/aviary/interface/test/test_phase_info.py @@ -146,8 +146,8 @@ def test_phase_info_parameterization_height_energy(self): prob.run_model() - range_resid = prob.get_val(Mission.Constraints.RANGE_RESIDUAL, units='km')[-1] - assert_near_equal(range_resid, 5000.0 - 1.e-3) + range_resid = prob.get_val(Mission.Constraints.RANGE_RESIDUAL, units='nmi')[-1] + assert_near_equal(range_resid, 1906, tolerance=1e-3) assert_near_equal(prob.get_val("traj.cruise.timeseries.altitude", units='ft')[0], 31000.0) assert_near_equal(prob.get_val("traj.cruise.timeseries.mach")[0], diff --git a/aviary/subsystems/geometry/gasp_based/fuselage.py b/aviary/subsystems/geometry/gasp_based/fuselage.py index c45766382..af7e78556 100644 --- a/aviary/subsystems/geometry/gasp_based/fuselage.py +++ b/aviary/subsystems/geometry/gasp_based/fuselage.py @@ -56,8 +56,7 @@ def compute(self, inputs, outputs): seat_width = aviary_options.get_val(Aircraft.Fuselage.SEAT_WIDTH, units='inch') num_aisle = aviary_options.get_val(Aircraft.Fuselage.NUM_AISLES) aisle_width = aviary_options.get_val(Aircraft.Fuselage.AISLE_WIDTH, units='inch') - PAX = self.options['aviary_options'].get_val( - Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') + PAX = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) seat_pitch = aviary_options.get_val(Aircraft.Fuselage.SEAT_PITCH, units='inch') delta_diameter = inputs[Aircraft.Fuselage.DELTA_DIAMETER] @@ -65,6 +64,7 @@ def compute(self, inputs, outputs): if PAX < 1: print("Warning: you have not specified at least one passenger") + print(aviary_options) # single seat across cabin_len_a = PAX * seat_pitch / 12 diff --git a/aviary/subsystems/geometry/gasp_based/test/test_fuselage.py b/aviary/subsystems/geometry/gasp_based/test/test_fuselage.py index b40f34f9d..ed0d33693 100644 --- a/aviary/subsystems/geometry/gasp_based/test/test_fuselage.py +++ b/aviary/subsystems/geometry/gasp_based/test/test_fuselage.py @@ -18,7 +18,7 @@ class FuselageParametersTestCase1(unittest.TestCase): def setUp(self): options = get_option_defaults() - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, val=180) options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) @@ -57,7 +57,8 @@ class FuselageParametersTestCase2(unittest.TestCase): def setUp(self): options = get_option_defaults() - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=30, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=30, units='unitless') options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 1) @@ -93,7 +94,7 @@ def test_case2(self): class FuselageSizeTestCase1(unittest.TestCase): - """ + """ this is the GASP test case, input and output values based on large single aisle 1 v3 without bug fix """ @@ -186,7 +187,8 @@ class FuselageGroupTestCase1( def setUp(self): options = get_option_defaults() - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) @@ -235,7 +237,8 @@ class FuselageGroupTestCase2(unittest.TestCase): def setUp(self): options = get_option_defaults() - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") # not actual GASP value options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) # not actual GASP value @@ -295,7 +298,8 @@ class FuselageGroupTestCase3(unittest.TestCase): def setUp(self): options = get_option_defaults() - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=30, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=30, units='unitless') options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") # not actual GASP value options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) # not actual GASP value @@ -355,7 +359,8 @@ class FuselageGroupTestCase4(unittest.TestCase): def setUp(self): options = get_option_defaults() - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=30, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=30, units='unitless') options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") # not actual GASP value options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) # not actual GASP value From ee7783bb8c71ca4a37abddbc5217891ecc14435d Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Tue, 24 Sep 2024 14:30:51 -0400 Subject: [PATCH 071/113] changed num_pax to design.num_pax for several tests. converter_configuration_test_data_GwGm had to be updated because preprocess_crewpayload() is not run before some tests such as test_ovverride.py, and will therefore cause aircraft mis-sizing when only num_pax info is entered instead of design.num_pax --- ...converter_configuration_test_data_GwGm.csv | 2 +- .../gasp_based/test/test_size_group.py | 12 +++++++---- .../flops_based/test/test_air_conditioning.py | 4 ++-- .../test/test_equipment_and_useful_load.py | 21 ++++++++++++------- 4 files changed, 25 insertions(+), 14 deletions(-) diff --git a/aviary/models/test_aircraft/converter_configuration_test_data_GwGm.csv b/aviary/models/test_aircraft/converter_configuration_test_data_GwGm.csv index c13c48922..821224123 100644 --- a/aviary/models/test_aircraft/converter_configuration_test_data_GwGm.csv +++ b/aviary/models/test_aircraft/converter_configuration_test_data_GwGm.csv @@ -9,7 +9,7 @@ aircraft:controls:stability_augmentation_system_mass,0,lbm aircraft:controls:stability_augmentation_system_mass_scaler,1,unitless aircraft:crew_and_payload:cargo_mass,15970,lbm aircraft:crew_and_payload:catering_items_mass_per_passenger,10,lbm -aircraft:crew_and_payload:num_passengers,154,unitless +aircraft:crew_and_payload:design:num_passengers,154,unitless aircraft:crew_and_payload:passenger_mass_with_bags,200,lbm aircraft:crew_and_payload:passenger_service_mass_per_passenger,5,lbm aircraft:crew_and_payload:water_mass_per_occupant,3,lbm diff --git a/aviary/subsystems/geometry/gasp_based/test/test_size_group.py b/aviary/subsystems/geometry/gasp_based/test/test_size_group.py index 0a9530218..dc7c1bb1f 100644 --- a/aviary/subsystems/geometry/gasp_based/test/test_size_group.py +++ b/aviary/subsystems/geometry/gasp_based/test/test_size_group.py @@ -17,7 +17,8 @@ def setUp(self): options = get_option_defaults() options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) @@ -164,7 +165,8 @@ def setUp(self): options.set_val(Aircraft.Wing.HAS_STRUT, val=True, units='unitless') options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, val=True, units='unitless') @@ -384,7 +386,8 @@ def setUp(self): val=True, units='unitless') options.set_val(Aircraft.Design.COMPUTE_VTAIL_VOLUME_COEFF, val=True, units='unitless') - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, val=True, units='unitless') options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") @@ -607,7 +610,8 @@ def setUp(self): val=False, units='unitless') options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 1) diff --git a/aviary/subsystems/mass/flops_based/test/test_air_conditioning.py b/aviary/subsystems/mass/flops_based/test/test_air_conditioning.py index a168955a5..b0becd20f 100644 --- a/aviary/subsystems/mass/flops_based/test/test_air_conditioning.py +++ b/aviary/subsystems/mass/flops_based/test/test_air_conditioning.py @@ -43,7 +43,7 @@ def test_case(self, case_name): Aircraft.Fuselage.MAX_HEIGHT, Aircraft.Fuselage.PLANFORM_AREA], output_keys=Aircraft.AirConditioning.MASS, - aviary_option_keys=[Aircraft.CrewPayload.NUM_PASSENGERS], + aviary_option_keys=[Aircraft.CrewPayload.Design.NUM_PASSENGERS], version=Version.TRANSPORT, tol=3.0e-4, atol=1e-11) @@ -115,7 +115,7 @@ def test_case(self, case_name): case_name, input_keys=Aircraft.AirConditioning.MASS_SCALER, output_keys=Aircraft.AirConditioning.MASS, - aviary_option_keys=Aircraft.CrewPayload.NUM_PASSENGERS, + aviary_option_keys=Aircraft.CrewPayload.Design.NUM_PASSENGERS, version=Version.ALTERNATE) def test_IO(self): diff --git a/aviary/subsystems/mass/gasp_based/test/test_equipment_and_useful_load.py b/aviary/subsystems/mass/gasp_based/test/test_equipment_and_useful_load.py index fe0d4c988..218e64672 100644 --- a/aviary/subsystems/mass/gasp_based/test/test_equipment_and_useful_load.py +++ b/aviary/subsystems/mass/gasp_based/test/test_equipment_and_useful_load.py @@ -16,7 +16,8 @@ class FixedEquipMassTestCase1(unittest.TestCase): def setUp(self): options = get_option_defaults() - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.LandingGear.FIXED_GEAR, val=False, units='unitless') @@ -105,7 +106,8 @@ class FixedEquipMassTestCase2(unittest.TestCase): def setUp(self): options = get_option_defaults() - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=5, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=5, units='unitless') options.set_val(Aircraft.LandingGear.FIXED_GEAR, val=False, units='unitless') @@ -288,7 +290,8 @@ class FixedEquipMassTestCase4smooth( def setUp(self): options = get_option_defaults() - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.LandingGear.FIXED_GEAR, val=False, units='unitless') options.set_val(Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, @@ -382,7 +385,8 @@ class FixedEquipMassTestCase5smooth(unittest.TestCase): def setUp(self): options = get_option_defaults() - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=5, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=5, units='unitless') options.set_val(Aircraft.LandingGear.FIXED_GEAR, val=False, units='unitless') options.set_val(Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, @@ -476,7 +480,8 @@ class FixedEquipMassTestCase6smooth(unittest.TestCase): def setUp(self): options = get_option_defaults() - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=5, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=5, units='unitless') options.set_val(Aircraft.Engine.TYPE, val=[GASPEngineType.RECIP_CARB], units='unitless') options.set_val(Aircraft.LandingGear.FIXED_GEAR, @@ -574,7 +579,8 @@ class EquipAndUsefulMassGroupTestCase1( def setUp(self): options = get_option_defaults() - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.LandingGear.FIXED_GEAR, val=False, units='unitless') @@ -676,7 +682,8 @@ def tearDown(self): def test_case1(self): options = get_option_defaults() - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.LandingGear.FIXED_GEAR, val=False, units='unitless') From aa8e6ce0e396343d7feb67bd22142cc5f9e7d024 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 26 Sep 2024 09:14:16 -0400 Subject: [PATCH 072/113] still trying to track down OEM_winfuel_mass issues --- .../large_single_aisle_1/V3_bug_fixed_IO.py | 2 +- aviary/subsystems/mass/gasp_based/fuel.py | 9 + .../gasp_based/test/test_mass_summation.py | 6274 ++++++++--------- 3 files changed, 3147 insertions(+), 3138 deletions(-) diff --git a/aviary/models/large_single_aisle_1/V3_bug_fixed_IO.py b/aviary/models/large_single_aisle_1/V3_bug_fixed_IO.py index 5686a33a0..ac83b406e 100644 --- a/aviary/models/large_single_aisle_1/V3_bug_fixed_IO.py +++ b/aviary/models/large_single_aisle_1/V3_bug_fixed_IO.py @@ -13,7 +13,7 @@ V3_bug_fixed_options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, val=False, units='unitless') V3_bug_fixed_options.set_val( - Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + Aircraft.CrewPayload.Design.NUM_PASSENGERS, val=180, units='unitless') V3_bug_fixed_options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') V3_bug_fixed_options.set_val( Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') diff --git a/aviary/subsystems/mass/gasp_based/fuel.py b/aviary/subsystems/mass/gasp_based/fuel.py index df1734897..650717fb5 100644 --- a/aviary/subsystems/mass/gasp_based/fuel.py +++ b/aviary/subsystems/mass/gasp_based/fuel.py @@ -502,6 +502,15 @@ def compute(self, inputs, outputs): - useful_wt ) + print('OEM_wingfuel_mass', OEM_wingfuel_wt / GRAV_ENGLISH_LBM) + print('supporting values') + print('gross_wt_initial', gross_wt_initial) + print('propulsion_wt', propulsion_wt) + print('control_wt', control_wt) + print('struct_wt', struct_wt) + print('fixed_equip_wt', fixed_equip_wt) + print('useful_wt', useful_wt) + OEM_fuel_vol = OEM_wingfuel_wt / rho_fuel design_fuel_vol = (1.0 + fuel_margin / 100.0) * req_fuel_wt / rho_fuel diff --git a/aviary/subsystems/mass/gasp_based/test/test_mass_summation.py b/aviary/subsystems/mass/gasp_based/test/test_mass_summation.py index 4101e5325..b8dc00c63 100644 --- a/aviary/subsystems/mass/gasp_based/test/test_mass_summation.py +++ b/aviary/subsystems/mass/gasp_based/test/test_mass_summation.py @@ -162,3143 +162,3143 @@ def test_case1(self): assert_check_partials(partial_data, atol=3e-10, rtol=1e-12) -class MassSummationTestCase2(unittest.TestCase): - """ - This is the large single aisle 1 V3.5 test case. - All values are from V3.5 output (or hand calculated from the output, and these cases - are specified). - """ - - def setUp(self): - - options = get_option_defaults() - options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, - val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') - options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') - options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') - options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.LandingGear.FIXED_GEAR, - val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, - val=200, units="lbm") - options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) - options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") - options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) - options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") - options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - - self.prob = om.Problem() - self.prob.model.add_subsystem( - "size", - SizeGroup( - aviary_options=options, - ), - promotes_inputs=["aircraft:*", "mission:*"], - promotes_outputs=[ - "aircraft:*", - ], - ) - self.prob.model.add_subsystem( - "GASP_mass", - MassPremission( - aviary_options=options, - ), - promotes=["*"], - ) - - self.prob.model.set_input_defaults( - Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" - ) - self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" - ) - self.prob.model.set_input_defaults( - Mission.Design.GROSS_MASS, val=175400, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.LOADING, val=128, units="lbf/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") - self.prob.model.set_input_defaults( - Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") - self.prob.model.set_input_defaults( - Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" - ) - # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 - self.prob.model.set_input_defaults( - Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") - # self.prob.model.set_input_defaults( - # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" - # ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless') - self.prob.model.set_input_defaults( - Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Nacelle.FINENESS, 2, units="unitless") - - self.prob.model.set_input_defaults( - Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" - ) - - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.SWEEP, val=0, units='deg' - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" - ) # Based onlarge single aisle 1for updated flaps mass model - self.prob.model.set_input_defaults( - Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" - ) # Based onlarge single aisle 1for updated flaps mass model - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.APU.MASS, val=928.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Avionics.MASS, val=1959.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.AntiIcing.MASS, val=551.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Furnishings.MASS, val=11192.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_MARGIN, val=0, units="unitless") - - self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - - self.prob.setup(check=False, force_alloc_complex=True) - - def test_case1(self): - - self.prob.run_model() - - tol = 5e-4 - # size values: - assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) - assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) - assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - - assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 17.49, tol) - assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.41, tol) - assert_near_equal( - self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1397, tol - ) # not exact GASP value from the output file, likely due to rounding error - - # note: this is not the value in the GASP output, because the output calculates - # them differently. This was calculated by hand. - assert_near_equal( - self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.578314120156815, tol - ) - # note: this is not the value in the GASP output, because the output calculates - # them differently. This was calculated by hand. - assert_near_equal( - self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 16.828924591320984, tol - ) - assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) - - # fixed mass values: - assert_near_equal( - self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.35, tol - ) # calculated by hand - - # note: fixed_mass.tail.loc_MAC_vtail not included in v3.5 - - assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) - assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) - - # wing values: - assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15653, tol) - - # fuel values: - # modified from GASP value to account for updated crew mass. GASP value is - # 79147.2 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 79002.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 79147.2 - - # calculated by hand, #modified from GASP value to account for updated crew - # mass. GASP value is 102321.45695930265 - assert_near_equal( - self.prob["fuel_mass.fus_mass_full"], 102359.6, tol - ) - # modified from GASP value to account for updated crew mass. GASP value is - # 1769 - assert_near_equal( - self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1763.1, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1769 - - assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 50186, tol) - assert_near_equal( - self.prob[Aircraft.Fuselage.MASS], 18663, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 18787 - - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS_REQUIRED], 43002.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 43147.2 - assert_near_equal( - self.prob[Aircraft.Propulsion.MASS], 16133.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 16140 - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS], 43002.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 43147 - assert_near_equal( - self.prob["fuel_mass.fuel_mass_min"], 32962.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 33107.2 - assert_near_equal( - self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 859.68, tol - ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 862.5603807559726 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1579.36, tol - ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 1582.2403068511774 - assert_near_equal( - self.prob[Aircraft.Design.OPERATING_MASS], 96397.1, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 96253.0 - # extra_fuel_mass calculated differently in this version, so fuel_mass.fuel_and_oem.payload_mass_max_fuel test not included - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 55725.1, tol - ) - assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 55725.1, tol) - assert_near_equal( - self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol - ) # always zero when no body tank - assert_near_equal( - self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol - ) # always zero when no body tank - assert_near_equal( - self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol - ) # always zero when no body tank - - partial_data = self.prob.check_partials(out_stream=None, method="cs") - assert_check_partials(partial_data, atol=2e-10, rtol=1e-12) - - -class MassSummationTestCase3(unittest.TestCase): - """ - This is thelarge single aisle 1V3.6 test case with a fuel margin of 0%, a wing loading of 128 psf, and a SLS thrust of 29500 lbf - All values are from V3.6 output (or hand calculated from the output, and these cases are specified). - """ - - def setUp(self): - - options = get_option_defaults() - options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, - val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') - options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') - options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') - options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.LandingGear.FIXED_GEAR, - val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, - val=200, units="lbm") - options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) - options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") - options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) - options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") - options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - - self.prob = om.Problem() - self.prob.model.add_subsystem( - "size", - SizeGroup( - aviary_options=options, - ), - promotes_inputs=["aircraft:*", "mission:*"], - promotes_outputs=[ - "aircraft:*", - ], - ) - self.prob.model.add_subsystem( - "GASP_mass", - MassPremission( - aviary_options=options, - ), - promotes=["*"], - ) - - self.prob.model.set_input_defaults( - Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" - ) - self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" - ) - self.prob.model.set_input_defaults( - Mission.Design.GROSS_MASS, val=175400, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.LOADING, val=128, units="lbf/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") - self.prob.model.set_input_defaults( - Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") - self.prob.model.set_input_defaults( - Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" - ) - # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 - self.prob.model.set_input_defaults( - Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") - # self.prob.model.set_input_defaults( - # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" - # ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Nacelle.FINENESS, 2, units="unitless") - - self.prob.model.set_input_defaults( - Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" - ) - - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.SWEEP, val=0, units='deg' - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" - ) # Based onlarge single aisle 1for updated flaps mass model - self.prob.model.set_input_defaults( - Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" - ) # Based on large single aisle 1 for updated flaps mass model - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.APU.MASS, val=928.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Avionics.MASS, val=1959.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.AntiIcing.MASS, val=551.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Furnishings.MASS, val=11192.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_MARGIN, val=0, units="unitless") - - self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - - self.prob.setup(check=False, force_alloc_complex=True) - - def test_case1(self): - - self.prob.run_model() - - tol = 5e-4 - # size values: - assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) - assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) - assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - - assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 17.49, tol) - assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.41, tol) - assert_near_equal( - self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1397, tol - ) # not exact value, likely due to rounding error - - assert_near_equal( - self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.578314120156815, tol - ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. - assert_near_equal( - self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 16.828924591320984, tol - ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. - assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) - - # fixed mass values: - assert_near_equal( - self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol - ) # calculated by hand - - assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) - assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) - - # wing values: - assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15653, tol) - - # fuel values: - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 79002.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 79147.2 - - assert_near_equal( - self.prob["fuel_mass.fus_mass_full"], 102359.6, tol - ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 102321.45695930265 - assert_near_equal( - self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1763.1, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 102321.45695930265 - - assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 50186, tol) - assert_near_equal( - self.prob[Aircraft.Fuselage.MASS], 18663, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 18787 - - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS_REQUIRED], 43002.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 43147.2 - assert_near_equal( - self.prob[Aircraft.Propulsion.MASS], 16133.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 16140 - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS], 43002.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 43147 - assert_near_equal( - self.prob["fuel_mass.fuel_mass_min"], 32962.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 33107.2 - assert_near_equal( - self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 859.68, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 862.6 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1579.36, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1582.2 - assert_near_equal( - self.prob[Aircraft.Design.OPERATING_MASS], 96397.1, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 96253.0 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 36000, tol - ) # note: value came from running the GASP code on my own and printing it out - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 55725.1, tol - ) - assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 55725.1, tol) - assert_near_equal( - self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol - ) # always zero when no body tank - assert_near_equal( - self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol - ) # always zero when no body tank - assert_near_equal( - self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol - ) # always zero when no body tank - - partial_data = self.prob.check_partials(out_stream=None, method="cs") - assert_check_partials(partial_data, atol=2e-10, rtol=1e-12) - - -class MassSummationTestCase4(unittest.TestCase): - """ - This is the large single aisle 1V3.6 test case with a fuel margin of 10%, a wing loading of 128 psf, and a SLS thrust of 29500 lbf - All values are from V3.6 output (or hand calculated from the output, and these cases are specified). - """ - - def setUp(self): - - options = get_option_defaults() - options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, - val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') - options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') - options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') - options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.LandingGear.FIXED_GEAR, - val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, - val=200, units="lbm") - options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) - options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") - options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) - options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") - options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - - self.prob = om.Problem() - self.prob.model.add_subsystem( - "size", - SizeGroup( - aviary_options=options, - ), - promotes_inputs=["aircraft:*", "mission:*"], - promotes_outputs=[ - "aircraft:*", - ], - ) - self.prob.model.add_subsystem( - "GASP_mass", - MassPremission( - aviary_options=options, - ), - promotes=["*"], - ) - - self.prob.model.set_input_defaults( - Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" - ) - self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" - ) - self.prob.model.set_input_defaults( - Mission.Design.GROSS_MASS, val=175400, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.LOADING, val=128, units="lbf/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") - self.prob.model.set_input_defaults( - Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") - self.prob.model.set_input_defaults( - Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" - ) - # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 - self.prob.model.set_input_defaults( - Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") - # self.prob.model.set_input_defaults( - # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" - # ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Nacelle.FINENESS, 2, units="unitless") - - self.prob.model.set_input_defaults( - Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" - ) - - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.SWEEP, val=0, units='deg' - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" - ) # Based onlarge single aisle 1for updated flaps mass model - self.prob.model.set_input_defaults( - Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" - ) # Based on large single aisle 1 for updated flaps mass model - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.APU.MASS, val=928.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Avionics.MASS, val=1959.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.AntiIcing.MASS, val=551.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Furnishings.MASS, val=11192.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_MARGIN, val=10, units="unitless" - ) - - self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - - self.prob.setup(check=False, force_alloc_complex=True) - - def test_case1(self): - - self.prob.run_model() - - tol = 5e-4 - # size values: - assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) - assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) - assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - - assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 17.49, tol) - assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.41, tol) - assert_near_equal( - self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1397, tol - ) # slightly different from GASP value, likely numerical error - - assert_near_equal( - self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.578314120156815, tol - ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. - assert_near_equal( - self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 16.828924591320984, tol - ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. - assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) - - # fixed mass values: - assert_near_equal( - self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol - ) # calculated by hand - - assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) - assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) - - # wing values: - assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15653, tol) - - # fuel values: - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 78823.0, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 78966.7 - - assert_near_equal( - self.prob["fuel_mass.fus_mass_full"], 102541.4, tol - ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 102501.95695930265 - assert_near_equal( - self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1931.3, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1938 - - assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 50198, tol) - assert_near_equal( - self.prob[Aircraft.Fuselage.MASS], 18675, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 18799 - - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS_REQUIRED], 42823.0, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 42966.7 - assert_near_equal( - self.prob[Aircraft.Propulsion.MASS], 16302.1, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 16309 - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS], 42823.0, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 42967 - assert_near_equal( - self.prob["fuel_mass.fuel_mass_min"], 32783.0, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 32926.7 - assert_near_equal( - self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 941.69, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 944.8 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1575.76, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1578.6 - assert_near_equal( - self.prob[Aircraft.Design.OPERATING_MASS], 96577.0, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 96433.0 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 36000, tol - ) # note: value came from running the GASP code on my own and printing it out - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 55725.1, tol - ) - assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 55725.1, tol) - assert_near_equal( - self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol - ) # always zero when no body tank - assert_near_equal( - self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol - ) # always zero when no body tank - assert_near_equal( - self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol - ) # always zero when no body tank - - partial_data = self.prob.check_partials(out_stream=None, method="cs") - assert_check_partials(partial_data, atol=2e-10, rtol=1e-12) - - -class MassSummationTestCase5(unittest.TestCase): - """ - This is thelarge single aisle 1V3.6 test case with a fuel margin of 0%, a wing loading of 150 psf, and a SLS thrust of 29500 lbf - All values are from V3.6 output (or hand calculated from the output, and these cases are specified). - """ - - def setUp(self): - - options = get_option_defaults() - options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, - val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') - options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') - options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') - options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.LandingGear.FIXED_GEAR, - val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, - val=200, units="lbm") - options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) - options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") - options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) - options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") - options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - - self.prob = om.Problem() - self.prob.model.add_subsystem( - "size", - SizeGroup( - aviary_options=options, - ), - promotes_inputs=["aircraft:*", "mission:*"], - promotes_outputs=[ - "aircraft:*", - ], - ) - self.prob.model.add_subsystem( - "GASP_mass", - MassPremission( - aviary_options=options, - ), - promotes=["*"], - ) - - self.prob.model.set_input_defaults( - Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" - ) - self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" - ) - self.prob.model.set_input_defaults( - Mission.Design.GROSS_MASS, val=175400, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.LOADING, val=150, units="lbf/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") - self.prob.model.set_input_defaults( - Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") - self.prob.model.set_input_defaults( - Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" - ) - # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 - self.prob.model.set_input_defaults( - Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") - # self.prob.model.set_input_defaults( - # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" - # ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Nacelle.FINENESS, 2, units="unitless") - - self.prob.model.set_input_defaults( - Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" - ) - - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.SWEEP, val=0, units='deg' - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" - ) # Based onlarge single aisle 1for updated flaps mass model - self.prob.model.set_input_defaults( - Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" - ) # Based on large single aisle 1 for updated flaps mass model - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.APU.MASS, val=928.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Avionics.MASS, val=1959.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.AntiIcing.MASS, val=551.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Furnishings.MASS, val=11192.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_MARGIN, val=0.0, units="unitless" - ) - - self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - - self.prob.setup(check=False, force_alloc_complex=True) - - def test_case1(self): - - self.prob.run_model() - - tol = 5e-4 - # size values: - assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) - assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) - assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - - assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 16.16, tol) - assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 15.1, tol) - assert_near_equal( - self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1394, tol - ) # slightly different from GASP value, likely rounding error - - assert_near_equal( - self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 8.848695928254141, tol - ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. - assert_near_equal( - self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 15.550266681026597, tol - ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. - assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) - - # fixed mass values: - assert_near_equal( - self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol - # self.prob["fixed_mass.main_gear_mass"], 6384.349999999999, tol - ) # calculated by hand - - assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) - assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) - - # wing values: - assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 14631, tol) - - # fuel values: - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 80475.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 81424.8 - - assert_near_equal( - self.prob["fuel_mass.fus_mass_full"], 102510.7, tol - ) # calculated by hand - assert_near_equal( - self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1823.4, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1862 - - assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 48941, tol) - assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 18675, tol) - - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS_REQUIRED], 44472.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 45424.8 - assert_near_equal( - self.prob[Aircraft.Propulsion.MASS], 16194.2, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 16233 - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS], 44472.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 45425 - assert_near_equal( - self.prob["fuel_mass.fuel_mass_min"], 34432.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 35384.8 - assert_near_equal( - self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 889.06, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 908.1 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1608.74, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1627.8 - assert_near_equal( - self.prob[Aircraft.Design.OPERATING_MASS], 94927.1, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 93975 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 35380.5, tol - ) # note: value came from running the GASP code on my own and printing it out, #modified from GASP value to account for updated crew mass. GASP value is 34427.4 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 43852.1, tol - ) - assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 43852.1, tol) - assert_near_equal( - self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 620.739, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1572.6 - assert_near_equal( - self.prob["fuel_mass.body_tank.extra_fuel_volume"], 12.4092, tol - ) # slightly different from GASP value, likely a rounding error, #modified from GASP value to account for updated crew mass. GASP value is 31.43 - assert_near_equal( - self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 620.736, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1572.6 - - partial_data = self.prob.check_partials(out_stream=None, method="cs") - assert_check_partials(partial_data, atol=3e-10, rtol=1e-12) - - -class MassSummationTestCase6(unittest.TestCase): - """ - This is thelarge single aisle 1V3.6 test case with a fuel margin of 10%, a wing loading of 150 psf, and a SLS thrust of 29500 lbf - All values are from V3.6 output (or hand calculated from the output, and these cases are specified). - """ - - def setUp(self): - - options = get_option_defaults() - options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, - val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') - options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') - options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') - options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.LandingGear.FIXED_GEAR, - val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, - val=200, units="lbm") - options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) - options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") - options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) - options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") - options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - - self.prob = om.Problem() - self.prob.model.add_subsystem( - "size", - SizeGroup( - aviary_options=options, - ), - promotes_inputs=["aircraft:*", "mission:*"], - promotes_outputs=[ - "aircraft:*", - ], - ) - self.prob.model.add_subsystem( - "GASP_mass", - MassPremission( - aviary_options=options, - ), - promotes=["*"], - ) - - self.prob.model.set_input_defaults( - Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" - ) - self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" - ) - self.prob.model.set_input_defaults( - Mission.Design.GROSS_MASS, val=175400, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.LOADING, val=150, units="lbf/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") - self.prob.model.set_input_defaults( - Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") - self.prob.model.set_input_defaults( - Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" - ) - # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 - self.prob.model.set_input_defaults( - Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") - # self.prob.model.set_input_defaults( - # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" - # ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Nacelle.FINENESS, 2, units="unitless") - - self.prob.model.set_input_defaults( - Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" - ) - - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.SWEEP, val=0, units='deg' - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" - ) # Based onlarge single aisle 1for updated flaps mass model - self.prob.model.set_input_defaults( - Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" - ) # Based onlarge single aisle 1for updated flaps mass model - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.APU.MASS, val=928.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Avionics.MASS, val=1959.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.AntiIcing.MASS, val=551.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Furnishings.MASS, val=11192.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_MARGIN, val=10.0, units="unitless" - ) - - self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - - self.prob.setup(check=False, force_alloc_complex=True) - - def test_case1(self): - - self.prob.run_model() - - tol = 5e-4 - # size values: - assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) - assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) - assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - - assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 16.16, tol) - assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 15.1, tol) - assert_near_equal( - self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1394, tol - ) # note: not exact GASP value, likely rounding error - - assert_near_equal( - self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 8.848695928254141, tol - ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. - assert_near_equal( - self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 15.550266681026597, tol - ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. - assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) - - # fixed mass values: - assert_near_equal( - self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol - # self.prob["fixed_mass.main_gear_mass"], 6384.349999999999, tol - ) # calculated by hand - - assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) - assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) - - # wing values: - assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 14631, tol) - - # fuel values: - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 80029.2, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 80982.7 - - assert_near_equal( - self.prob["fuel_mass.fus_mass_full"], 106913.6, tol - ) # calculated by hand - assert_near_equal( - self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1985.7, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 2029 - - assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 49222, tol) - assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 18956, tol) - - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS_REQUIRED], 44029.2, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 44982.7 - assert_near_equal( - self.prob[Aircraft.Propulsion.MASS], 16356.5, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 16399 - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS], 44029.2, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 44982.7 - assert_near_equal( - self.prob["fuel_mass.fuel_mass_min"], 33989.2, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 34942.7 - assert_near_equal( - self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 968.21, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 989.2 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1599.87, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1618.9 - assert_near_equal( - self.prob[Aircraft.Design.OPERATING_MASS], 95370.8, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 94417 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 35823.0, tol - ) # note: value came from running the GASP code on my own and printing it out, #modified from GASP value to account for updated crew mass. GASP value is 34879.2 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 43852.1, tol - ) - assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 43852.1, tol) - assert_near_equal( - self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 177.042, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1120.9 - assert_near_equal( - self.prob["fuel_mass.body_tank.extra_fuel_volume"], 91.5585, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 112.3 - assert_near_equal( - self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 4579.96, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 5618.2 - - partial_data = self.prob.check_partials(out_stream=None, method="cs") - assert_check_partials(partial_data, atol=3e-10, rtol=1e-12) - - -class MassSummationTestCase7(unittest.TestCase): - """ - This is the Advanced Tube and Wing V3.6 test case - All values are from V3.6 output, hand calculated from the output, or were printed out after running the code manually. - Values not directly from the output are labeled as such. - """ - - def setUp(self): - - options = get_option_defaults() - options.set_val(Aircraft.Wing.HAS_FOLD, val=True, units='unitless') - options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, - val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') - options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37100, units='ft') - options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.LandingGear.FIXED_GEAR, - val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, - val=200, units="lbm") - options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) - options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") - options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) - options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") - options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - - self.prob = om.Problem() - self.prob.model.add_subsystem( - "size", - SizeGroup( - aviary_options=options, - ), - promotes_inputs=["aircraft:*", "mission:*"], - promotes_outputs=[ - "aircraft:*", - ], - ) - self.prob.model.add_subsystem( - "GASP_mass", - MassPremission( - aviary_options=options, - ), - promotes=["*"], - ) - - self.prob.model.set_input_defaults( - Aircraft.Wing.ASPECT_RATIO, val=11, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" - ) - self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Mission.Design.GROSS_MASS, val=145388.0, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.LOADING, val=104.50, units="lbf/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALED_SLS_THRUST, val=17000.0, units="lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") - self.prob.model.set_input_defaults( - Aircraft.Fuel.WING_FUEL_FRACTION, 0.475, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.09986, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") - self.prob.model.set_input_defaults( - Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.WETTED_AREA_SCALER, 1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MOMENT_RATIO, 2.1621, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.REFERENCE_DIAMETER, 7.36, units="ft") - # self.prob.model.set_input_defaults( - # Aircraft.Engine.REFERENCE_SLS_THRUST, 28620.0, units="lbf" - # ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALE_FACTOR, 0.594, units='unitless' - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.2095, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Nacelle.FINENESS, 1.715, units="unitless") - self.prob.model.set_input_defaults(Aircraft.Wing.FOLDED_SPAN, 118, units="ft") - - self.prob.model.set_input_defaults( - Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" - ) - - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CARGO_MASS, val=15970.0, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.SWEEP, val=0, units='deg' - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" - ) # Based onlarge single aisle 1for updated flaps mass model - self.prob.model.set_input_defaults( - Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" - ) # Based on large single aisle 1 for updated flaps mass model - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SPECIFIC, val=0.2355, units="lbm/lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.165, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.APU.MASS, val=1014.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.085, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.105, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Avionics.MASS, val=1504.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.AntiIcing.MASS, val=126.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Furnishings.MASS, val=9114.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=0.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=10.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_COEFFICIENT, val=85, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.FOLD_MASS_COEFFICIENT, val=0.2, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' - ) # note: not actually defined in program, likely an error - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_MARGIN, val=10.0, units="unitless" - ) - - self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - - self.prob.setup(check=False, force_alloc_complex=True) - - def test_case1(self): - - self.prob.run_model() - - tol = 5e-4 - # size values: - assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) - assert_near_equal(self.prob["size.fuselage.cabin_len"], 61.6, tol) - assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - - assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 16.91, tol) - assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.01, tol) - assert_near_equal( - self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1132, tol - ) # slightly different from GASP value, likely a rounding error - - assert_near_equal( - self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.6498, tol - # note: value came from running the GASP code on my own and printing it out (GASP output calculates this differently) - ) - assert_near_equal( - self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 13.4662, tol - # note: value came from running the GASP code on my own and printing it out (GASP output calculates this differently) - ) - assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 11.77, tol) - - # fixed mass values: - assert_near_equal( - self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 5219.3076, tol - # self.prob["fixed_mass.main_gear_mass"], 5219.3076, tol - ) # note: value came from running the GASP code on my own and printing it out - - assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 8007, tol) - assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1321/2, tol) - - # wing values: - assert_near_equal( - self.prob["wing_mass.isolated_wing_mass"], 13993, tol - ) # calculated as difference between wing mass and fold mass, not an actual GASP variable - - # fuel values: - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 63452.2, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 62427.2 - - assert_near_equal( - self.prob["fuel_mass.fus_mass_full"], 99396.7, tol - ) # note: value came from running the GASP code on my own and printing it out - assert_near_equal( - self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1472.6, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1426 - - assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 45373.4, tol) - assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 18859.9, tol) - - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS_REQUIRED], 32652.2, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 31627.2 - assert_near_equal( - self.prob[Aircraft.Propulsion.MASS], 10800.8, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 10755.0 - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS], 32652.2, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 31627.0 - assert_near_equal( - self.prob["fuel_mass.fuel_mass_min"], 16682.2, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 15657.2 - assert_near_equal( - self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 718.03, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 695.5 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1268.48, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1248.0 - assert_near_equal( - self.prob[Aircraft.Design.OPERATING_MASS], 81935.8, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 82961.0 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 30800.0039, tol - ) # note: value came from running the GASP code on my own and printing it out - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 33892.8, tol - ) - assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 33892.8, tol) - assert_near_equal(self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol) - assert_near_equal( - self.prob["fuel_mass.body_tank.extra_fuel_volume"], 40.4789, 0.005 - ) # note: higher tol because slightly different from GASP value, likely numerical issues, #modified from GASP value to account for updated crew mass. GASP value is 17.9 - assert_near_equal( - self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 2024.70, 0.003 - ) # note: higher tol because slightly different from GASP value, likely numerical issues, #modified from GASP value to account for updated crew mass. GASP value is 897.2 - - partial_data = self.prob.check_partials(out_stream=None, method="cs") - assert_check_partials(partial_data, atol=3e-9, rtol=6e-11) - - -class MassSummationTestCase8(unittest.TestCase): - """ - This is the Trans-sonic Truss-Braced Wing V3.6 test case - All values are from V3.6 output, hand calculated from the output, or were printed out after running the code manually. - Values not directly from the output are labeled as such. - """ - - def setUp(self): - - options = get_option_defaults() - options.set_val(Aircraft.Wing.HAS_FOLD, val=True, units='unitless') - options.set_val(Aircraft.Wing.HAS_STRUT, val=True, units='unitless') - options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, - val=False, units='unitless') - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') - options.set_val(Mission.Design.CRUISE_ALTITUDE, val=43000, units='ft') - options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') - options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.LandingGear.FIXED_GEAR, - val=False, units='unitless') - options.set_val(Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, - val=True, units='unitless') - options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, - val=200, units="lbm") - options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) - options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") - options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) - options.set_val(Aircraft.Fuselage.SEAT_PITCH, 44.2, units="inch") - options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - - self.prob = om.Problem() - self.prob.model.add_subsystem( - "size", - SizeGroup( - aviary_options=options, - ), - promotes_inputs=["aircraft:*", "mission:*"], - promotes_outputs=[ - "aircraft:*", - ], - ) - self.prob.model.add_subsystem( - "GASP_mass", - MassPremission( - aviary_options=options, - ), - promotes=["*"], - ) - - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MOMENT_RATIO, val=0.13067, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.ASPECT_RATIO, val=4.025, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MOMENT_RATIO, 3.0496, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.REFERENCE_DIAMETER, 7.642, units="ft") - # self.prob.model.set_input_defaults( - # Aircraft.Engine.REFERENCE_SLS_THRUST, 28620.0, units="lbf" - # ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALE_FACTOR, 1.35255, units='unitless' - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.2095, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Nacelle.FINENESS, 1.660, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 6.85, units="ft" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.TAIL_FINENESS, 1.18, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.WETTED_AREA_SCALER, 1.0, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.LOADING, val=87.5, units="lbf/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" - ) - - self.prob.model.set_input_defaults( - Aircraft.APU.MASS, val=1014.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.085, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.105, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Avionics.MASS, val=1504.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.AntiIcing.MASS, val=126.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Furnishings.MASS, val=9114.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=0.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=10.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALED_SLS_THRUST, val=21160.0, units="lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALE_FACTOR, 0.73934, units='unitless' - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.WING_FUEL_FRACTION, 0.5625, units="unitless" - ) - self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=22.47, units="deg") - self.prob.model.set_input_defaults( - Aircraft.Wing.MOUNTING_TYPE, val=.1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.ASPECT_RATIO, val=19.565, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Strut.ATTACHMENT_LOCATION, val=118, units="ft" - ) - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CARGO_MASS, val=15970.0, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SPECIFIC, val=0.2470, units="lbm/lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.MASS_SPECIFIC, val=2.5, units="lbm/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.163, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Engine.WING_LOCATIONS, val=0.2143, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.ASPECT_RATIO, val=0.825, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.SWEEP, val=0, units='deg' - ) # not in file - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.2076, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.2587, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.11, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" - ) # Based onlarge single aisle 1for updated flaps mass model - self.prob.model.set_input_defaults( - Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" - ) # Based on large single aisle 1 for updated flaps mass model - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.5936, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=30, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" - ) # not in file - self.prob.model.set_input_defaults( - Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" - ) # not in file - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MASS_COEFFICIENT, val=0.03390, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_MARGIN, val=10.0, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.060, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_COEFFICIENT, val=89.66, units="unitless" - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' - ) # not in file - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Mission.Design.GROSS_MASS, val=143100.0, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_COEFFICIENT, val=78.94, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.TAPER_RATIO, val=0.346, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.11, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.43, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.066, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.FOLD_MASS_COEFFICIENT, val=0.2, units="unitless" - ) - # self.prob.model.set_input_defaults( - # Aircraft.Strut.AREA, 523.337, units="ft**2" - # ) # had to calculate by hand - self.prob.model.set_input_defaults( - Aircraft.Strut.MASS_COEFFICIENT, 0.238, units="unitless" - ) - - self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - - self.prob.setup(check=False, force_alloc_complex=True) - - def test_case1(self): - - self.prob.run_model() - - tol = 5e-4 - # size values: - assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) - assert_near_equal(self.prob["size.fuselage.cabin_len"], 93.9, tol) - assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - - assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 13.59, tol) - assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 13.15, tol) - assert_near_equal( - self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1068, tol - ) # note:precision came from running code on my own and printing it out - - assert_near_equal( - self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.381, tol - ) # note, printed out manually because calculated differently in output subroutine - assert_near_equal( - self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 20.056, tol - ) # note, printed out manually because calculated differently in output subroutine - assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 13.19, tol) - - # fixed mass values: - assert_near_equal( - self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 4123.4, tol - # self.prob["fixed_mass.main_gear_mass"], 4123.4, tol - ) # note:printed out from GASP code - - assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 10453.0, tol) - assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1704.0/2, tol) - - # wing values: - assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 14040, tol) - assert_near_equal(self.prob[Aircraft.Wing.MASS], 18031, tol) - - # fuel values: - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 60410.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 59372.3 - - assert_near_equal( - self.prob["fuel_mass.fus_mass_full"], 97697.5, tol - ) # note:printed out from GASP code - assert_near_equal( - self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1954.3, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1886.0 - - assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 43660.4, tol) - assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 14657.4, tol) - - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS_REQUIRED], 29610.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 28572.3 - assert_near_equal( - self.prob[Aircraft.Propulsion.MASS], 14111.2, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 14043.0 - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS], 29610.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 28572.0 - assert_near_equal( - self.prob["fuel_mass.fuel_mass_min"], 13640.9, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 12602.3 - assert_near_equal( - self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 651.15, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 628.3 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1207.68, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1186.9 - assert_near_equal( - self.prob[Aircraft.Design.OPERATING_MASS], 82689.1, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 83728.0 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 30800.0, tol - ) # note:printed out from GASP code - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 31051.6, tol - ) - assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 31051.6, tol) - assert_near_equal(self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol) - assert_near_equal( - self.prob["fuel_mass.body_tank.extra_fuel_volume"], 30.3942, 0.009 - ) # note: higher tol because slightly different from GASP value, likely numerical issues, printed out from the GASP code, #modified from GASP value to account for updated crew mass. GASP value is 7.5568 - assert_near_equal( - self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 1520.384, 0.009 - ) # note: higher tol because slightly different from GASP value, likely numerical issues, printed out from the GASP code, #modified from GASP value to account for updated crew mass. GASP value is 378.0062 - - partial_data = self.prob.check_partials(out_stream=None, method="cs") - assert_check_partials(partial_data, atol=3e-9, rtol=6e-11) - - -class MassSummationTestCase9(unittest.TestCase): - """ - This is the electrified Trans-sonic Truss-Braced Wing V3.6 test case - All values are from V3.6 output, hand calculated from the output, or were printed out after running the code manually. - Values not directly from the output are labeled as such. - """ - - def setUp(self): - - options = get_option_defaults() - options.set_val(Aircraft.Wing.HAS_FOLD, val=True, units='unitless') - options.set_val(Aircraft.Wing.HAS_STRUT, val=True, units='unitless') - options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') - options.set_val(Mission.Design.CRUISE_ALTITUDE, val=43000, units='ft') - options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') - options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, - val=True, units='unitless') - options.set_val(Aircraft.LandingGear.FIXED_GEAR, - val=False, units='unitless') - options.set_val(Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, - val=True, units='unitless') - options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, - val=200, units="lbm") - options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) - options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") - options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) - options.set_val(Aircraft.Fuselage.SEAT_PITCH, 44.2, units="inch") - options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - - self.prob = om.Problem() - self.prob.model.add_subsystem( - "size", - SizeGroup( - aviary_options=options, - ), - promotes_inputs=["aircraft:*", "mission:*"], - promotes_outputs=[ - "aircraft:*", - ], - ) - self.prob.model.add_subsystem( - "GASP_mass", - MassPremission( - aviary_options=options, - ), - promotes=["*"], - ) - - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MOMENT_RATIO, val=0.13067, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.ASPECT_RATIO, val=4.025, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MOMENT_RATIO, 3.0496, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.REFERENCE_DIAMETER, 8.425, units="ft") - # self.prob.model.set_input_defaults( - # Aircraft.Engine.REFERENCE_SLS_THRUST, 28620, units="lbf" - # ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALE_FACTOR, 0.73934, units='unitless' - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.2095, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Nacelle.FINENESS, 1.569, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 6.85, units="ft" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.TAIL_FINENESS, 1.18, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.WETTED_AREA_SCALER, 1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.LOADING, val=96.10, units="lbf/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" - ) - - self.prob.model.set_input_defaults( - Aircraft.APU.MASS, val=1014.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.085, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.105, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Avionics.MASS, val=1504.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.AntiIcing.MASS, val=126.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Furnishings.MASS, val=9114.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=0.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=10.0, units="lbm") - self.prob.model.set_input_defaults( - Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - - self.prob.model.set_input_defaults( - Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALED_SLS_THRUST, val=23750.0, units="lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.SCALE_FACTOR, 0.82984, units='unitless' - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.WING_FUEL_FRACTION, 0.5936, units="unitless" - ) - self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=22.47, units="deg") - self.prob.model.set_input_defaults( - Aircraft.Wing.MOUNTING_TYPE, val=.1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.ASPECT_RATIO, val=19.565, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Strut.ATTACHMENT_LOCATION, val=118.0, units="ft" - ) - self.prob.model.set_input_defaults( - Aircraft.CrewPayload.CARGO_MASS, val=15970.0, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SPECIFIC, val=0.2744, units="lbm/lbf" - ) - self.prob.model.set_input_defaults( - Aircraft.Nacelle.MASS_SPECIFIC, val=2.5, units="lbm/ft**2" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.163, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Engine.WING_LOCATIONS, val=0.2143, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.ASPECT_RATIO, val=0.825, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.SWEEP, val=0, units='deg' - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.2076, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.2587, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.11, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" - ) # Based onlarge single aisle 1for updated flaps mass model - self.prob.model.set_input_defaults( - Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" - ) # Based on large single aisle 1 for updated flaps mass model - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.5936, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=30.0, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=1, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MASS_COEFFICIENT, val=0.03390, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_MARGIN, val=0.0, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.060, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_COEFFICIENT, val=96.94, units="unitless" - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' - ) - self.prob.model.set_input_defaults( - "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' - ) - self.prob.model.set_input_defaults( - Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") - self.prob.model.set_input_defaults( - Mission.Design.GROSS_MASS, val=166100.0, units="lbm" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.MASS_COEFFICIENT, val=78.94, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.TAPER_RATIO, val=0.346, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.11, units="unitless" - ) - - self.prob.model.set_input_defaults( - Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.43, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.066, units="unitless" - ) - self.prob.model.set_input_defaults( - Aircraft.Wing.FOLD_MASS_COEFFICIENT, val=0.2, units="unitless" - ) - # self.prob.model.set_input_defaults( - # Aircraft.Strut.AREA, 553.1, units="ft**2" - # ) - self.prob.model.set_input_defaults( - Aircraft.Strut.MASS_COEFFICIENT, 0.238, units="unitless" - ) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.motor_power", 830, units="kW" - ) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.motor_voltage", 850, units="V" - ) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.max_amp_per_wire", 260, units="A" - ) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.safety_factor", 1, units="unitless" - ) # (not in this GASP code) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.wire_area", 0.0015, units="ft**2" - ) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.rho_wire", 565, units="lbm/ft**3" - ) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.battery_energy", 6077, units="MJ" - ) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.motor_eff", 0.98, units="unitless" - ) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.inverter_eff", 0.99, units="unitless" - ) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.transmission_eff", 0.975, units="unitless" - ) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.battery_eff", 0.975, units="unitless" - ) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.rho_battery", 0.5, units="kW*h/kg" - ) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.motor_spec_mass", 4, units="hp/lbm" - ) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.inverter_spec_mass", 12, units="kW/kg" - ) - self.prob.model.set_input_defaults( - "fixed_mass.augmentation.TMS_spec_mass", 0.125, units="lbm/kW" - ) - - self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - - self.prob.setup(check=False, force_alloc_complex=True) - - def test_case1(self): - - self.prob.run_model() - - tol = 5e-4 - # size values: - assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) - assert_near_equal(self.prob["size.fuselage.cabin_len"], 93.9, tol) - assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - - assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 13.97, tol) - assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 13.53, tol) - assert_near_equal( - self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1068, tol - ) # (printed out from GASP code to get better precision) - - assert_near_equal( - self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.644, tol - ) # (printed out from GASP code) - assert_near_equal( - self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 20.618, tol - ) # (printed out from GASP code) - assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.56, tol) - - # fixed mass values: - assert_near_equal( - self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 4786.2, tol - ) # (printed out from GASP code) - - assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 13034.0, tol) - assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 2124.5/2, tol) - - # wing values: - assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15895, tol) - assert_near_equal(self.prob[Aircraft.Wing.MASS], 20461.7, tol) - - # fuel values: - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 64594.0, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 63707.6 - - assert_near_equal( - self.prob["fuel_mass.fus_mass_full"], 108803.9, tol - ) # (printed out from GASP code), #modified from GASP value to account for updated crew mass. GASP value is 108754.4 - assert_near_equal( - self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 2027.6, 0.00055 - ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 1974.5 - - assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 49582, tol) - assert_near_equal( - self.prob[Aircraft.Fuselage.MASS], 16313.0, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 16436.0 - - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS_REQUIRED], 33794.0, 0.00058 - ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 32907.6 - assert_near_equal( - self.prob[Aircraft.Propulsion.MASS], 26565.2, 0.00054 - ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 26527.0 - assert_near_equal( - self.prob[Mission.Design.FUEL_MASS], 33794.0, 0.00056 - ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 32908 - assert_near_equal( - self.prob["fuel_mass.fuel_mass_min"], 17824.0, 0.0012 - ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 16937.6 - assert_near_equal( - self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 675.58, 0.00051 - ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 657.9 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1291.31, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 1273.6 - assert_near_equal( - self.prob[Aircraft.Design.OPERATING_MASS], 101506.0, tol - ) # modified from GASP value to account for updated crew mass. GASP value is 102392.0 - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 30800.0, tol - ) # (printed out from GASP code) - assert_near_equal( - self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 35042.1, tol - ) - assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 35042.1, tol) - assert_near_equal(self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol) - assert_near_equal( - self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol - ) - assert_near_equal( - self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol - ) - - assert_near_equal(self.prob[Aircraft.Electrical.HYBRID_CABLE_LENGTH], 65.6, tol) - assert_near_equal( - self.prob["fixed_mass.aug_mass"], 9394.3, 0.0017 - ) # slightly above tol, due to non-integer number of wires - - partial_data = self.prob.check_partials(out_stream=None, method="cs") - assert_check_partials(partial_data, atol=3e-9, rtol=6e-11) +# class MassSummationTestCase2(unittest.TestCase): +# """ +# This is the large single aisle 1 V3.5 test case. +# All values are from V3.5 output (or hand calculated from the output, and these cases +# are specified). +# """ + +# def setUp(self): + +# options = get_option_defaults() +# options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, +# val=False, units='unitless') +# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') +# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') +# options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') +# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.LandingGear.FIXED_GEAR, +# val=False, units='unitless') +# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, +# val=200, units="lbm") +# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) +# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") +# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) +# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") +# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + +# self.prob = om.Problem() +# self.prob.model.add_subsystem( +# "size", +# SizeGroup( +# aviary_options=options, +# ), +# promotes_inputs=["aircraft:*", "mission:*"], +# promotes_outputs=[ +# "aircraft:*", +# ], +# ) +# self.prob.model.add_subsystem( +# "GASP_mass", +# MassPremission( +# aviary_options=options, +# ), +# promotes=["*"], +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" +# ) +# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Mission.Design.GROSS_MASS, val=175400, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.LOADING, val=128, units="lbf/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" +# ) +# # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") +# # self.prob.model.set_input_defaults( +# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" +# # ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless') +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.FINENESS, 2, units="unitless") + +# self.prob.model.set_input_defaults( +# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.SWEEP, val=0, units='deg' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" +# ) # Based onlarge single aisle 1for updated flaps mass model +# self.prob.model.set_input_defaults( +# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" +# ) # Based onlarge single aisle 1for updated flaps mass model +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.APU.MASS, val=928.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Avionics.MASS, val=1959.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.AntiIcing.MASS, val=551.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Furnishings.MASS, val=11192.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_MARGIN, val=0, units="unitless") + +# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + +# self.prob.setup(check=False, force_alloc_complex=True) + +# def test_case1(self): + +# self.prob.run_model() + +# tol = 5e-4 +# # size values: +# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) +# assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) +# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + +# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 17.49, tol) +# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.41, tol) +# assert_near_equal( +# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1397, tol +# ) # not exact GASP value from the output file, likely due to rounding error + +# # note: this is not the value in the GASP output, because the output calculates +# # them differently. This was calculated by hand. +# assert_near_equal( +# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.578314120156815, tol +# ) +# # note: this is not the value in the GASP output, because the output calculates +# # them differently. This was calculated by hand. +# assert_near_equal( +# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 16.828924591320984, tol +# ) +# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) + +# # fixed mass values: +# assert_near_equal( +# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.35, tol +# ) # calculated by hand + +# # note: fixed_mass.tail.loc_MAC_vtail not included in v3.5 + +# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) +# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) + +# # wing values: +# assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15653, tol) + +# # fuel values: +# # modified from GASP value to account for updated crew mass. GASP value is +# # 79147.2 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 79002.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 79147.2 + +# # calculated by hand, #modified from GASP value to account for updated crew +# # mass. GASP value is 102321.45695930265 +# assert_near_equal( +# self.prob["fuel_mass.fus_mass_full"], 102359.6, tol +# ) +# # modified from GASP value to account for updated crew mass. GASP value is +# # 1769 +# assert_near_equal( +# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1763.1, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1769 + +# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 50186, tol) +# assert_near_equal( +# self.prob[Aircraft.Fuselage.MASS], 18663, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 18787 + +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 43002.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 43147.2 +# assert_near_equal( +# self.prob[Aircraft.Propulsion.MASS], 16133.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 16140 +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS], 43002.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 43147 +# assert_near_equal( +# self.prob["fuel_mass.fuel_mass_min"], 32962.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 33107.2 +# assert_near_equal( +# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 859.68, tol +# ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 862.5603807559726 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1579.36, tol +# ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 1582.2403068511774 +# assert_near_equal( +# self.prob[Aircraft.Design.OPERATING_MASS], 96397.1, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 96253.0 +# # extra_fuel_mass calculated differently in this version, so fuel_mass.fuel_and_oem.payload_mass_max_fuel test not included +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 55725.1, tol +# ) +# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 55725.1, tol) +# assert_near_equal( +# self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol +# ) # always zero when no body tank +# assert_near_equal( +# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol +# ) # always zero when no body tank +# assert_near_equal( +# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol +# ) # always zero when no body tank + +# partial_data = self.prob.check_partials(out_stream=None, method="cs") +# assert_check_partials(partial_data, atol=2e-10, rtol=1e-12) + + +# class MassSummationTestCase3(unittest.TestCase): +# """ +# This is thelarge single aisle 1V3.6 test case with a fuel margin of 0%, a wing loading of 128 psf, and a SLS thrust of 29500 lbf +# All values are from V3.6 output (or hand calculated from the output, and these cases are specified). +# """ + +# def setUp(self): + +# options = get_option_defaults() +# options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, +# val=False, units='unitless') +# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') +# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') +# options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') +# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.LandingGear.FIXED_GEAR, +# val=False, units='unitless') +# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, +# val=200, units="lbm") +# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) +# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") +# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) +# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") +# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + +# self.prob = om.Problem() +# self.prob.model.add_subsystem( +# "size", +# SizeGroup( +# aviary_options=options, +# ), +# promotes_inputs=["aircraft:*", "mission:*"], +# promotes_outputs=[ +# "aircraft:*", +# ], +# ) +# self.prob.model.add_subsystem( +# "GASP_mass", +# MassPremission( +# aviary_options=options, +# ), +# promotes=["*"], +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" +# ) +# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Mission.Design.GROSS_MASS, val=175400, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.LOADING, val=128, units="lbf/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" +# ) +# # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") +# # self.prob.model.set_input_defaults( +# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" +# # ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.FINENESS, 2, units="unitless") + +# self.prob.model.set_input_defaults( +# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.SWEEP, val=0, units='deg' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" +# ) # Based onlarge single aisle 1for updated flaps mass model +# self.prob.model.set_input_defaults( +# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" +# ) # Based on large single aisle 1 for updated flaps mass model +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.APU.MASS, val=928.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Avionics.MASS, val=1959.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.AntiIcing.MASS, val=551.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Furnishings.MASS, val=11192.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_MARGIN, val=0, units="unitless") + +# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + +# self.prob.setup(check=False, force_alloc_complex=True) + +# def test_case1(self): + +# self.prob.run_model() + +# tol = 5e-4 +# # size values: +# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) +# assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) +# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + +# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 17.49, tol) +# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.41, tol) +# assert_near_equal( +# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1397, tol +# ) # not exact value, likely due to rounding error + +# assert_near_equal( +# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.578314120156815, tol +# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. +# assert_near_equal( +# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 16.828924591320984, tol +# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. +# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) + +# # fixed mass values: +# assert_near_equal( +# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol +# ) # calculated by hand + +# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) +# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) + +# # wing values: +# assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15653, tol) + +# # fuel values: +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 79002.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 79147.2 + +# assert_near_equal( +# self.prob["fuel_mass.fus_mass_full"], 102359.6, tol +# ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 102321.45695930265 +# assert_near_equal( +# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1763.1, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 102321.45695930265 + +# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 50186, tol) +# assert_near_equal( +# self.prob[Aircraft.Fuselage.MASS], 18663, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 18787 + +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 43002.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 43147.2 +# assert_near_equal( +# self.prob[Aircraft.Propulsion.MASS], 16133.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 16140 +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS], 43002.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 43147 +# assert_near_equal( +# self.prob["fuel_mass.fuel_mass_min"], 32962.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 33107.2 +# assert_near_equal( +# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 859.68, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 862.6 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1579.36, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1582.2 +# assert_near_equal( +# self.prob[Aircraft.Design.OPERATING_MASS], 96397.1, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 96253.0 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 36000, tol +# ) # note: value came from running the GASP code on my own and printing it out +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 55725.1, tol +# ) +# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 55725.1, tol) +# assert_near_equal( +# self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol +# ) # always zero when no body tank +# assert_near_equal( +# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol +# ) # always zero when no body tank +# assert_near_equal( +# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol +# ) # always zero when no body tank + +# partial_data = self.prob.check_partials(out_stream=None, method="cs") +# assert_check_partials(partial_data, atol=2e-10, rtol=1e-12) + + +# class MassSummationTestCase4(unittest.TestCase): +# """ +# This is the large single aisle 1V3.6 test case with a fuel margin of 10%, a wing loading of 128 psf, and a SLS thrust of 29500 lbf +# All values are from V3.6 output (or hand calculated from the output, and these cases are specified). +# """ + +# def setUp(self): + +# options = get_option_defaults() +# options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, +# val=False, units='unitless') +# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') +# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') +# options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') +# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.LandingGear.FIXED_GEAR, +# val=False, units='unitless') +# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, +# val=200, units="lbm") +# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) +# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") +# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) +# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") +# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + +# self.prob = om.Problem() +# self.prob.model.add_subsystem( +# "size", +# SizeGroup( +# aviary_options=options, +# ), +# promotes_inputs=["aircraft:*", "mission:*"], +# promotes_outputs=[ +# "aircraft:*", +# ], +# ) +# self.prob.model.add_subsystem( +# "GASP_mass", +# MassPremission( +# aviary_options=options, +# ), +# promotes=["*"], +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" +# ) +# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Mission.Design.GROSS_MASS, val=175400, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.LOADING, val=128, units="lbf/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" +# ) +# # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") +# # self.prob.model.set_input_defaults( +# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" +# # ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.FINENESS, 2, units="unitless") + +# self.prob.model.set_input_defaults( +# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.SWEEP, val=0, units='deg' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" +# ) # Based onlarge single aisle 1for updated flaps mass model +# self.prob.model.set_input_defaults( +# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" +# ) # Based on large single aisle 1 for updated flaps mass model +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.APU.MASS, val=928.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Avionics.MASS, val=1959.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.AntiIcing.MASS, val=551.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Furnishings.MASS, val=11192.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_MARGIN, val=10, units="unitless" +# ) + +# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + +# self.prob.setup(check=False, force_alloc_complex=True) + +# def test_case1(self): + +# self.prob.run_model() + +# tol = 5e-4 +# # size values: +# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) +# assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) +# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + +# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 17.49, tol) +# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.41, tol) +# assert_near_equal( +# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1397, tol +# ) # slightly different from GASP value, likely numerical error + +# assert_near_equal( +# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.578314120156815, tol +# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. +# assert_near_equal( +# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 16.828924591320984, tol +# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. +# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) + +# # fixed mass values: +# assert_near_equal( +# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol +# ) # calculated by hand + +# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) +# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) + +# # wing values: +# assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15653, tol) + +# # fuel values: +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 78823.0, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 78966.7 + +# assert_near_equal( +# self.prob["fuel_mass.fus_mass_full"], 102541.4, tol +# ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 102501.95695930265 +# assert_near_equal( +# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1931.3, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1938 + +# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 50198, tol) +# assert_near_equal( +# self.prob[Aircraft.Fuselage.MASS], 18675, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 18799 + +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 42823.0, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 42966.7 +# assert_near_equal( +# self.prob[Aircraft.Propulsion.MASS], 16302.1, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 16309 +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS], 42823.0, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 42967 +# assert_near_equal( +# self.prob["fuel_mass.fuel_mass_min"], 32783.0, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 32926.7 +# assert_near_equal( +# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 941.69, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 944.8 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1575.76, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1578.6 +# assert_near_equal( +# self.prob[Aircraft.Design.OPERATING_MASS], 96577.0, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 96433.0 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 36000, tol +# ) # note: value came from running the GASP code on my own and printing it out +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 55725.1, tol +# ) +# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 55725.1, tol) +# assert_near_equal( +# self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol +# ) # always zero when no body tank +# assert_near_equal( +# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol +# ) # always zero when no body tank +# assert_near_equal( +# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol +# ) # always zero when no body tank + +# partial_data = self.prob.check_partials(out_stream=None, method="cs") +# assert_check_partials(partial_data, atol=2e-10, rtol=1e-12) + + +# class MassSummationTestCase5(unittest.TestCase): +# """ +# This is thelarge single aisle 1V3.6 test case with a fuel margin of 0%, a wing loading of 150 psf, and a SLS thrust of 29500 lbf +# All values are from V3.6 output (or hand calculated from the output, and these cases are specified). +# """ + +# def setUp(self): + +# options = get_option_defaults() +# options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, +# val=False, units='unitless') +# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') +# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') +# options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') +# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.LandingGear.FIXED_GEAR, +# val=False, units='unitless') +# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, +# val=200, units="lbm") +# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) +# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") +# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) +# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") +# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + +# self.prob = om.Problem() +# self.prob.model.add_subsystem( +# "size", +# SizeGroup( +# aviary_options=options, +# ), +# promotes_inputs=["aircraft:*", "mission:*"], +# promotes_outputs=[ +# "aircraft:*", +# ], +# ) +# self.prob.model.add_subsystem( +# "GASP_mass", +# MassPremission( +# aviary_options=options, +# ), +# promotes=["*"], +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" +# ) +# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Mission.Design.GROSS_MASS, val=175400, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.LOADING, val=150, units="lbf/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" +# ) +# # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") +# # self.prob.model.set_input_defaults( +# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" +# # ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.FINENESS, 2, units="unitless") + +# self.prob.model.set_input_defaults( +# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.SWEEP, val=0, units='deg' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" +# ) # Based onlarge single aisle 1for updated flaps mass model +# self.prob.model.set_input_defaults( +# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" +# ) # Based on large single aisle 1 for updated flaps mass model +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.APU.MASS, val=928.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Avionics.MASS, val=1959.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.AntiIcing.MASS, val=551.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Furnishings.MASS, val=11192.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_MARGIN, val=0.0, units="unitless" +# ) + +# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + +# self.prob.setup(check=False, force_alloc_complex=True) + +# def test_case1(self): + +# self.prob.run_model() + +# tol = 5e-4 +# # size values: +# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) +# assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) +# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + +# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 16.16, tol) +# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 15.1, tol) +# assert_near_equal( +# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1394, tol +# ) # slightly different from GASP value, likely rounding error + +# assert_near_equal( +# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 8.848695928254141, tol +# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. +# assert_near_equal( +# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 15.550266681026597, tol +# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. +# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) + +# # fixed mass values: +# assert_near_equal( +# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol +# # self.prob["fixed_mass.main_gear_mass"], 6384.349999999999, tol +# ) # calculated by hand + +# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) +# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) + +# # wing values: +# assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 14631, tol) + +# # fuel values: +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 80475.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 81424.8 + +# assert_near_equal( +# self.prob["fuel_mass.fus_mass_full"], 102510.7, tol +# ) # calculated by hand +# assert_near_equal( +# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1823.4, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1862 + +# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 48941, tol) +# assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 18675, tol) + +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 44472.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 45424.8 +# assert_near_equal( +# self.prob[Aircraft.Propulsion.MASS], 16194.2, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 16233 +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS], 44472.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 45425 +# assert_near_equal( +# self.prob["fuel_mass.fuel_mass_min"], 34432.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 35384.8 +# assert_near_equal( +# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 889.06, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 908.1 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1608.74, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1627.8 +# assert_near_equal( +# self.prob[Aircraft.Design.OPERATING_MASS], 94927.1, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 93975 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 35380.5, tol +# ) # note: value came from running the GASP code on my own and printing it out, #modified from GASP value to account for updated crew mass. GASP value is 34427.4 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 43852.1, tol +# ) +# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 43852.1, tol) +# assert_near_equal( +# self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 620.739, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1572.6 +# assert_near_equal( +# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 12.4092, tol +# ) # slightly different from GASP value, likely a rounding error, #modified from GASP value to account for updated crew mass. GASP value is 31.43 +# assert_near_equal( +# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 620.736, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1572.6 + +# partial_data = self.prob.check_partials(out_stream=None, method="cs") +# assert_check_partials(partial_data, atol=3e-10, rtol=1e-12) + + +# class MassSummationTestCase6(unittest.TestCase): +# """ +# This is thelarge single aisle 1V3.6 test case with a fuel margin of 10%, a wing loading of 150 psf, and a SLS thrust of 29500 lbf +# All values are from V3.6 output (or hand calculated from the output, and these cases are specified). +# """ + +# def setUp(self): + +# options = get_option_defaults() +# options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, +# val=False, units='unitless') +# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') +# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') +# options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') +# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.LandingGear.FIXED_GEAR, +# val=False, units='unitless') +# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, +# val=200, units="lbm") +# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) +# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") +# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) +# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") +# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + +# self.prob = om.Problem() +# self.prob.model.add_subsystem( +# "size", +# SizeGroup( +# aviary_options=options, +# ), +# promotes_inputs=["aircraft:*", "mission:*"], +# promotes_outputs=[ +# "aircraft:*", +# ], +# ) +# self.prob.model.add_subsystem( +# "GASP_mass", +# MassPremission( +# aviary_options=options, +# ), +# promotes=["*"], +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" +# ) +# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Mission.Design.GROSS_MASS, val=175400, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.LOADING, val=150, units="lbf/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" +# ) +# # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") +# # self.prob.model.set_input_defaults( +# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" +# # ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.FINENESS, 2, units="unitless") + +# self.prob.model.set_input_defaults( +# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.SWEEP, val=0, units='deg' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" +# ) # Based onlarge single aisle 1for updated flaps mass model +# self.prob.model.set_input_defaults( +# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" +# ) # Based onlarge single aisle 1for updated flaps mass model +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.APU.MASS, val=928.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Avionics.MASS, val=1959.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.AntiIcing.MASS, val=551.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Furnishings.MASS, val=11192.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_MARGIN, val=10.0, units="unitless" +# ) + +# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + +# self.prob.setup(check=False, force_alloc_complex=True) + +# def test_case1(self): + +# self.prob.run_model() + +# tol = 5e-4 +# # size values: +# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) +# assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) +# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + +# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 16.16, tol) +# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 15.1, tol) +# assert_near_equal( +# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1394, tol +# ) # note: not exact GASP value, likely rounding error + +# assert_near_equal( +# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 8.848695928254141, tol +# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. +# assert_near_equal( +# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 15.550266681026597, tol +# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. +# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) + +# # fixed mass values: +# assert_near_equal( +# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol +# # self.prob["fixed_mass.main_gear_mass"], 6384.349999999999, tol +# ) # calculated by hand + +# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) +# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) + +# # wing values: +# assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 14631, tol) + +# # fuel values: +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 80029.2, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 80982.7 + +# assert_near_equal( +# self.prob["fuel_mass.fus_mass_full"], 106913.6, tol +# ) # calculated by hand +# assert_near_equal( +# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1985.7, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 2029 + +# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 49222, tol) +# assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 18956, tol) + +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 44029.2, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 44982.7 +# assert_near_equal( +# self.prob[Aircraft.Propulsion.MASS], 16356.5, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 16399 +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS], 44029.2, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 44982.7 +# assert_near_equal( +# self.prob["fuel_mass.fuel_mass_min"], 33989.2, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 34942.7 +# assert_near_equal( +# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 968.21, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 989.2 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1599.87, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1618.9 +# assert_near_equal( +# self.prob[Aircraft.Design.OPERATING_MASS], 95370.8, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 94417 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 35823.0, tol +# ) # note: value came from running the GASP code on my own and printing it out, #modified from GASP value to account for updated crew mass. GASP value is 34879.2 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 43852.1, tol +# ) +# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 43852.1, tol) +# assert_near_equal( +# self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 177.042, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1120.9 +# assert_near_equal( +# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 91.5585, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 112.3 +# assert_near_equal( +# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 4579.96, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 5618.2 + +# partial_data = self.prob.check_partials(out_stream=None, method="cs") +# assert_check_partials(partial_data, atol=3e-10, rtol=1e-12) + + +# class MassSummationTestCase7(unittest.TestCase): +# """ +# This is the Advanced Tube and Wing V3.6 test case +# All values are from V3.6 output, hand calculated from the output, or were printed out after running the code manually. +# Values not directly from the output are labeled as such. +# """ + +# def setUp(self): + +# options = get_option_defaults() +# options.set_val(Aircraft.Wing.HAS_FOLD, val=True, units='unitless') +# options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, +# val=False, units='unitless') +# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') +# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37100, units='ft') +# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.LandingGear.FIXED_GEAR, +# val=False, units='unitless') +# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, +# val=200, units="lbm") +# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) +# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") +# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) +# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") +# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + +# self.prob = om.Problem() +# self.prob.model.add_subsystem( +# "size", +# SizeGroup( +# aviary_options=options, +# ), +# promotes_inputs=["aircraft:*", "mission:*"], +# promotes_outputs=[ +# "aircraft:*", +# ], +# ) +# self.prob.model.add_subsystem( +# "GASP_mass", +# MassPremission( +# aviary_options=options, +# ), +# promotes=["*"], +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.Wing.ASPECT_RATIO, val=11, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" +# ) +# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Mission.Design.GROSS_MASS, val=145388.0, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.LOADING, val=104.50, units="lbf/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALED_SLS_THRUST, val=17000.0, units="lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.WING_FUEL_FRACTION, 0.475, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.09986, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.WETTED_AREA_SCALER, 1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MOMENT_RATIO, 2.1621, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.REFERENCE_DIAMETER, 7.36, units="ft") +# # self.prob.model.set_input_defaults( +# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28620.0, units="lbf" +# # ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALE_FACTOR, 0.594, units='unitless' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.2095, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.FINENESS, 1.715, units="unitless") +# self.prob.model.set_input_defaults(Aircraft.Wing.FOLDED_SPAN, 118, units="ft") + +# self.prob.model.set_input_defaults( +# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CARGO_MASS, val=15970.0, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.SWEEP, val=0, units='deg' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" +# ) # Based onlarge single aisle 1for updated flaps mass model +# self.prob.model.set_input_defaults( +# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" +# ) # Based on large single aisle 1 for updated flaps mass model +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SPECIFIC, val=0.2355, units="lbm/lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.165, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.APU.MASS, val=1014.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.085, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.105, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Avionics.MASS, val=1504.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.AntiIcing.MASS, val=126.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Furnishings.MASS, val=9114.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=0.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=10.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_COEFFICIENT, val=85, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.FOLD_MASS_COEFFICIENT, val=0.2, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' +# ) # note: not actually defined in program, likely an error +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_MARGIN, val=10.0, units="unitless" +# ) + +# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + +# self.prob.setup(check=False, force_alloc_complex=True) + +# def test_case1(self): + +# self.prob.run_model() + +# tol = 5e-4 +# # size values: +# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) +# assert_near_equal(self.prob["size.fuselage.cabin_len"], 61.6, tol) +# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + +# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 16.91, tol) +# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.01, tol) +# assert_near_equal( +# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1132, tol +# ) # slightly different from GASP value, likely a rounding error + +# assert_near_equal( +# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.6498, tol +# # note: value came from running the GASP code on my own and printing it out (GASP output calculates this differently) +# ) +# assert_near_equal( +# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 13.4662, tol +# # note: value came from running the GASP code on my own and printing it out (GASP output calculates this differently) +# ) +# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 11.77, tol) + +# # fixed mass values: +# assert_near_equal( +# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 5219.3076, tol +# # self.prob["fixed_mass.main_gear_mass"], 5219.3076, tol +# ) # note: value came from running the GASP code on my own and printing it out + +# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 8007, tol) +# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1321/2, tol) + +# # wing values: +# assert_near_equal( +# self.prob["wing_mass.isolated_wing_mass"], 13993, tol +# ) # calculated as difference between wing mass and fold mass, not an actual GASP variable + +# # fuel values: +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 63452.2, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 62427.2 + +# assert_near_equal( +# self.prob["fuel_mass.fus_mass_full"], 99396.7, tol +# ) # note: value came from running the GASP code on my own and printing it out +# assert_near_equal( +# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1472.6, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1426 + +# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 45373.4, tol) +# assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 18859.9, tol) + +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 32652.2, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 31627.2 +# assert_near_equal( +# self.prob[Aircraft.Propulsion.MASS], 10800.8, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 10755.0 +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS], 32652.2, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 31627.0 +# assert_near_equal( +# self.prob["fuel_mass.fuel_mass_min"], 16682.2, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 15657.2 +# assert_near_equal( +# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 718.03, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 695.5 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1268.48, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1248.0 +# assert_near_equal( +# self.prob[Aircraft.Design.OPERATING_MASS], 81935.8, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 82961.0 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 30800.0039, tol +# ) # note: value came from running the GASP code on my own and printing it out +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 33892.8, tol +# ) +# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 33892.8, tol) +# assert_near_equal(self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol) +# assert_near_equal( +# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 40.4789, 0.005 +# ) # note: higher tol because slightly different from GASP value, likely numerical issues, #modified from GASP value to account for updated crew mass. GASP value is 17.9 +# assert_near_equal( +# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 2024.70, 0.003 +# ) # note: higher tol because slightly different from GASP value, likely numerical issues, #modified from GASP value to account for updated crew mass. GASP value is 897.2 + +# partial_data = self.prob.check_partials(out_stream=None, method="cs") +# assert_check_partials(partial_data, atol=3e-9, rtol=6e-11) + + +# class MassSummationTestCase8(unittest.TestCase): +# """ +# This is the Trans-sonic Truss-Braced Wing V3.6 test case +# All values are from V3.6 output, hand calculated from the output, or were printed out after running the code manually. +# Values not directly from the output are labeled as such. +# """ + +# def setUp(self): + +# options = get_option_defaults() +# options.set_val(Aircraft.Wing.HAS_FOLD, val=True, units='unitless') +# options.set_val(Aircraft.Wing.HAS_STRUT, val=True, units='unitless') +# options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, +# val=False, units='unitless') +# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') +# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=43000, units='ft') +# options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') +# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.LandingGear.FIXED_GEAR, +# val=False, units='unitless') +# options.set_val(Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, +# val=True, units='unitless') +# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, +# val=200, units="lbm") +# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) +# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") +# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) +# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 44.2, units="inch") +# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + +# self.prob = om.Problem() +# self.prob.model.add_subsystem( +# "size", +# SizeGroup( +# aviary_options=options, +# ), +# promotes_inputs=["aircraft:*", "mission:*"], +# promotes_outputs=[ +# "aircraft:*", +# ], +# ) +# self.prob.model.add_subsystem( +# "GASP_mass", +# MassPremission( +# aviary_options=options, +# ), +# promotes=["*"], +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.13067, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.025, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MOMENT_RATIO, 3.0496, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.REFERENCE_DIAMETER, 7.642, units="ft") +# # self.prob.model.set_input_defaults( +# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28620.0, units="lbf" +# # ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALE_FACTOR, 1.35255, units='unitless' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.2095, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.FINENESS, 1.660, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 6.85, units="ft" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.TAIL_FINENESS, 1.18, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.WETTED_AREA_SCALER, 1.0, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.LOADING, val=87.5, units="lbf/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.APU.MASS, val=1014.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.085, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.105, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Avionics.MASS, val=1504.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.AntiIcing.MASS, val=126.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Furnishings.MASS, val=9114.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=0.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=10.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALED_SLS_THRUST, val=21160.0, units="lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALE_FACTOR, 0.73934, units='unitless' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.WING_FUEL_FRACTION, 0.5625, units="unitless" +# ) +# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=22.47, units="deg") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MOUNTING_TYPE, val=.1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.ASPECT_RATIO, val=19.565, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Strut.ATTACHMENT_LOCATION, val=118, units="ft" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CARGO_MASS, val=15970.0, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SPECIFIC, val=0.2470, units="lbm/lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.MASS_SPECIFIC, val=2.5, units="lbm/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.163, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Engine.WING_LOCATIONS, val=0.2143, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.ASPECT_RATIO, val=0.825, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.SWEEP, val=0, units='deg' +# ) # not in file +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.2076, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.2587, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.11, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" +# ) # Based onlarge single aisle 1for updated flaps mass model +# self.prob.model.set_input_defaults( +# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" +# ) # Based on large single aisle 1 for updated flaps mass model +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.5936, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=30, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" +# ) # not in file +# self.prob.model.set_input_defaults( +# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" +# ) # not in file +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.03390, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_MARGIN, val=10.0, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.060, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_COEFFICIENT, val=89.66, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' +# ) # not in file +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Mission.Design.GROSS_MASS, val=143100.0, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_COEFFICIENT, val=78.94, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.TAPER_RATIO, val=0.346, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.11, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.43, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.066, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.FOLD_MASS_COEFFICIENT, val=0.2, units="unitless" +# ) +# # self.prob.model.set_input_defaults( +# # Aircraft.Strut.AREA, 523.337, units="ft**2" +# # ) # had to calculate by hand +# self.prob.model.set_input_defaults( +# Aircraft.Strut.MASS_COEFFICIENT, 0.238, units="unitless" +# ) + +# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + +# self.prob.setup(check=False, force_alloc_complex=True) + +# def test_case1(self): + +# self.prob.run_model() + +# tol = 5e-4 +# # size values: +# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) +# assert_near_equal(self.prob["size.fuselage.cabin_len"], 93.9, tol) +# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + +# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 13.59, tol) +# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 13.15, tol) +# assert_near_equal( +# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1068, tol +# ) # note:precision came from running code on my own and printing it out + +# assert_near_equal( +# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.381, tol +# ) # note, printed out manually because calculated differently in output subroutine +# assert_near_equal( +# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 20.056, tol +# ) # note, printed out manually because calculated differently in output subroutine +# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 13.19, tol) + +# # fixed mass values: +# assert_near_equal( +# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 4123.4, tol +# # self.prob["fixed_mass.main_gear_mass"], 4123.4, tol +# ) # note:printed out from GASP code + +# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 10453.0, tol) +# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1704.0/2, tol) + +# # wing values: +# assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 14040, tol) +# assert_near_equal(self.prob[Aircraft.Wing.MASS], 18031, tol) + +# # fuel values: +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 60410.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 59372.3 + +# assert_near_equal( +# self.prob["fuel_mass.fus_mass_full"], 97697.5, tol +# ) # note:printed out from GASP code +# assert_near_equal( +# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1954.3, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1886.0 + +# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 43660.4, tol) +# assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 14657.4, tol) + +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 29610.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 28572.3 +# assert_near_equal( +# self.prob[Aircraft.Propulsion.MASS], 14111.2, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 14043.0 +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS], 29610.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 28572.0 +# assert_near_equal( +# self.prob["fuel_mass.fuel_mass_min"], 13640.9, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 12602.3 +# assert_near_equal( +# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 651.15, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 628.3 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1207.68, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1186.9 +# assert_near_equal( +# self.prob[Aircraft.Design.OPERATING_MASS], 82689.1, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 83728.0 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 30800.0, tol +# ) # note:printed out from GASP code +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 31051.6, tol +# ) +# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 31051.6, tol) +# assert_near_equal(self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol) +# assert_near_equal( +# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 30.3942, 0.009 +# ) # note: higher tol because slightly different from GASP value, likely numerical issues, printed out from the GASP code, #modified from GASP value to account for updated crew mass. GASP value is 7.5568 +# assert_near_equal( +# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 1520.384, 0.009 +# ) # note: higher tol because slightly different from GASP value, likely numerical issues, printed out from the GASP code, #modified from GASP value to account for updated crew mass. GASP value is 378.0062 + +# partial_data = self.prob.check_partials(out_stream=None, method="cs") +# assert_check_partials(partial_data, atol=3e-9, rtol=6e-11) + + +# class MassSummationTestCase9(unittest.TestCase): +# """ +# This is the electrified Trans-sonic Truss-Braced Wing V3.6 test case +# All values are from V3.6 output, hand calculated from the output, or were printed out after running the code manually. +# Values not directly from the output are labeled as such. +# """ + +# def setUp(self): + +# options = get_option_defaults() +# options.set_val(Aircraft.Wing.HAS_FOLD, val=True, units='unitless') +# options.set_val(Aircraft.Wing.HAS_STRUT, val=True, units='unitless') +# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') +# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=43000, units='ft') +# options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') +# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, +# val=True, units='unitless') +# options.set_val(Aircraft.LandingGear.FIXED_GEAR, +# val=False, units='unitless') +# options.set_val(Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, +# val=True, units='unitless') +# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, +# val=200, units="lbm") +# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) +# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") +# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) +# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 44.2, units="inch") +# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + +# self.prob = om.Problem() +# self.prob.model.add_subsystem( +# "size", +# SizeGroup( +# aviary_options=options, +# ), +# promotes_inputs=["aircraft:*", "mission:*"], +# promotes_outputs=[ +# "aircraft:*", +# ], +# ) +# self.prob.model.add_subsystem( +# "GASP_mass", +# MassPremission( +# aviary_options=options, +# ), +# promotes=["*"], +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.13067, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.025, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MOMENT_RATIO, 3.0496, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.REFERENCE_DIAMETER, 8.425, units="ft") +# # self.prob.model.set_input_defaults( +# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28620, units="lbf" +# # ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALE_FACTOR, 0.73934, units='unitless' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.2095, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.FINENESS, 1.569, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 6.85, units="ft" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.TAIL_FINENESS, 1.18, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.WETTED_AREA_SCALER, 1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.LOADING, val=96.10, units="lbf/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.APU.MASS, val=1014.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.085, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.105, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Avionics.MASS, val=1504.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.AntiIcing.MASS, val=126.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Furnishings.MASS, val=9114.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=0.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=10.0, units="lbm") +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALED_SLS_THRUST, val=23750.0, units="lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.SCALE_FACTOR, 0.82984, units='unitless' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.WING_FUEL_FRACTION, 0.5936, units="unitless" +# ) +# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=22.47, units="deg") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MOUNTING_TYPE, val=.1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.ASPECT_RATIO, val=19.565, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Strut.ATTACHMENT_LOCATION, val=118.0, units="ft" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.CrewPayload.CARGO_MASS, val=15970.0, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SPECIFIC, val=0.2744, units="lbm/lbf" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Nacelle.MASS_SPECIFIC, val=2.5, units="lbm/ft**2" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.163, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Engine.WING_LOCATIONS, val=0.2143, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.ASPECT_RATIO, val=0.825, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.SWEEP, val=0, units='deg' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.2076, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.2587, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.11, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" +# ) # Based onlarge single aisle 1for updated flaps mass model +# self.prob.model.set_input_defaults( +# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" +# ) # Based on large single aisle 1 for updated flaps mass model +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.5936, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=30.0, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=1, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.03390, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_MARGIN, val=0.0, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.060, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_COEFFICIENT, val=96.94, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' +# ) +# self.prob.model.set_input_defaults( +# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") +# self.prob.model.set_input_defaults( +# Mission.Design.GROSS_MASS, val=166100.0, units="lbm" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.MASS_COEFFICIENT, val=78.94, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.TAPER_RATIO, val=0.346, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.11, units="unitless" +# ) + +# self.prob.model.set_input_defaults( +# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.43, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.066, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# Aircraft.Wing.FOLD_MASS_COEFFICIENT, val=0.2, units="unitless" +# ) +# # self.prob.model.set_input_defaults( +# # Aircraft.Strut.AREA, 553.1, units="ft**2" +# # ) +# self.prob.model.set_input_defaults( +# Aircraft.Strut.MASS_COEFFICIENT, 0.238, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.motor_power", 830, units="kW" +# ) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.motor_voltage", 850, units="V" +# ) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.max_amp_per_wire", 260, units="A" +# ) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.safety_factor", 1, units="unitless" +# ) # (not in this GASP code) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.wire_area", 0.0015, units="ft**2" +# ) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.rho_wire", 565, units="lbm/ft**3" +# ) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.battery_energy", 6077, units="MJ" +# ) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.motor_eff", 0.98, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.inverter_eff", 0.99, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.transmission_eff", 0.975, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.battery_eff", 0.975, units="unitless" +# ) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.rho_battery", 0.5, units="kW*h/kg" +# ) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.motor_spec_mass", 4, units="hp/lbm" +# ) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.inverter_spec_mass", 12, units="kW/kg" +# ) +# self.prob.model.set_input_defaults( +# "fixed_mass.augmentation.TMS_spec_mass", 0.125, units="lbm/kW" +# ) + +# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + +# self.prob.setup(check=False, force_alloc_complex=True) + +# def test_case1(self): + +# self.prob.run_model() + +# tol = 5e-4 +# # size values: +# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) +# assert_near_equal(self.prob["size.fuselage.cabin_len"], 93.9, tol) +# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + +# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 13.97, tol) +# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 13.53, tol) +# assert_near_equal( +# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1068, tol +# ) # (printed out from GASP code to get better precision) + +# assert_near_equal( +# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.644, tol +# ) # (printed out from GASP code) +# assert_near_equal( +# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 20.618, tol +# ) # (printed out from GASP code) +# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.56, tol) + +# # fixed mass values: +# assert_near_equal( +# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 4786.2, tol +# ) # (printed out from GASP code) + +# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 13034.0, tol) +# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 2124.5/2, tol) + +# # wing values: +# assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15895, tol) +# assert_near_equal(self.prob[Aircraft.Wing.MASS], 20461.7, tol) + +# # fuel values: +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 64594.0, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 63707.6 + +# assert_near_equal( +# self.prob["fuel_mass.fus_mass_full"], 108803.9, tol +# ) # (printed out from GASP code), #modified from GASP value to account for updated crew mass. GASP value is 108754.4 +# assert_near_equal( +# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 2027.6, 0.00055 +# ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 1974.5 + +# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 49582, tol) +# assert_near_equal( +# self.prob[Aircraft.Fuselage.MASS], 16313.0, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 16436.0 + +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 33794.0, 0.00058 +# ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 32907.6 +# assert_near_equal( +# self.prob[Aircraft.Propulsion.MASS], 26565.2, 0.00054 +# ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 26527.0 +# assert_near_equal( +# self.prob[Mission.Design.FUEL_MASS], 33794.0, 0.00056 +# ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 32908 +# assert_near_equal( +# self.prob["fuel_mass.fuel_mass_min"], 17824.0, 0.0012 +# ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 16937.6 +# assert_near_equal( +# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 675.58, 0.00051 +# ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 657.9 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1291.31, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 1273.6 +# assert_near_equal( +# self.prob[Aircraft.Design.OPERATING_MASS], 101506.0, tol +# ) # modified from GASP value to account for updated crew mass. GASP value is 102392.0 +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 30800.0, tol +# ) # (printed out from GASP code) +# assert_near_equal( +# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 35042.1, tol +# ) +# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 35042.1, tol) +# assert_near_equal(self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol) +# assert_near_equal( +# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol +# ) +# assert_near_equal( +# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol +# ) + +# assert_near_equal(self.prob[Aircraft.Electrical.HYBRID_CABLE_LENGTH], 65.6, tol) +# assert_near_equal( +# self.prob["fixed_mass.aug_mass"], 9394.3, 0.0017 +# ) # slightly above tol, due to non-integer number of wires + +# partial_data = self.prob.check_partials(out_stream=None, method="cs") +# assert_check_partials(partial_data, atol=3e-9, rtol=6e-11) if __name__ == "__main__": From 265a5984deaea3c0d32fc98b9300dfeffc3dcd67 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 26 Sep 2024 09:33:57 -0400 Subject: [PATCH 073/113] assumed all old flops and leaps names with conflicts between design vs. as-flow were design values --- aviary/variable_info/variable_meta_data.py | 130 ++++++++++----------- 1 file changed, 65 insertions(+), 65 deletions(-) diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index 8fcb0f326..be75473e2 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -621,64 +621,6 @@ # TODO: Set initial defaults better # from aviary.utils.aviary_values import AviaryValues -add_meta_data( - Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, - meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": 'WTIN.NPB', # ['&DEFINE.WTIN.NPB', 'WTS.NPB'], - "LEAPS1": 'aircraft.inputs.L0_crew_and_payload.business_class_count' - }, - units='unitless', - desc='number of business class passengers that the aircraft is designed to accommodate', - types=int, - option=True, - default_value=0, # AviaryValues.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS), -) - -add_meta_data( - Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, - meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": 'WTIN.NPF', # ['&DEFINE.WTIN.NPF', 'WTS.NPF'], - "LEAPS1": 'aircraft.inputs.L0_crew_and_payload.first_class_count' - }, - units='unitless', - desc='number of first class passengers that the aircraft is designed to accommodate', - types=int, - option=True, - default_value=0, -) - -# TODO rename to economy? -add_meta_data( - Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, - meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": 'WTIN.NPT', # ['&DEFINE.WTIN.NPT', 'WTS.NPT'], - "LEAPS1": 'aircraft.inputs.L0_crew_and_payload.tourist_class_count' - }, - units='unitless', - desc='number of tourist class passengers that the aircraft is designed to accommodate', - types=int, - option=True, - default_value=0, -) - -add_meta_data( - Aircraft.CrewPayload.Design.NUM_PASSENGERS, - meta_data=_MetaData, - historical_name={"GASP": 'INGASP.PAX', - "FLOPS": None, # ['CSTDAT.NSV', '~WEIGHT.NPASS', '~WTSTAT.NPASS'], - "LEAPS1": 'aircraft.outputs.L0_crew_and_payload.passenger_count' - }, - units='unitless', - desc='total number of passengers that the aircraft is designed to accommodate', - option=True, - default_value=0, - types=int, -) - - add_meta_data( Aircraft.CrewPayload.BAGGAGE_MASS, meta_data=_MetaData, @@ -762,6 +704,64 @@ default_value=0.7, ) +add_meta_data( + Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": 'WTIN.NPB', # ['&DEFINE.WTIN.NPB', 'WTS.NPB'], + "LEAPS1": 'aircraft.inputs.L0_crew_and_payload.business_class_count' + }, + units='unitless', + desc='number of business class passengers that the aircraft is designed to accommodate', + types=int, + option=True, + default_value=0, # AviaryValues.get_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS), +) + +add_meta_data( + Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": 'WTIN.NPF', # ['&DEFINE.WTIN.NPF', 'WTS.NPF'], + "LEAPS1": 'aircraft.inputs.L0_crew_and_payload.first_class_count' + }, + units='unitless', + desc='number of first class passengers that the aircraft is designed to accommodate', + types=int, + option=True, + default_value=0, +) + +add_meta_data( + Aircraft.CrewPayload.Design.NUM_PASSENGERS, + meta_data=_MetaData, + historical_name={"GASP": 'INGASP.PAX', + "FLOPS": None, # ['CSTDAT.NSV', '~WEIGHT.NPASS', '~WTSTAT.NPASS'], + "LEAPS1": 'aircraft.outputs.L0_crew_and_payload.passenger_count' + }, + units='unitless', + desc='total number of passengers that the aircraft is designed to accommodate', + option=True, + default_value=0, + types=int, +) + + +# TODO rename to economy? +add_meta_data( + Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": 'WTIN.NPT', # ['&DEFINE.WTIN.NPT', 'WTS.NPT'], + "LEAPS1": 'aircraft.inputs.L0_crew_and_payload.tourist_class_count' + }, + units='unitless', + desc='number of tourist class passengers that the aircraft is designed to accommodate', + types=int, + option=True, + default_value=0, +) + add_meta_data( # Note user override # - see also: Aircraft.CrewPayload.FLIGHT_CREW_MASS_SCALER @@ -851,8 +851,8 @@ Aircraft.CrewPayload.NUM_BUSINESS_CLASS, meta_data=_MetaData, historical_name={"GASP": None, - "FLOPS": 'WTIN.NPB', # ['&DEFINE.WTIN.NPB', 'WTS.NPB'], - "LEAPS1": 'aircraft.inputs.L0_crew_and_payload.business_class_count' + "FLOPS": None, # ['&DEFINE.WTIN.NPB', 'WTS.NPB'], + "LEAPS1": None, # 'aircraft.inputs.L0_crew_and_payload.business_class_count' }, units='unitless', desc='number of business class passengers', @@ -865,8 +865,8 @@ Aircraft.CrewPayload.NUM_FIRST_CLASS, meta_data=_MetaData, historical_name={"GASP": None, - "FLOPS": 'WTIN.NPF', # ['&DEFINE.WTIN.NPF', 'WTS.NPF'], - "LEAPS1": 'aircraft.inputs.L0_crew_and_payload.first_class_count' + "FLOPS": None, # ['&DEFINE.WTIN.NPF', 'WTS.NPF'], + "LEAPS1": None, # 'aircraft.inputs.L0_crew_and_payload.first_class_count' }, units='unitless', desc='number of first class passengers', @@ -929,7 +929,7 @@ meta_data=_MetaData, historical_name={"GASP": 'INGASP.PAX', "FLOPS": None, # ['CSTDAT.NSV', '~WEIGHT.NPASS', '~WTSTAT.NPASS'], - "LEAPS1": 'aircraft.outputs.L0_crew_and_payload.passenger_count' + "LEAPS1": None, # 'aircraft.outputs.L0_crew_and_payload.passenger_count' }, units='unitless', desc='total number of passengers', @@ -943,8 +943,8 @@ Aircraft.CrewPayload.NUM_TOURIST_CLASS, meta_data=_MetaData, historical_name={"GASP": None, - "FLOPS": 'WTIN.NPT', # ['&DEFINE.WTIN.NPT', 'WTS.NPT'], - "LEAPS1": 'aircraft.inputs.L0_crew_and_payload.tourist_class_count' + "FLOPS": None, # ['&DEFINE.WTIN.NPT', 'WTS.NPT'], + "LEAPS1": None, # 'aircraft.inputs.L0_crew_and_payload.tourist_class_count' }, units='unitless', desc='number of tourist class passengers', From 8fbce594ba9c4c121711a1dcd7d2e845962b149b Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 26 Sep 2024 10:00:01 -0400 Subject: [PATCH 074/113] test_mass_summation.py working after CrewPayload.NUM_PAX added back into large_single_aisle/V3_bug_fixed_IO.py example aircraft --- .../large_single_aisle_1/V3_bug_fixed_IO.py | 4 + aviary/subsystems/mass/gasp_based/fuel.py | 9 - .../gasp_based/test/test_mass_summation.py | 6274 ++++++++--------- 3 files changed, 3141 insertions(+), 3146 deletions(-) diff --git a/aviary/models/large_single_aisle_1/V3_bug_fixed_IO.py b/aviary/models/large_single_aisle_1/V3_bug_fixed_IO.py index ac83b406e..229a932d0 100644 --- a/aviary/models/large_single_aisle_1/V3_bug_fixed_IO.py +++ b/aviary/models/large_single_aisle_1/V3_bug_fixed_IO.py @@ -14,6 +14,10 @@ val=False, units='unitless') V3_bug_fixed_options.set_val( Aircraft.CrewPayload.Design.NUM_PASSENGERS, val=180, units='unitless') +# we keep CrewPayload.NUM_PASSENGERS here because preprocess_crewpayload is often not run in these +# tests which prevents these values being assigned from Design.NUM_PASSENGERS as would normally happen +V3_bug_fixed_options.set_val( + Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') V3_bug_fixed_options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') V3_bug_fixed_options.set_val( Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') diff --git a/aviary/subsystems/mass/gasp_based/fuel.py b/aviary/subsystems/mass/gasp_based/fuel.py index 650717fb5..df1734897 100644 --- a/aviary/subsystems/mass/gasp_based/fuel.py +++ b/aviary/subsystems/mass/gasp_based/fuel.py @@ -502,15 +502,6 @@ def compute(self, inputs, outputs): - useful_wt ) - print('OEM_wingfuel_mass', OEM_wingfuel_wt / GRAV_ENGLISH_LBM) - print('supporting values') - print('gross_wt_initial', gross_wt_initial) - print('propulsion_wt', propulsion_wt) - print('control_wt', control_wt) - print('struct_wt', struct_wt) - print('fixed_equip_wt', fixed_equip_wt) - print('useful_wt', useful_wt) - OEM_fuel_vol = OEM_wingfuel_wt / rho_fuel design_fuel_vol = (1.0 + fuel_margin / 100.0) * req_fuel_wt / rho_fuel diff --git a/aviary/subsystems/mass/gasp_based/test/test_mass_summation.py b/aviary/subsystems/mass/gasp_based/test/test_mass_summation.py index b8dc00c63..4101e5325 100644 --- a/aviary/subsystems/mass/gasp_based/test/test_mass_summation.py +++ b/aviary/subsystems/mass/gasp_based/test/test_mass_summation.py @@ -162,3143 +162,3143 @@ def test_case1(self): assert_check_partials(partial_data, atol=3e-10, rtol=1e-12) -# class MassSummationTestCase2(unittest.TestCase): -# """ -# This is the large single aisle 1 V3.5 test case. -# All values are from V3.5 output (or hand calculated from the output, and these cases -# are specified). -# """ - -# def setUp(self): - -# options = get_option_defaults() -# options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, -# val=False, units='unitless') -# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') -# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') -# options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') -# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.LandingGear.FIXED_GEAR, -# val=False, units='unitless') -# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, -# val=200, units="lbm") -# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) -# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") -# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) -# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") -# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - -# self.prob = om.Problem() -# self.prob.model.add_subsystem( -# "size", -# SizeGroup( -# aviary_options=options, -# ), -# promotes_inputs=["aircraft:*", "mission:*"], -# promotes_outputs=[ -# "aircraft:*", -# ], -# ) -# self.prob.model.add_subsystem( -# "GASP_mass", -# MassPremission( -# aviary_options=options, -# ), -# promotes=["*"], -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" -# ) -# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Mission.Design.GROSS_MASS, val=175400, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.LOADING, val=128, units="lbf/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" -# ) -# # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") -# # self.prob.model.set_input_defaults( -# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" -# # ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless') -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.FINENESS, 2, units="unitless") - -# self.prob.model.set_input_defaults( -# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.SWEEP, val=0, units='deg' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" -# ) # Based onlarge single aisle 1for updated flaps mass model -# self.prob.model.set_input_defaults( -# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" -# ) # Based onlarge single aisle 1for updated flaps mass model -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.APU.MASS, val=928.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Avionics.MASS, val=1959.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.AntiIcing.MASS, val=551.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Furnishings.MASS, val=11192.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_MARGIN, val=0, units="unitless") - -# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - -# self.prob.setup(check=False, force_alloc_complex=True) - -# def test_case1(self): - -# self.prob.run_model() - -# tol = 5e-4 -# # size values: -# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) -# assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) -# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - -# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 17.49, tol) -# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.41, tol) -# assert_near_equal( -# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1397, tol -# ) # not exact GASP value from the output file, likely due to rounding error - -# # note: this is not the value in the GASP output, because the output calculates -# # them differently. This was calculated by hand. -# assert_near_equal( -# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.578314120156815, tol -# ) -# # note: this is not the value in the GASP output, because the output calculates -# # them differently. This was calculated by hand. -# assert_near_equal( -# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 16.828924591320984, tol -# ) -# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) - -# # fixed mass values: -# assert_near_equal( -# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.35, tol -# ) # calculated by hand - -# # note: fixed_mass.tail.loc_MAC_vtail not included in v3.5 - -# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) -# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) - -# # wing values: -# assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15653, tol) - -# # fuel values: -# # modified from GASP value to account for updated crew mass. GASP value is -# # 79147.2 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 79002.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 79147.2 - -# # calculated by hand, #modified from GASP value to account for updated crew -# # mass. GASP value is 102321.45695930265 -# assert_near_equal( -# self.prob["fuel_mass.fus_mass_full"], 102359.6, tol -# ) -# # modified from GASP value to account for updated crew mass. GASP value is -# # 1769 -# assert_near_equal( -# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1763.1, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1769 - -# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 50186, tol) -# assert_near_equal( -# self.prob[Aircraft.Fuselage.MASS], 18663, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 18787 - -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 43002.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 43147.2 -# assert_near_equal( -# self.prob[Aircraft.Propulsion.MASS], 16133.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 16140 -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS], 43002.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 43147 -# assert_near_equal( -# self.prob["fuel_mass.fuel_mass_min"], 32962.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 33107.2 -# assert_near_equal( -# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 859.68, tol -# ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 862.5603807559726 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1579.36, tol -# ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 1582.2403068511774 -# assert_near_equal( -# self.prob[Aircraft.Design.OPERATING_MASS], 96397.1, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 96253.0 -# # extra_fuel_mass calculated differently in this version, so fuel_mass.fuel_and_oem.payload_mass_max_fuel test not included -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 55725.1, tol -# ) -# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 55725.1, tol) -# assert_near_equal( -# self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol -# ) # always zero when no body tank -# assert_near_equal( -# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol -# ) # always zero when no body tank -# assert_near_equal( -# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol -# ) # always zero when no body tank - -# partial_data = self.prob.check_partials(out_stream=None, method="cs") -# assert_check_partials(partial_data, atol=2e-10, rtol=1e-12) - - -# class MassSummationTestCase3(unittest.TestCase): -# """ -# This is thelarge single aisle 1V3.6 test case with a fuel margin of 0%, a wing loading of 128 psf, and a SLS thrust of 29500 lbf -# All values are from V3.6 output (or hand calculated from the output, and these cases are specified). -# """ - -# def setUp(self): - -# options = get_option_defaults() -# options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, -# val=False, units='unitless') -# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') -# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') -# options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') -# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.LandingGear.FIXED_GEAR, -# val=False, units='unitless') -# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, -# val=200, units="lbm") -# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) -# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") -# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) -# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") -# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - -# self.prob = om.Problem() -# self.prob.model.add_subsystem( -# "size", -# SizeGroup( -# aviary_options=options, -# ), -# promotes_inputs=["aircraft:*", "mission:*"], -# promotes_outputs=[ -# "aircraft:*", -# ], -# ) -# self.prob.model.add_subsystem( -# "GASP_mass", -# MassPremission( -# aviary_options=options, -# ), -# promotes=["*"], -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" -# ) -# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Mission.Design.GROSS_MASS, val=175400, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.LOADING, val=128, units="lbf/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" -# ) -# # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") -# # self.prob.model.set_input_defaults( -# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" -# # ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.FINENESS, 2, units="unitless") - -# self.prob.model.set_input_defaults( -# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.SWEEP, val=0, units='deg' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" -# ) # Based onlarge single aisle 1for updated flaps mass model -# self.prob.model.set_input_defaults( -# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" -# ) # Based on large single aisle 1 for updated flaps mass model -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.APU.MASS, val=928.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Avionics.MASS, val=1959.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.AntiIcing.MASS, val=551.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Furnishings.MASS, val=11192.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_MARGIN, val=0, units="unitless") - -# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - -# self.prob.setup(check=False, force_alloc_complex=True) - -# def test_case1(self): - -# self.prob.run_model() - -# tol = 5e-4 -# # size values: -# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) -# assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) -# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - -# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 17.49, tol) -# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.41, tol) -# assert_near_equal( -# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1397, tol -# ) # not exact value, likely due to rounding error - -# assert_near_equal( -# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.578314120156815, tol -# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. -# assert_near_equal( -# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 16.828924591320984, tol -# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. -# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) - -# # fixed mass values: -# assert_near_equal( -# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol -# ) # calculated by hand - -# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) -# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) - -# # wing values: -# assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15653, tol) - -# # fuel values: -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 79002.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 79147.2 - -# assert_near_equal( -# self.prob["fuel_mass.fus_mass_full"], 102359.6, tol -# ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 102321.45695930265 -# assert_near_equal( -# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1763.1, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 102321.45695930265 - -# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 50186, tol) -# assert_near_equal( -# self.prob[Aircraft.Fuselage.MASS], 18663, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 18787 - -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 43002.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 43147.2 -# assert_near_equal( -# self.prob[Aircraft.Propulsion.MASS], 16133.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 16140 -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS], 43002.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 43147 -# assert_near_equal( -# self.prob["fuel_mass.fuel_mass_min"], 32962.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 33107.2 -# assert_near_equal( -# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 859.68, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 862.6 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1579.36, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1582.2 -# assert_near_equal( -# self.prob[Aircraft.Design.OPERATING_MASS], 96397.1, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 96253.0 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 36000, tol -# ) # note: value came from running the GASP code on my own and printing it out -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 55725.1, tol -# ) -# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 55725.1, tol) -# assert_near_equal( -# self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol -# ) # always zero when no body tank -# assert_near_equal( -# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol -# ) # always zero when no body tank -# assert_near_equal( -# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol -# ) # always zero when no body tank - -# partial_data = self.prob.check_partials(out_stream=None, method="cs") -# assert_check_partials(partial_data, atol=2e-10, rtol=1e-12) - - -# class MassSummationTestCase4(unittest.TestCase): -# """ -# This is the large single aisle 1V3.6 test case with a fuel margin of 10%, a wing loading of 128 psf, and a SLS thrust of 29500 lbf -# All values are from V3.6 output (or hand calculated from the output, and these cases are specified). -# """ - -# def setUp(self): - -# options = get_option_defaults() -# options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, -# val=False, units='unitless') -# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') -# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') -# options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') -# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.LandingGear.FIXED_GEAR, -# val=False, units='unitless') -# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, -# val=200, units="lbm") -# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) -# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") -# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) -# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") -# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - -# self.prob = om.Problem() -# self.prob.model.add_subsystem( -# "size", -# SizeGroup( -# aviary_options=options, -# ), -# promotes_inputs=["aircraft:*", "mission:*"], -# promotes_outputs=[ -# "aircraft:*", -# ], -# ) -# self.prob.model.add_subsystem( -# "GASP_mass", -# MassPremission( -# aviary_options=options, -# ), -# promotes=["*"], -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" -# ) -# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Mission.Design.GROSS_MASS, val=175400, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.LOADING, val=128, units="lbf/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" -# ) -# # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") -# # self.prob.model.set_input_defaults( -# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" -# # ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.FINENESS, 2, units="unitless") - -# self.prob.model.set_input_defaults( -# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.SWEEP, val=0, units='deg' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" -# ) # Based onlarge single aisle 1for updated flaps mass model -# self.prob.model.set_input_defaults( -# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" -# ) # Based on large single aisle 1 for updated flaps mass model -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.APU.MASS, val=928.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Avionics.MASS, val=1959.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.AntiIcing.MASS, val=551.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Furnishings.MASS, val=11192.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_MARGIN, val=10, units="unitless" -# ) - -# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - -# self.prob.setup(check=False, force_alloc_complex=True) - -# def test_case1(self): - -# self.prob.run_model() - -# tol = 5e-4 -# # size values: -# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) -# assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) -# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - -# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 17.49, tol) -# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.41, tol) -# assert_near_equal( -# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1397, tol -# ) # slightly different from GASP value, likely numerical error - -# assert_near_equal( -# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.578314120156815, tol -# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. -# assert_near_equal( -# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 16.828924591320984, tol -# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. -# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) - -# # fixed mass values: -# assert_near_equal( -# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol -# ) # calculated by hand - -# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) -# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) - -# # wing values: -# assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15653, tol) - -# # fuel values: -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 78823.0, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 78966.7 - -# assert_near_equal( -# self.prob["fuel_mass.fus_mass_full"], 102541.4, tol -# ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 102501.95695930265 -# assert_near_equal( -# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1931.3, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1938 - -# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 50198, tol) -# assert_near_equal( -# self.prob[Aircraft.Fuselage.MASS], 18675, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 18799 - -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 42823.0, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 42966.7 -# assert_near_equal( -# self.prob[Aircraft.Propulsion.MASS], 16302.1, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 16309 -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS], 42823.0, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 42967 -# assert_near_equal( -# self.prob["fuel_mass.fuel_mass_min"], 32783.0, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 32926.7 -# assert_near_equal( -# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 941.69, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 944.8 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1575.76, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1578.6 -# assert_near_equal( -# self.prob[Aircraft.Design.OPERATING_MASS], 96577.0, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 96433.0 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 36000, tol -# ) # note: value came from running the GASP code on my own and printing it out -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 55725.1, tol -# ) -# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 55725.1, tol) -# assert_near_equal( -# self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol -# ) # always zero when no body tank -# assert_near_equal( -# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol -# ) # always zero when no body tank -# assert_near_equal( -# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol -# ) # always zero when no body tank - -# partial_data = self.prob.check_partials(out_stream=None, method="cs") -# assert_check_partials(partial_data, atol=2e-10, rtol=1e-12) - - -# class MassSummationTestCase5(unittest.TestCase): -# """ -# This is thelarge single aisle 1V3.6 test case with a fuel margin of 0%, a wing loading of 150 psf, and a SLS thrust of 29500 lbf -# All values are from V3.6 output (or hand calculated from the output, and these cases are specified). -# """ - -# def setUp(self): - -# options = get_option_defaults() -# options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, -# val=False, units='unitless') -# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') -# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') -# options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') -# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.LandingGear.FIXED_GEAR, -# val=False, units='unitless') -# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, -# val=200, units="lbm") -# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) -# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") -# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) -# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") -# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - -# self.prob = om.Problem() -# self.prob.model.add_subsystem( -# "size", -# SizeGroup( -# aviary_options=options, -# ), -# promotes_inputs=["aircraft:*", "mission:*"], -# promotes_outputs=[ -# "aircraft:*", -# ], -# ) -# self.prob.model.add_subsystem( -# "GASP_mass", -# MassPremission( -# aviary_options=options, -# ), -# promotes=["*"], -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" -# ) -# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Mission.Design.GROSS_MASS, val=175400, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.LOADING, val=150, units="lbf/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" -# ) -# # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") -# # self.prob.model.set_input_defaults( -# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" -# # ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.FINENESS, 2, units="unitless") - -# self.prob.model.set_input_defaults( -# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.SWEEP, val=0, units='deg' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" -# ) # Based onlarge single aisle 1for updated flaps mass model -# self.prob.model.set_input_defaults( -# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" -# ) # Based on large single aisle 1 for updated flaps mass model -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.APU.MASS, val=928.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Avionics.MASS, val=1959.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.AntiIcing.MASS, val=551.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Furnishings.MASS, val=11192.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_MARGIN, val=0.0, units="unitless" -# ) - -# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - -# self.prob.setup(check=False, force_alloc_complex=True) - -# def test_case1(self): - -# self.prob.run_model() - -# tol = 5e-4 -# # size values: -# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) -# assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) -# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - -# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 16.16, tol) -# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 15.1, tol) -# assert_near_equal( -# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1394, tol -# ) # slightly different from GASP value, likely rounding error - -# assert_near_equal( -# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 8.848695928254141, tol -# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. -# assert_near_equal( -# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 15.550266681026597, tol -# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. -# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) - -# # fixed mass values: -# assert_near_equal( -# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol -# # self.prob["fixed_mass.main_gear_mass"], 6384.349999999999, tol -# ) # calculated by hand - -# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) -# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) - -# # wing values: -# assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 14631, tol) - -# # fuel values: -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 80475.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 81424.8 - -# assert_near_equal( -# self.prob["fuel_mass.fus_mass_full"], 102510.7, tol -# ) # calculated by hand -# assert_near_equal( -# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1823.4, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1862 - -# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 48941, tol) -# assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 18675, tol) - -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 44472.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 45424.8 -# assert_near_equal( -# self.prob[Aircraft.Propulsion.MASS], 16194.2, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 16233 -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS], 44472.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 45425 -# assert_near_equal( -# self.prob["fuel_mass.fuel_mass_min"], 34432.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 35384.8 -# assert_near_equal( -# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 889.06, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 908.1 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1608.74, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1627.8 -# assert_near_equal( -# self.prob[Aircraft.Design.OPERATING_MASS], 94927.1, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 93975 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 35380.5, tol -# ) # note: value came from running the GASP code on my own and printing it out, #modified from GASP value to account for updated crew mass. GASP value is 34427.4 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 43852.1, tol -# ) -# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 43852.1, tol) -# assert_near_equal( -# self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 620.739, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1572.6 -# assert_near_equal( -# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 12.4092, tol -# ) # slightly different from GASP value, likely a rounding error, #modified from GASP value to account for updated crew mass. GASP value is 31.43 -# assert_near_equal( -# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 620.736, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1572.6 - -# partial_data = self.prob.check_partials(out_stream=None, method="cs") -# assert_check_partials(partial_data, atol=3e-10, rtol=1e-12) - - -# class MassSummationTestCase6(unittest.TestCase): -# """ -# This is thelarge single aisle 1V3.6 test case with a fuel margin of 10%, a wing loading of 150 psf, and a SLS thrust of 29500 lbf -# All values are from V3.6 output (or hand calculated from the output, and these cases are specified). -# """ - -# def setUp(self): - -# options = get_option_defaults() -# options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, -# val=False, units='unitless') -# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') -# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') -# options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') -# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.LandingGear.FIXED_GEAR, -# val=False, units='unitless') -# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, -# val=200, units="lbm") -# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) -# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") -# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) -# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") -# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - -# self.prob = om.Problem() -# self.prob.model.add_subsystem( -# "size", -# SizeGroup( -# aviary_options=options, -# ), -# promotes_inputs=["aircraft:*", "mission:*"], -# promotes_outputs=[ -# "aircraft:*", -# ], -# ) -# self.prob.model.add_subsystem( -# "GASP_mass", -# MassPremission( -# aviary_options=options, -# ), -# promotes=["*"], -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" -# ) -# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Mission.Design.GROSS_MASS, val=175400, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.LOADING, val=150, units="lbf/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" -# ) -# # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") -# # self.prob.model.set_input_defaults( -# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" -# # ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.FINENESS, 2, units="unitless") - -# self.prob.model.set_input_defaults( -# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.SWEEP, val=0, units='deg' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" -# ) # Based onlarge single aisle 1for updated flaps mass model -# self.prob.model.set_input_defaults( -# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" -# ) # Based onlarge single aisle 1for updated flaps mass model -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.APU.MASS, val=928.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Avionics.MASS, val=1959.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.AntiIcing.MASS, val=551.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Furnishings.MASS, val=11192.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_MARGIN, val=10.0, units="unitless" -# ) - -# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - -# self.prob.setup(check=False, force_alloc_complex=True) - -# def test_case1(self): - -# self.prob.run_model() - -# tol = 5e-4 -# # size values: -# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) -# assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) -# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - -# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 16.16, tol) -# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 15.1, tol) -# assert_near_equal( -# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1394, tol -# ) # note: not exact GASP value, likely rounding error - -# assert_near_equal( -# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 8.848695928254141, tol -# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. -# assert_near_equal( -# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 15.550266681026597, tol -# ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. -# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) - -# # fixed mass values: -# assert_near_equal( -# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol -# # self.prob["fixed_mass.main_gear_mass"], 6384.349999999999, tol -# ) # calculated by hand - -# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) -# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) - -# # wing values: -# assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 14631, tol) - -# # fuel values: -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 80029.2, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 80982.7 - -# assert_near_equal( -# self.prob["fuel_mass.fus_mass_full"], 106913.6, tol -# ) # calculated by hand -# assert_near_equal( -# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1985.7, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 2029 - -# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 49222, tol) -# assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 18956, tol) - -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 44029.2, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 44982.7 -# assert_near_equal( -# self.prob[Aircraft.Propulsion.MASS], 16356.5, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 16399 -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS], 44029.2, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 44982.7 -# assert_near_equal( -# self.prob["fuel_mass.fuel_mass_min"], 33989.2, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 34942.7 -# assert_near_equal( -# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 968.21, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 989.2 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1599.87, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1618.9 -# assert_near_equal( -# self.prob[Aircraft.Design.OPERATING_MASS], 95370.8, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 94417 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 35823.0, tol -# ) # note: value came from running the GASP code on my own and printing it out, #modified from GASP value to account for updated crew mass. GASP value is 34879.2 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 43852.1, tol -# ) -# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 43852.1, tol) -# assert_near_equal( -# self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 177.042, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1120.9 -# assert_near_equal( -# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 91.5585, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 112.3 -# assert_near_equal( -# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 4579.96, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 5618.2 - -# partial_data = self.prob.check_partials(out_stream=None, method="cs") -# assert_check_partials(partial_data, atol=3e-10, rtol=1e-12) - - -# class MassSummationTestCase7(unittest.TestCase): -# """ -# This is the Advanced Tube and Wing V3.6 test case -# All values are from V3.6 output, hand calculated from the output, or were printed out after running the code manually. -# Values not directly from the output are labeled as such. -# """ - -# def setUp(self): - -# options = get_option_defaults() -# options.set_val(Aircraft.Wing.HAS_FOLD, val=True, units='unitless') -# options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, -# val=False, units='unitless') -# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') -# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37100, units='ft') -# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.LandingGear.FIXED_GEAR, -# val=False, units='unitless') -# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, -# val=200, units="lbm") -# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) -# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") -# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) -# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") -# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - -# self.prob = om.Problem() -# self.prob.model.add_subsystem( -# "size", -# SizeGroup( -# aviary_options=options, -# ), -# promotes_inputs=["aircraft:*", "mission:*"], -# promotes_outputs=[ -# "aircraft:*", -# ], -# ) -# self.prob.model.add_subsystem( -# "GASP_mass", -# MassPremission( -# aviary_options=options, -# ), -# promotes=["*"], -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.Wing.ASPECT_RATIO, val=11, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" -# ) -# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Mission.Design.GROSS_MASS, val=145388.0, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.LOADING, val=104.50, units="lbf/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALED_SLS_THRUST, val=17000.0, units="lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.WING_FUEL_FRACTION, 0.475, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.09986, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.WETTED_AREA_SCALER, 1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MOMENT_RATIO, 2.1621, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.REFERENCE_DIAMETER, 7.36, units="ft") -# # self.prob.model.set_input_defaults( -# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28620.0, units="lbf" -# # ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALE_FACTOR, 0.594, units='unitless' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.2095, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.FINENESS, 1.715, units="unitless") -# self.prob.model.set_input_defaults(Aircraft.Wing.FOLDED_SPAN, 118, units="ft") - -# self.prob.model.set_input_defaults( -# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CARGO_MASS, val=15970.0, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.SWEEP, val=0, units='deg' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" -# ) # Based onlarge single aisle 1for updated flaps mass model -# self.prob.model.set_input_defaults( -# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" -# ) # Based on large single aisle 1 for updated flaps mass model -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SPECIFIC, val=0.2355, units="lbm/lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.165, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.APU.MASS, val=1014.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.085, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.105, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Avionics.MASS, val=1504.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.AntiIcing.MASS, val=126.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Furnishings.MASS, val=9114.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=0.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=10.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_COEFFICIENT, val=85, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.FOLD_MASS_COEFFICIENT, val=0.2, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' -# ) # note: not actually defined in program, likely an error -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_MARGIN, val=10.0, units="unitless" -# ) - -# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - -# self.prob.setup(check=False, force_alloc_complex=True) - -# def test_case1(self): - -# self.prob.run_model() - -# tol = 5e-4 -# # size values: -# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) -# assert_near_equal(self.prob["size.fuselage.cabin_len"], 61.6, tol) -# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - -# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 16.91, tol) -# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.01, tol) -# assert_near_equal( -# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1132, tol -# ) # slightly different from GASP value, likely a rounding error - -# assert_near_equal( -# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.6498, tol -# # note: value came from running the GASP code on my own and printing it out (GASP output calculates this differently) -# ) -# assert_near_equal( -# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 13.4662, tol -# # note: value came from running the GASP code on my own and printing it out (GASP output calculates this differently) -# ) -# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 11.77, tol) - -# # fixed mass values: -# assert_near_equal( -# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 5219.3076, tol -# # self.prob["fixed_mass.main_gear_mass"], 5219.3076, tol -# ) # note: value came from running the GASP code on my own and printing it out - -# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 8007, tol) -# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1321/2, tol) - -# # wing values: -# assert_near_equal( -# self.prob["wing_mass.isolated_wing_mass"], 13993, tol -# ) # calculated as difference between wing mass and fold mass, not an actual GASP variable - -# # fuel values: -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 63452.2, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 62427.2 - -# assert_near_equal( -# self.prob["fuel_mass.fus_mass_full"], 99396.7, tol -# ) # note: value came from running the GASP code on my own and printing it out -# assert_near_equal( -# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1472.6, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1426 - -# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 45373.4, tol) -# assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 18859.9, tol) - -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 32652.2, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 31627.2 -# assert_near_equal( -# self.prob[Aircraft.Propulsion.MASS], 10800.8, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 10755.0 -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS], 32652.2, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 31627.0 -# assert_near_equal( -# self.prob["fuel_mass.fuel_mass_min"], 16682.2, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 15657.2 -# assert_near_equal( -# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 718.03, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 695.5 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1268.48, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1248.0 -# assert_near_equal( -# self.prob[Aircraft.Design.OPERATING_MASS], 81935.8, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 82961.0 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 30800.0039, tol -# ) # note: value came from running the GASP code on my own and printing it out -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 33892.8, tol -# ) -# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 33892.8, tol) -# assert_near_equal(self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol) -# assert_near_equal( -# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 40.4789, 0.005 -# ) # note: higher tol because slightly different from GASP value, likely numerical issues, #modified from GASP value to account for updated crew mass. GASP value is 17.9 -# assert_near_equal( -# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 2024.70, 0.003 -# ) # note: higher tol because slightly different from GASP value, likely numerical issues, #modified from GASP value to account for updated crew mass. GASP value is 897.2 - -# partial_data = self.prob.check_partials(out_stream=None, method="cs") -# assert_check_partials(partial_data, atol=3e-9, rtol=6e-11) - - -# class MassSummationTestCase8(unittest.TestCase): -# """ -# This is the Trans-sonic Truss-Braced Wing V3.6 test case -# All values are from V3.6 output, hand calculated from the output, or were printed out after running the code manually. -# Values not directly from the output are labeled as such. -# """ - -# def setUp(self): - -# options = get_option_defaults() -# options.set_val(Aircraft.Wing.HAS_FOLD, val=True, units='unitless') -# options.set_val(Aircraft.Wing.HAS_STRUT, val=True, units='unitless') -# options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, -# val=False, units='unitless') -# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') -# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=43000, units='ft') -# options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') -# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.LandingGear.FIXED_GEAR, -# val=False, units='unitless') -# options.set_val(Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, -# val=True, units='unitless') -# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, -# val=200, units="lbm") -# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) -# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") -# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) -# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 44.2, units="inch") -# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - -# self.prob = om.Problem() -# self.prob.model.add_subsystem( -# "size", -# SizeGroup( -# aviary_options=options, -# ), -# promotes_inputs=["aircraft:*", "mission:*"], -# promotes_outputs=[ -# "aircraft:*", -# ], -# ) -# self.prob.model.add_subsystem( -# "GASP_mass", -# MassPremission( -# aviary_options=options, -# ), -# promotes=["*"], -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.13067, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.025, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MOMENT_RATIO, 3.0496, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.REFERENCE_DIAMETER, 7.642, units="ft") -# # self.prob.model.set_input_defaults( -# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28620.0, units="lbf" -# # ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALE_FACTOR, 1.35255, units='unitless' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.2095, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.FINENESS, 1.660, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 6.85, units="ft" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.TAIL_FINENESS, 1.18, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.WETTED_AREA_SCALER, 1.0, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.LOADING, val=87.5, units="lbf/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.APU.MASS, val=1014.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.085, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.105, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Avionics.MASS, val=1504.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.AntiIcing.MASS, val=126.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Furnishings.MASS, val=9114.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=0.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=10.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALED_SLS_THRUST, val=21160.0, units="lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALE_FACTOR, 0.73934, units='unitless' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.WING_FUEL_FRACTION, 0.5625, units="unitless" -# ) -# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=22.47, units="deg") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MOUNTING_TYPE, val=.1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.ASPECT_RATIO, val=19.565, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Strut.ATTACHMENT_LOCATION, val=118, units="ft" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CARGO_MASS, val=15970.0, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SPECIFIC, val=0.2470, units="lbm/lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.MASS_SPECIFIC, val=2.5, units="lbm/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.163, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Engine.WING_LOCATIONS, val=0.2143, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.ASPECT_RATIO, val=0.825, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.SWEEP, val=0, units='deg' -# ) # not in file -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.2076, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.2587, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.11, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" -# ) # Based onlarge single aisle 1for updated flaps mass model -# self.prob.model.set_input_defaults( -# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" -# ) # Based on large single aisle 1 for updated flaps mass model -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.5936, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=30, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" -# ) # not in file -# self.prob.model.set_input_defaults( -# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" -# ) # not in file -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.03390, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_MARGIN, val=10.0, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.060, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_COEFFICIENT, val=89.66, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' -# ) # not in file -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Mission.Design.GROSS_MASS, val=143100.0, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_COEFFICIENT, val=78.94, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.TAPER_RATIO, val=0.346, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.11, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.43, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.066, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.FOLD_MASS_COEFFICIENT, val=0.2, units="unitless" -# ) -# # self.prob.model.set_input_defaults( -# # Aircraft.Strut.AREA, 523.337, units="ft**2" -# # ) # had to calculate by hand -# self.prob.model.set_input_defaults( -# Aircraft.Strut.MASS_COEFFICIENT, 0.238, units="unitless" -# ) - -# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - -# self.prob.setup(check=False, force_alloc_complex=True) - -# def test_case1(self): - -# self.prob.run_model() - -# tol = 5e-4 -# # size values: -# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) -# assert_near_equal(self.prob["size.fuselage.cabin_len"], 93.9, tol) -# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - -# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 13.59, tol) -# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 13.15, tol) -# assert_near_equal( -# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1068, tol -# ) # note:precision came from running code on my own and printing it out - -# assert_near_equal( -# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.381, tol -# ) # note, printed out manually because calculated differently in output subroutine -# assert_near_equal( -# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 20.056, tol -# ) # note, printed out manually because calculated differently in output subroutine -# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 13.19, tol) - -# # fixed mass values: -# assert_near_equal( -# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 4123.4, tol -# # self.prob["fixed_mass.main_gear_mass"], 4123.4, tol -# ) # note:printed out from GASP code - -# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 10453.0, tol) -# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1704.0/2, tol) - -# # wing values: -# assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 14040, tol) -# assert_near_equal(self.prob[Aircraft.Wing.MASS], 18031, tol) - -# # fuel values: -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 60410.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 59372.3 - -# assert_near_equal( -# self.prob["fuel_mass.fus_mass_full"], 97697.5, tol -# ) # note:printed out from GASP code -# assert_near_equal( -# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1954.3, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1886.0 - -# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 43660.4, tol) -# assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 14657.4, tol) - -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 29610.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 28572.3 -# assert_near_equal( -# self.prob[Aircraft.Propulsion.MASS], 14111.2, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 14043.0 -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS], 29610.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 28572.0 -# assert_near_equal( -# self.prob["fuel_mass.fuel_mass_min"], 13640.9, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 12602.3 -# assert_near_equal( -# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 651.15, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 628.3 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1207.68, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1186.9 -# assert_near_equal( -# self.prob[Aircraft.Design.OPERATING_MASS], 82689.1, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 83728.0 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 30800.0, tol -# ) # note:printed out from GASP code -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 31051.6, tol -# ) -# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 31051.6, tol) -# assert_near_equal(self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol) -# assert_near_equal( -# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 30.3942, 0.009 -# ) # note: higher tol because slightly different from GASP value, likely numerical issues, printed out from the GASP code, #modified from GASP value to account for updated crew mass. GASP value is 7.5568 -# assert_near_equal( -# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 1520.384, 0.009 -# ) # note: higher tol because slightly different from GASP value, likely numerical issues, printed out from the GASP code, #modified from GASP value to account for updated crew mass. GASP value is 378.0062 - -# partial_data = self.prob.check_partials(out_stream=None, method="cs") -# assert_check_partials(partial_data, atol=3e-9, rtol=6e-11) - - -# class MassSummationTestCase9(unittest.TestCase): -# """ -# This is the electrified Trans-sonic Truss-Braced Wing V3.6 test case -# All values are from V3.6 output, hand calculated from the output, or were printed out after running the code manually. -# Values not directly from the output are labeled as such. -# """ - -# def setUp(self): - -# options = get_option_defaults() -# options.set_val(Aircraft.Wing.HAS_FOLD, val=True, units='unitless') -# options.set_val(Aircraft.Wing.HAS_STRUT, val=True, units='unitless') -# options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') -# options.set_val(Mission.Design.CRUISE_ALTITUDE, val=43000, units='ft') -# options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') -# options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, -# val=True, units='unitless') -# options.set_val(Aircraft.LandingGear.FIXED_GEAR, -# val=False, units='unitless') -# options.set_val(Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, -# val=True, units='unitless') -# options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, -# val=200, units="lbm") -# options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) -# options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") -# options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) -# options.set_val(Aircraft.Fuselage.SEAT_PITCH, 44.2, units="inch") -# options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") - -# self.prob = om.Problem() -# self.prob.model.add_subsystem( -# "size", -# SizeGroup( -# aviary_options=options, -# ), -# promotes_inputs=["aircraft:*", "mission:*"], -# promotes_outputs=[ -# "aircraft:*", -# ], -# ) -# self.prob.model.add_subsystem( -# "GASP_mass", -# MassPremission( -# aviary_options=options, -# ), -# promotes=["*"], -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MOMENT_RATIO, val=0.13067, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.ASPECT_RATIO, val=4.025, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MOMENT_RATIO, 3.0496, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.REFERENCE_DIAMETER, 8.425, units="ft") -# # self.prob.model.set_input_defaults( -# # Aircraft.Engine.REFERENCE_SLS_THRUST, 28620, units="lbf" -# # ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALE_FACTOR, 0.73934, units='unitless' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.2095, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.FINENESS, 1.569, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 6.85, units="ft" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.TAIL_FINENESS, 1.18, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.WETTED_AREA_SCALER, 1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.LOADING, val=96.10, units="lbf/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.APU.MASS, val=1014.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.085, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.105, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Avionics.MASS, val=1504.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.AntiIcing.MASS, val=126.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Furnishings.MASS, val=9114.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=0.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=10.0, units="lbm") -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") - -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALED_SLS_THRUST, val=23750.0, units="lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.SCALE_FACTOR, 0.82984, units='unitless' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.WING_FUEL_FRACTION, 0.5936, units="unitless" -# ) -# self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=22.47, units="deg") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MOUNTING_TYPE, val=.1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.ASPECT_RATIO, val=19.565, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Strut.ATTACHMENT_LOCATION, val=118.0, units="ft" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.CrewPayload.CARGO_MASS, val=15970.0, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SPECIFIC, val=0.2744, units="lbm/lbf" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Nacelle.MASS_SPECIFIC, val=2.5, units="lbm/ft**2" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.163, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Engine.WING_LOCATIONS, val=0.2143, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.ASPECT_RATIO, val=0.825, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.SWEEP, val=0, units='deg' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.2076, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.2587, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.11, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" -# ) # Based onlarge single aisle 1for updated flaps mass model -# self.prob.model.set_input_defaults( -# Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" -# ) # Based on large single aisle 1 for updated flaps mass model -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.5936, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=30.0, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=1, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MASS_COEFFICIENT, val=0.03390, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_MARGIN, val=0.0, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.060, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_COEFFICIENT, val=96.94, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' -# ) -# self.prob.model.set_input_defaults( -# "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") -# self.prob.model.set_input_defaults( -# Mission.Design.GROSS_MASS, val=166100.0, units="lbm" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.MASS_COEFFICIENT, val=78.94, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.TAPER_RATIO, val=0.346, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.11, units="unitless" -# ) - -# self.prob.model.set_input_defaults( -# Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.43, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.066, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# Aircraft.Wing.FOLD_MASS_COEFFICIENT, val=0.2, units="unitless" -# ) -# # self.prob.model.set_input_defaults( -# # Aircraft.Strut.AREA, 553.1, units="ft**2" -# # ) -# self.prob.model.set_input_defaults( -# Aircraft.Strut.MASS_COEFFICIENT, 0.238, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.motor_power", 830, units="kW" -# ) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.motor_voltage", 850, units="V" -# ) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.max_amp_per_wire", 260, units="A" -# ) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.safety_factor", 1, units="unitless" -# ) # (not in this GASP code) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.wire_area", 0.0015, units="ft**2" -# ) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.rho_wire", 565, units="lbm/ft**3" -# ) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.battery_energy", 6077, units="MJ" -# ) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.motor_eff", 0.98, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.inverter_eff", 0.99, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.transmission_eff", 0.975, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.battery_eff", 0.975, units="unitless" -# ) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.rho_battery", 0.5, units="kW*h/kg" -# ) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.motor_spec_mass", 4, units="hp/lbm" -# ) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.inverter_spec_mass", 12, units="kW/kg" -# ) -# self.prob.model.set_input_defaults( -# "fixed_mass.augmentation.TMS_spec_mass", 0.125, units="lbm/kW" -# ) - -# self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") - -# self.prob.setup(check=False, force_alloc_complex=True) - -# def test_case1(self): - -# self.prob.run_model() - -# tol = 5e-4 -# # size values: -# assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) -# assert_near_equal(self.prob["size.fuselage.cabin_len"], 93.9, tol) -# assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) - -# assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 13.97, tol) -# assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 13.53, tol) -# assert_near_equal( -# self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1068, tol -# ) # (printed out from GASP code to get better precision) - -# assert_near_equal( -# self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.644, tol -# ) # (printed out from GASP code) -# assert_near_equal( -# self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 20.618, tol -# ) # (printed out from GASP code) -# assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.56, tol) - -# # fixed mass values: -# assert_near_equal( -# self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 4786.2, tol -# ) # (printed out from GASP code) - -# assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 13034.0, tol) -# assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 2124.5/2, tol) - -# # wing values: -# assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15895, tol) -# assert_near_equal(self.prob[Aircraft.Wing.MASS], 20461.7, tol) - -# # fuel values: -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 64594.0, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 63707.6 - -# assert_near_equal( -# self.prob["fuel_mass.fus_mass_full"], 108803.9, tol -# ) # (printed out from GASP code), #modified from GASP value to account for updated crew mass. GASP value is 108754.4 -# assert_near_equal( -# self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 2027.6, 0.00055 -# ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 1974.5 - -# assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 49582, tol) -# assert_near_equal( -# self.prob[Aircraft.Fuselage.MASS], 16313.0, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 16436.0 - -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS_REQUIRED], 33794.0, 0.00058 -# ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 32907.6 -# assert_near_equal( -# self.prob[Aircraft.Propulsion.MASS], 26565.2, 0.00054 -# ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 26527.0 -# assert_near_equal( -# self.prob[Mission.Design.FUEL_MASS], 33794.0, 0.00056 -# ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 32908 -# assert_near_equal( -# self.prob["fuel_mass.fuel_mass_min"], 17824.0, 0.0012 -# ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 16937.6 -# assert_near_equal( -# self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 675.58, 0.00051 -# ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 657.9 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1291.31, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 1273.6 -# assert_near_equal( -# self.prob[Aircraft.Design.OPERATING_MASS], 101506.0, tol -# ) # modified from GASP value to account for updated crew mass. GASP value is 102392.0 -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 30800.0, tol -# ) # (printed out from GASP code) -# assert_near_equal( -# self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 35042.1, tol -# ) -# assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 35042.1, tol) -# assert_near_equal(self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol) -# assert_near_equal( -# self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol -# ) -# assert_near_equal( -# self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol -# ) - -# assert_near_equal(self.prob[Aircraft.Electrical.HYBRID_CABLE_LENGTH], 65.6, tol) -# assert_near_equal( -# self.prob["fixed_mass.aug_mass"], 9394.3, 0.0017 -# ) # slightly above tol, due to non-integer number of wires - -# partial_data = self.prob.check_partials(out_stream=None, method="cs") -# assert_check_partials(partial_data, atol=3e-9, rtol=6e-11) +class MassSummationTestCase2(unittest.TestCase): + """ + This is the large single aisle 1 V3.5 test case. + All values are from V3.5 output (or hand calculated from the output, and these cases + are specified). + """ + + def setUp(self): + + options = get_option_defaults() + options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, + val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') + options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') + options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.LandingGear.FIXED_GEAR, + val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, + val=200, units="lbm") + options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) + options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") + options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) + options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") + options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + + self.prob = om.Problem() + self.prob.model.add_subsystem( + "size", + SizeGroup( + aviary_options=options, + ), + promotes_inputs=["aircraft:*", "mission:*"], + promotes_outputs=[ + "aircraft:*", + ], + ) + self.prob.model.add_subsystem( + "GASP_mass", + MassPremission( + aviary_options=options, + ), + promotes=["*"], + ) + + self.prob.model.set_input_defaults( + Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" + ) + self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" + ) + self.prob.model.set_input_defaults( + Mission.Design.GROSS_MASS, val=175400, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.LOADING, val=128, units="lbf/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") + self.prob.model.set_input_defaults( + Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") + self.prob.model.set_input_defaults( + Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" + ) + # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 + self.prob.model.set_input_defaults( + Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") + # self.prob.model.set_input_defaults( + # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" + # ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless') + self.prob.model.set_input_defaults( + Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Nacelle.FINENESS, 2, units="unitless") + + self.prob.model.set_input_defaults( + Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" + ) + + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.SWEEP, val=0, units='deg' + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" + ) # Based onlarge single aisle 1for updated flaps mass model + self.prob.model.set_input_defaults( + Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" + ) # Based onlarge single aisle 1for updated flaps mass model + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.APU.MASS, val=928.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Avionics.MASS, val=1959.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.AntiIcing.MASS, val=551.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Furnishings.MASS, val=11192.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_MARGIN, val=0, units="unitless") + + self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + + self.prob.setup(check=False, force_alloc_complex=True) + + def test_case1(self): + + self.prob.run_model() + + tol = 5e-4 + # size values: + assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) + assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) + assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + + assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 17.49, tol) + assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.41, tol) + assert_near_equal( + self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1397, tol + ) # not exact GASP value from the output file, likely due to rounding error + + # note: this is not the value in the GASP output, because the output calculates + # them differently. This was calculated by hand. + assert_near_equal( + self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.578314120156815, tol + ) + # note: this is not the value in the GASP output, because the output calculates + # them differently. This was calculated by hand. + assert_near_equal( + self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 16.828924591320984, tol + ) + assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) + + # fixed mass values: + assert_near_equal( + self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.35, tol + ) # calculated by hand + + # note: fixed_mass.tail.loc_MAC_vtail not included in v3.5 + + assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) + assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) + + # wing values: + assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15653, tol) + + # fuel values: + # modified from GASP value to account for updated crew mass. GASP value is + # 79147.2 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 79002.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 79147.2 + + # calculated by hand, #modified from GASP value to account for updated crew + # mass. GASP value is 102321.45695930265 + assert_near_equal( + self.prob["fuel_mass.fus_mass_full"], 102359.6, tol + ) + # modified from GASP value to account for updated crew mass. GASP value is + # 1769 + assert_near_equal( + self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1763.1, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1769 + + assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 50186, tol) + assert_near_equal( + self.prob[Aircraft.Fuselage.MASS], 18663, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 18787 + + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS_REQUIRED], 43002.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 43147.2 + assert_near_equal( + self.prob[Aircraft.Propulsion.MASS], 16133.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 16140 + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS], 43002.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 43147 + assert_near_equal( + self.prob["fuel_mass.fuel_mass_min"], 32962.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 33107.2 + assert_near_equal( + self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 859.68, tol + ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 862.5603807559726 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1579.36, tol + ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 1582.2403068511774 + assert_near_equal( + self.prob[Aircraft.Design.OPERATING_MASS], 96397.1, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 96253.0 + # extra_fuel_mass calculated differently in this version, so fuel_mass.fuel_and_oem.payload_mass_max_fuel test not included + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 55725.1, tol + ) + assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 55725.1, tol) + assert_near_equal( + self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol + ) # always zero when no body tank + assert_near_equal( + self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol + ) # always zero when no body tank + assert_near_equal( + self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol + ) # always zero when no body tank + + partial_data = self.prob.check_partials(out_stream=None, method="cs") + assert_check_partials(partial_data, atol=2e-10, rtol=1e-12) + + +class MassSummationTestCase3(unittest.TestCase): + """ + This is thelarge single aisle 1V3.6 test case with a fuel margin of 0%, a wing loading of 128 psf, and a SLS thrust of 29500 lbf + All values are from V3.6 output (or hand calculated from the output, and these cases are specified). + """ + + def setUp(self): + + options = get_option_defaults() + options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, + val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') + options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') + options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.LandingGear.FIXED_GEAR, + val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, + val=200, units="lbm") + options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) + options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") + options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) + options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") + options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + + self.prob = om.Problem() + self.prob.model.add_subsystem( + "size", + SizeGroup( + aviary_options=options, + ), + promotes_inputs=["aircraft:*", "mission:*"], + promotes_outputs=[ + "aircraft:*", + ], + ) + self.prob.model.add_subsystem( + "GASP_mass", + MassPremission( + aviary_options=options, + ), + promotes=["*"], + ) + + self.prob.model.set_input_defaults( + Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" + ) + self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" + ) + self.prob.model.set_input_defaults( + Mission.Design.GROSS_MASS, val=175400, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.LOADING, val=128, units="lbf/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") + self.prob.model.set_input_defaults( + Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") + self.prob.model.set_input_defaults( + Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" + ) + # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 + self.prob.model.set_input_defaults( + Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") + # self.prob.model.set_input_defaults( + # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" + # ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Nacelle.FINENESS, 2, units="unitless") + + self.prob.model.set_input_defaults( + Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" + ) + + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.SWEEP, val=0, units='deg' + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" + ) # Based onlarge single aisle 1for updated flaps mass model + self.prob.model.set_input_defaults( + Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" + ) # Based on large single aisle 1 for updated flaps mass model + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.APU.MASS, val=928.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Avionics.MASS, val=1959.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.AntiIcing.MASS, val=551.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Furnishings.MASS, val=11192.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_MARGIN, val=0, units="unitless") + + self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + + self.prob.setup(check=False, force_alloc_complex=True) + + def test_case1(self): + + self.prob.run_model() + + tol = 5e-4 + # size values: + assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) + assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) + assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + + assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 17.49, tol) + assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.41, tol) + assert_near_equal( + self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1397, tol + ) # not exact value, likely due to rounding error + + assert_near_equal( + self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.578314120156815, tol + ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. + assert_near_equal( + self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 16.828924591320984, tol + ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. + assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) + + # fixed mass values: + assert_near_equal( + self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol + ) # calculated by hand + + assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) + assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) + + # wing values: + assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15653, tol) + + # fuel values: + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 79002.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 79147.2 + + assert_near_equal( + self.prob["fuel_mass.fus_mass_full"], 102359.6, tol + ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 102321.45695930265 + assert_near_equal( + self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1763.1, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 102321.45695930265 + + assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 50186, tol) + assert_near_equal( + self.prob[Aircraft.Fuselage.MASS], 18663, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 18787 + + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS_REQUIRED], 43002.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 43147.2 + assert_near_equal( + self.prob[Aircraft.Propulsion.MASS], 16133.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 16140 + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS], 43002.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 43147 + assert_near_equal( + self.prob["fuel_mass.fuel_mass_min"], 32962.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 33107.2 + assert_near_equal( + self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 859.68, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 862.6 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1579.36, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1582.2 + assert_near_equal( + self.prob[Aircraft.Design.OPERATING_MASS], 96397.1, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 96253.0 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 36000, tol + ) # note: value came from running the GASP code on my own and printing it out + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 55725.1, tol + ) + assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 55725.1, tol) + assert_near_equal( + self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol + ) # always zero when no body tank + assert_near_equal( + self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol + ) # always zero when no body tank + assert_near_equal( + self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol + ) # always zero when no body tank + + partial_data = self.prob.check_partials(out_stream=None, method="cs") + assert_check_partials(partial_data, atol=2e-10, rtol=1e-12) + + +class MassSummationTestCase4(unittest.TestCase): + """ + This is the large single aisle 1V3.6 test case with a fuel margin of 10%, a wing loading of 128 psf, and a SLS thrust of 29500 lbf + All values are from V3.6 output (or hand calculated from the output, and these cases are specified). + """ + + def setUp(self): + + options = get_option_defaults() + options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, + val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') + options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') + options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.LandingGear.FIXED_GEAR, + val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, + val=200, units="lbm") + options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) + options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") + options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) + options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") + options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + + self.prob = om.Problem() + self.prob.model.add_subsystem( + "size", + SizeGroup( + aviary_options=options, + ), + promotes_inputs=["aircraft:*", "mission:*"], + promotes_outputs=[ + "aircraft:*", + ], + ) + self.prob.model.add_subsystem( + "GASP_mass", + MassPremission( + aviary_options=options, + ), + promotes=["*"], + ) + + self.prob.model.set_input_defaults( + Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" + ) + self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" + ) + self.prob.model.set_input_defaults( + Mission.Design.GROSS_MASS, val=175400, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.LOADING, val=128, units="lbf/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") + self.prob.model.set_input_defaults( + Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") + self.prob.model.set_input_defaults( + Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" + ) + # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 + self.prob.model.set_input_defaults( + Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") + # self.prob.model.set_input_defaults( + # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" + # ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Nacelle.FINENESS, 2, units="unitless") + + self.prob.model.set_input_defaults( + Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" + ) + + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.SWEEP, val=0, units='deg' + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" + ) # Based onlarge single aisle 1for updated flaps mass model + self.prob.model.set_input_defaults( + Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" + ) # Based on large single aisle 1 for updated flaps mass model + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.APU.MASS, val=928.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Avionics.MASS, val=1959.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.AntiIcing.MASS, val=551.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Furnishings.MASS, val=11192.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_MARGIN, val=10, units="unitless" + ) + + self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + + self.prob.setup(check=False, force_alloc_complex=True) + + def test_case1(self): + + self.prob.run_model() + + tol = 5e-4 + # size values: + assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) + assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) + assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + + assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 17.49, tol) + assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.41, tol) + assert_near_equal( + self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1397, tol + ) # slightly different from GASP value, likely numerical error + + assert_near_equal( + self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.578314120156815, tol + ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. + assert_near_equal( + self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 16.828924591320984, tol + ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. + assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) + + # fixed mass values: + assert_near_equal( + self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol + ) # calculated by hand + + assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) + assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) + + # wing values: + assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15653, tol) + + # fuel values: + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 78823.0, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 78966.7 + + assert_near_equal( + self.prob["fuel_mass.fus_mass_full"], 102541.4, tol + ) # calculated by hand, #modified from GASP value to account for updated crew mass. GASP value is 102501.95695930265 + assert_near_equal( + self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1931.3, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1938 + + assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 50198, tol) + assert_near_equal( + self.prob[Aircraft.Fuselage.MASS], 18675, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 18799 + + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS_REQUIRED], 42823.0, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 42966.7 + assert_near_equal( + self.prob[Aircraft.Propulsion.MASS], 16302.1, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 16309 + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS], 42823.0, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 42967 + assert_near_equal( + self.prob["fuel_mass.fuel_mass_min"], 32783.0, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 32926.7 + assert_near_equal( + self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 941.69, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 944.8 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1575.76, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1578.6 + assert_near_equal( + self.prob[Aircraft.Design.OPERATING_MASS], 96577.0, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 96433.0 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 36000, tol + ) # note: value came from running the GASP code on my own and printing it out + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 55725.1, tol + ) + assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 55725.1, tol) + assert_near_equal( + self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol + ) # always zero when no body tank + assert_near_equal( + self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol + ) # always zero when no body tank + assert_near_equal( + self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol + ) # always zero when no body tank + + partial_data = self.prob.check_partials(out_stream=None, method="cs") + assert_check_partials(partial_data, atol=2e-10, rtol=1e-12) + + +class MassSummationTestCase5(unittest.TestCase): + """ + This is thelarge single aisle 1V3.6 test case with a fuel margin of 0%, a wing loading of 150 psf, and a SLS thrust of 29500 lbf + All values are from V3.6 output (or hand calculated from the output, and these cases are specified). + """ + + def setUp(self): + + options = get_option_defaults() + options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, + val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') + options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') + options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.LandingGear.FIXED_GEAR, + val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, + val=200, units="lbm") + options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) + options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") + options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) + options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") + options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + + self.prob = om.Problem() + self.prob.model.add_subsystem( + "size", + SizeGroup( + aviary_options=options, + ), + promotes_inputs=["aircraft:*", "mission:*"], + promotes_outputs=[ + "aircraft:*", + ], + ) + self.prob.model.add_subsystem( + "GASP_mass", + MassPremission( + aviary_options=options, + ), + promotes=["*"], + ) + + self.prob.model.set_input_defaults( + Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" + ) + self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" + ) + self.prob.model.set_input_defaults( + Mission.Design.GROSS_MASS, val=175400, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.LOADING, val=150, units="lbf/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") + self.prob.model.set_input_defaults( + Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") + self.prob.model.set_input_defaults( + Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" + ) + # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 + self.prob.model.set_input_defaults( + Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") + # self.prob.model.set_input_defaults( + # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" + # ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Nacelle.FINENESS, 2, units="unitless") + + self.prob.model.set_input_defaults( + Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" + ) + + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.SWEEP, val=0, units='deg' + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" + ) # Based onlarge single aisle 1for updated flaps mass model + self.prob.model.set_input_defaults( + Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" + ) # Based on large single aisle 1 for updated flaps mass model + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.APU.MASS, val=928.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Avionics.MASS, val=1959.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.AntiIcing.MASS, val=551.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Furnishings.MASS, val=11192.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_MARGIN, val=0.0, units="unitless" + ) + + self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + + self.prob.setup(check=False, force_alloc_complex=True) + + def test_case1(self): + + self.prob.run_model() + + tol = 5e-4 + # size values: + assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) + assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) + assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + + assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 16.16, tol) + assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 15.1, tol) + assert_near_equal( + self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1394, tol + ) # slightly different from GASP value, likely rounding error + + assert_near_equal( + self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 8.848695928254141, tol + ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. + assert_near_equal( + self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 15.550266681026597, tol + ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. + assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) + + # fixed mass values: + assert_near_equal( + self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol + # self.prob["fixed_mass.main_gear_mass"], 6384.349999999999, tol + ) # calculated by hand + + assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) + assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) + + # wing values: + assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 14631, tol) + + # fuel values: + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 80475.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 81424.8 + + assert_near_equal( + self.prob["fuel_mass.fus_mass_full"], 102510.7, tol + ) # calculated by hand + assert_near_equal( + self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1823.4, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1862 + + assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 48941, tol) + assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 18675, tol) + + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS_REQUIRED], 44472.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 45424.8 + assert_near_equal( + self.prob[Aircraft.Propulsion.MASS], 16194.2, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 16233 + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS], 44472.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 45425 + assert_near_equal( + self.prob["fuel_mass.fuel_mass_min"], 34432.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 35384.8 + assert_near_equal( + self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 889.06, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 908.1 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1608.74, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1627.8 + assert_near_equal( + self.prob[Aircraft.Design.OPERATING_MASS], 94927.1, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 93975 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 35380.5, tol + ) # note: value came from running the GASP code on my own and printing it out, #modified from GASP value to account for updated crew mass. GASP value is 34427.4 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 43852.1, tol + ) + assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 43852.1, tol) + assert_near_equal( + self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 620.739, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1572.6 + assert_near_equal( + self.prob["fuel_mass.body_tank.extra_fuel_volume"], 12.4092, tol + ) # slightly different from GASP value, likely a rounding error, #modified from GASP value to account for updated crew mass. GASP value is 31.43 + assert_near_equal( + self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 620.736, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1572.6 + + partial_data = self.prob.check_partials(out_stream=None, method="cs") + assert_check_partials(partial_data, atol=3e-10, rtol=1e-12) + + +class MassSummationTestCase6(unittest.TestCase): + """ + This is thelarge single aisle 1V3.6 test case with a fuel margin of 10%, a wing loading of 150 psf, and a SLS thrust of 29500 lbf + All values are from V3.6 output (or hand calculated from the output, and these cases are specified). + """ + + def setUp(self): + + options = get_option_defaults() + options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, + val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') + options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') + options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') + options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.LandingGear.FIXED_GEAR, + val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, + val=200, units="lbm") + options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) + options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") + options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) + options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") + options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + + self.prob = om.Problem() + self.prob.model.add_subsystem( + "size", + SizeGroup( + aviary_options=options, + ), + promotes_inputs=["aircraft:*", "mission:*"], + promotes_outputs=[ + "aircraft:*", + ], + ) + self.prob.model.add_subsystem( + "GASP_mass", + MassPremission( + aviary_options=options, + ), + promotes=["*"], + ) + + self.prob.model.set_input_defaults( + Aircraft.Wing.ASPECT_RATIO, val=10.13, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" + ) + self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.15, units="unitless" + ) + self.prob.model.set_input_defaults( + Mission.Design.GROSS_MASS, val=175400, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.LOADING, val=150, units="lbf/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALED_SLS_THRUST, val=29500.0, units="lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") + self.prob.model.set_input_defaults( + Aircraft.Fuel.WING_FUEL_FRACTION, 0.6, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.145, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") + self.prob.model.set_input_defaults( + Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" + ) + # Adjust WETTED_AREA_SCALER such that WETTED_AREA = 4000.0 + self.prob.model.set_input_defaults( + Aircraft.Fuselage.WETTED_AREA_SCALER, val=0.86215, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MOMENT_RATIO, 2.362, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.REFERENCE_DIAMETER, 5.8, units="ft") + # self.prob.model.set_input_defaults( + # Aircraft.Engine.REFERENCE_SLS_THRUST, 28690, units="lbf" + # ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALE_FACTOR, 1.02823, units='unitless' + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.25, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Nacelle.FINENESS, 2, units="unitless") + + self.prob.model.set_input_defaults( + Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" + ) + + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CARGO_MASS, val=10040, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.SWEEP, val=0, units='deg' + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" + ) # Based onlarge single aisle 1for updated flaps mass model + self.prob.model.set_input_defaults( + Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" + ) # Based onlarge single aisle 1for updated flaps mass model + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SPECIFIC, val=0.21366, units="lbm/lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.14, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.APU.MASS, val=928.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.112, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.14, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Avionics.MASS, val=1959.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.AntiIcing.MASS, val=551.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Furnishings.MASS, val=11192.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=50.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=7.6, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_COEFFICIENT, val=102.5, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_MARGIN, val=10.0, units="unitless" + ) + + self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + + self.prob.setup(check=False, force_alloc_complex=True) + + def test_case1(self): + + self.prob.run_model() + + tol = 5e-4 + # size values: + assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) + assert_near_equal(self.prob["size.fuselage.cabin_len"], 72.1, tol) + assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + + assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 16.16, tol) + assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 15.1, tol) + assert_near_equal( + self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1394, tol + ) # note: not exact GASP value, likely rounding error + + assert_near_equal( + self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 8.848695928254141, tol + ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. + assert_near_equal( + self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 15.550266681026597, tol + ) # note: this is not the value in the GASP output, because the output calculates them differently. This was calculated by hand. + assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.7, tol) + + # fixed mass values: + assert_near_equal( + self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 6384.349999999999, tol + # self.prob["fixed_mass.main_gear_mass"], 6384.349999999999, tol + ) # calculated by hand + + assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 12606, tol) + assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1765/2, tol) + + # wing values: + assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 14631, tol) + + # fuel values: + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 80029.2, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 80982.7 + + assert_near_equal( + self.prob["fuel_mass.fus_mass_full"], 106913.6, tol + ) # calculated by hand + assert_near_equal( + self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1985.7, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 2029 + + assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 49222, tol) + assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 18956, tol) + + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS_REQUIRED], 44029.2, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 44982.7 + assert_near_equal( + self.prob[Aircraft.Propulsion.MASS], 16356.5, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 16399 + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS], 44029.2, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 44982.7 + assert_near_equal( + self.prob["fuel_mass.fuel_mass_min"], 33989.2, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 34942.7 + assert_near_equal( + self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 968.21, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 989.2 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1599.87, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1618.9 + assert_near_equal( + self.prob[Aircraft.Design.OPERATING_MASS], 95370.8, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 94417 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 35823.0, tol + ) # note: value came from running the GASP code on my own and printing it out, #modified from GASP value to account for updated crew mass. GASP value is 34879.2 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 43852.1, tol + ) + assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 43852.1, tol) + assert_near_equal( + self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 177.042, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1120.9 + assert_near_equal( + self.prob["fuel_mass.body_tank.extra_fuel_volume"], 91.5585, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 112.3 + assert_near_equal( + self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 4579.96, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 5618.2 + + partial_data = self.prob.check_partials(out_stream=None, method="cs") + assert_check_partials(partial_data, atol=3e-10, rtol=1e-12) + + +class MassSummationTestCase7(unittest.TestCase): + """ + This is the Advanced Tube and Wing V3.6 test case + All values are from V3.6 output, hand calculated from the output, or were printed out after running the code manually. + Values not directly from the output are labeled as such. + """ + + def setUp(self): + + options = get_option_defaults() + options.set_val(Aircraft.Wing.HAS_FOLD, val=True, units='unitless') + options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, + val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') + options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37100, units='ft') + options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.LandingGear.FIXED_GEAR, + val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, + val=200, units="lbm") + options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) + options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") + options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) + options.set_val(Aircraft.Fuselage.SEAT_PITCH, 29, units="inch") + options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + + self.prob = om.Problem() + self.prob.model.add_subsystem( + "size", + SizeGroup( + aviary_options=options, + ), + promotes_inputs=["aircraft:*", "mission:*"], + promotes_outputs=[ + "aircraft:*", + ], + ) + self.prob.model.add_subsystem( + "GASP_mass", + MassPremission( + aviary_options=options, + ), + promotes=["*"], + ) + + self.prob.model.set_input_defaults( + Aircraft.Wing.ASPECT_RATIO, val=11, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.TAPER_RATIO, val=0.33, units="unitless" + ) + self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=25, units="deg") + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Mission.Design.GROSS_MASS, val=145388.0, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.LOADING, val=104.50, units="lbf/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=0, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.ASPECT_RATIO, val=1.67, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALED_SLS_THRUST, val=17000.0, units="lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.WING_LOCATIONS, val=0.35, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") + self.prob.model.set_input_defaults( + Aircraft.Fuel.WING_FUEL_FRACTION, 0.475, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.189, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.09986, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 9.5, units="ft") + self.prob.model.set_input_defaults( + Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.TAIL_FINENESS, 3, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.WETTED_AREA_SCALER, 1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MOMENT_RATIO, val=0.2307, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MOMENT_RATIO, 2.1621, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.ASPECT_RATIO, val=4.75, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.REFERENCE_DIAMETER, 7.36, units="ft") + # self.prob.model.set_input_defaults( + # Aircraft.Engine.REFERENCE_SLS_THRUST, 28620.0, units="lbf" + # ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALE_FACTOR, 0.594, units='unitless' + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.2095, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Nacelle.FINENESS, 1.715, units="unitless") + self.prob.model.set_input_defaults(Aircraft.Wing.FOLDED_SPAN, 118, units="ft") + + self.prob.model.set_input_defaults( + Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" + ) + + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CARGO_MASS, val=15970.0, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.SWEEP, val=0, units='deg' + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.232, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.289, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.12, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" + ) # Based onlarge single aisle 1for updated flaps mass model + self.prob.model.set_input_defaults( + Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" + ) # Based on large single aisle 1 for updated flaps mass model + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.95, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=16.5, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.CLEARANCE_RATIO, val=0.2, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SPECIFIC, val=0.2355, units="lbm/lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.MASS_SPECIFIC, val=3, units="lbm/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.165, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0.15, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.APU.MASS, val=1014.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.085, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.105, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Avionics.MASS, val=1504.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.AntiIcing.MASS, val=126.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Furnishings.MASS, val=9114.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=0.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=10.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_COEFFICIENT, val=85, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.FOLD_MASS_COEFFICIENT, val=0.2, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_COEFFICIENT, val=128, units="unitless" + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' + ) # note: not actually defined in program, likely an error + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.041, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_MARGIN, val=10.0, units="unitless" + ) + + self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + + self.prob.setup(check=False, force_alloc_complex=True) + + def test_case1(self): + + self.prob.run_model() + + tol = 5e-4 + # size values: + assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) + assert_near_equal(self.prob["size.fuselage.cabin_len"], 61.6, tol) + assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + + assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 16.91, tol) + assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 16.01, tol) + assert_near_equal( + self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1132, tol + ) # slightly different from GASP value, likely a rounding error + + assert_near_equal( + self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.6498, tol + # note: value came from running the GASP code on my own and printing it out (GASP output calculates this differently) + ) + assert_near_equal( + self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 13.4662, tol + # note: value came from running the GASP code on my own and printing it out (GASP output calculates this differently) + ) + assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 11.77, tol) + + # fixed mass values: + assert_near_equal( + self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 5219.3076, tol + # self.prob["fixed_mass.main_gear_mass"], 5219.3076, tol + ) # note: value came from running the GASP code on my own and printing it out + + assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 8007, tol) + assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1321/2, tol) + + # wing values: + assert_near_equal( + self.prob["wing_mass.isolated_wing_mass"], 13993, tol + ) # calculated as difference between wing mass and fold mass, not an actual GASP variable + + # fuel values: + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 63452.2, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 62427.2 + + assert_near_equal( + self.prob["fuel_mass.fus_mass_full"], 99396.7, tol + ) # note: value came from running the GASP code on my own and printing it out + assert_near_equal( + self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1472.6, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1426 + + assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 45373.4, tol) + assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 18859.9, tol) + + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS_REQUIRED], 32652.2, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 31627.2 + assert_near_equal( + self.prob[Aircraft.Propulsion.MASS], 10800.8, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 10755.0 + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS], 32652.2, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 31627.0 + assert_near_equal( + self.prob["fuel_mass.fuel_mass_min"], 16682.2, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 15657.2 + assert_near_equal( + self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 718.03, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 695.5 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1268.48, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1248.0 + assert_near_equal( + self.prob[Aircraft.Design.OPERATING_MASS], 81935.8, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 82961.0 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 30800.0039, tol + ) # note: value came from running the GASP code on my own and printing it out + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 33892.8, tol + ) + assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 33892.8, tol) + assert_near_equal(self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol) + assert_near_equal( + self.prob["fuel_mass.body_tank.extra_fuel_volume"], 40.4789, 0.005 + ) # note: higher tol because slightly different from GASP value, likely numerical issues, #modified from GASP value to account for updated crew mass. GASP value is 17.9 + assert_near_equal( + self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 2024.70, 0.003 + ) # note: higher tol because slightly different from GASP value, likely numerical issues, #modified from GASP value to account for updated crew mass. GASP value is 897.2 + + partial_data = self.prob.check_partials(out_stream=None, method="cs") + assert_check_partials(partial_data, atol=3e-9, rtol=6e-11) + + +class MassSummationTestCase8(unittest.TestCase): + """ + This is the Trans-sonic Truss-Braced Wing V3.6 test case + All values are from V3.6 output, hand calculated from the output, or were printed out after running the code manually. + Values not directly from the output are labeled as such. + """ + + def setUp(self): + + options = get_option_defaults() + options.set_val(Aircraft.Wing.HAS_FOLD, val=True, units='unitless') + options.set_val(Aircraft.Wing.HAS_STRUT, val=True, units='unitless') + options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, + val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') + options.set_val(Mission.Design.CRUISE_ALTITUDE, val=43000, units='ft') + options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') + options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.LandingGear.FIXED_GEAR, + val=False, units='unitless') + options.set_val(Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, + val=True, units='unitless') + options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, + val=200, units="lbm") + options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) + options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") + options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) + options.set_val(Aircraft.Fuselage.SEAT_PITCH, 44.2, units="inch") + options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + + self.prob = om.Problem() + self.prob.model.add_subsystem( + "size", + SizeGroup( + aviary_options=options, + ), + promotes_inputs=["aircraft:*", "mission:*"], + promotes_outputs=[ + "aircraft:*", + ], + ) + self.prob.model.add_subsystem( + "GASP_mass", + MassPremission( + aviary_options=options, + ), + promotes=["*"], + ) + + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MOMENT_RATIO, val=0.13067, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.ASPECT_RATIO, val=4.025, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MOMENT_RATIO, 3.0496, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.REFERENCE_DIAMETER, 7.642, units="ft") + # self.prob.model.set_input_defaults( + # Aircraft.Engine.REFERENCE_SLS_THRUST, 28620.0, units="lbf" + # ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALE_FACTOR, 1.35255, units='unitless' + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.2095, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Nacelle.FINENESS, 1.660, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 6.85, units="ft" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.TAIL_FINENESS, 1.18, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.WETTED_AREA_SCALER, 1.0, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.LOADING, val=87.5, units="lbf/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" + ) + + self.prob.model.set_input_defaults( + Aircraft.APU.MASS, val=1014.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.085, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.105, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Avionics.MASS, val=1504.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.AntiIcing.MASS, val=126.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Furnishings.MASS, val=9114.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=0.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=10.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALED_SLS_THRUST, val=21160.0, units="lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALE_FACTOR, 0.73934, units='unitless' + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.WING_FUEL_FRACTION, 0.5625, units="unitless" + ) + self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=22.47, units="deg") + self.prob.model.set_input_defaults( + Aircraft.Wing.MOUNTING_TYPE, val=.1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.ASPECT_RATIO, val=19.565, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Strut.ATTACHMENT_LOCATION, val=118, units="ft" + ) + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CARGO_MASS, val=15970.0, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SPECIFIC, val=0.2470, units="lbm/lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.MASS_SPECIFIC, val=2.5, units="lbm/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.163, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Engine.WING_LOCATIONS, val=0.2143, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.ASPECT_RATIO, val=0.825, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.SWEEP, val=0, units='deg' + ) # not in file + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.2076, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.2587, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.11, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" + ) # Based onlarge single aisle 1for updated flaps mass model + self.prob.model.set_input_defaults( + Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" + ) # Based on large single aisle 1 for updated flaps mass model + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.5936, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=30, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=0, units="lbm" + ) # not in file + self.prob.model.set_input_defaults( + Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" + ) # not in file + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MASS_COEFFICIENT, val=0.03390, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_MARGIN, val=10.0, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.060, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_COEFFICIENT, val=89.66, units="unitless" + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' + ) # not in file + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Mission.Design.GROSS_MASS, val=143100.0, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_COEFFICIENT, val=78.94, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.TAPER_RATIO, val=0.346, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.11, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.43, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.066, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.FOLD_MASS_COEFFICIENT, val=0.2, units="unitless" + ) + # self.prob.model.set_input_defaults( + # Aircraft.Strut.AREA, 523.337, units="ft**2" + # ) # had to calculate by hand + self.prob.model.set_input_defaults( + Aircraft.Strut.MASS_COEFFICIENT, 0.238, units="unitless" + ) + + self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + + self.prob.setup(check=False, force_alloc_complex=True) + + def test_case1(self): + + self.prob.run_model() + + tol = 5e-4 + # size values: + assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) + assert_near_equal(self.prob["size.fuselage.cabin_len"], 93.9, tol) + assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + + assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 13.59, tol) + assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 13.15, tol) + assert_near_equal( + self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1068, tol + ) # note:precision came from running code on my own and printing it out + + assert_near_equal( + self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.381, tol + ) # note, printed out manually because calculated differently in output subroutine + assert_near_equal( + self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 20.056, tol + ) # note, printed out manually because calculated differently in output subroutine + assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 13.19, tol) + + # fixed mass values: + assert_near_equal( + self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 4123.4, tol + # self.prob["fixed_mass.main_gear_mass"], 4123.4, tol + ) # note:printed out from GASP code + + assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 10453.0, tol) + assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 1704.0/2, tol) + + # wing values: + assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 14040, tol) + assert_near_equal(self.prob[Aircraft.Wing.MASS], 18031, tol) + + # fuel values: + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 60410.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 59372.3 + + assert_near_equal( + self.prob["fuel_mass.fus_mass_full"], 97697.5, tol + ) # note:printed out from GASP code + assert_near_equal( + self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 1954.3, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1886.0 + + assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 43660.4, tol) + assert_near_equal(self.prob[Aircraft.Fuselage.MASS], 14657.4, tol) + + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS_REQUIRED], 29610.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 28572.3 + assert_near_equal( + self.prob[Aircraft.Propulsion.MASS], 14111.2, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 14043.0 + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS], 29610.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 28572.0 + assert_near_equal( + self.prob["fuel_mass.fuel_mass_min"], 13640.9, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 12602.3 + assert_near_equal( + self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 651.15, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 628.3 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1207.68, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1186.9 + assert_near_equal( + self.prob[Aircraft.Design.OPERATING_MASS], 82689.1, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 83728.0 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 30800.0, tol + ) # note:printed out from GASP code + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 31051.6, tol + ) + assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 31051.6, tol) + assert_near_equal(self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol) + assert_near_equal( + self.prob["fuel_mass.body_tank.extra_fuel_volume"], 30.3942, 0.009 + ) # note: higher tol because slightly different from GASP value, likely numerical issues, printed out from the GASP code, #modified from GASP value to account for updated crew mass. GASP value is 7.5568 + assert_near_equal( + self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 1520.384, 0.009 + ) # note: higher tol because slightly different from GASP value, likely numerical issues, printed out from the GASP code, #modified from GASP value to account for updated crew mass. GASP value is 378.0062 + + partial_data = self.prob.check_partials(out_stream=None, method="cs") + assert_check_partials(partial_data, atol=3e-9, rtol=6e-11) + + +class MassSummationTestCase9(unittest.TestCase): + """ + This is the electrified Trans-sonic Truss-Braced Wing V3.6 test case + All values are from V3.6 output, hand calculated from the output, or were printed out after running the code manually. + Values not directly from the output are labeled as such. + """ + + def setUp(self): + + options = get_option_defaults() + options.set_val(Aircraft.Wing.HAS_FOLD, val=True, units='unitless') + options.set_val(Aircraft.Wing.HAS_STRUT, val=True, units='unitless') + options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') + options.set_val(Mission.Design.CRUISE_ALTITUDE, val=43000, units='ft') + options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') + options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED, + val=True, units='unitless') + options.set_val(Aircraft.LandingGear.FIXED_GEAR, + val=False, units='unitless') + options.set_val(Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, + val=True, units='unitless') + options.set_val(Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, + val=200, units="lbm") + options.set_val(Aircraft.Fuselage.NUM_SEATS_ABREAST, 6) + options.set_val(Aircraft.Fuselage.AISLE_WIDTH, 24, units="inch") + options.set_val(Aircraft.Fuselage.NUM_AISLES, 1) + options.set_val(Aircraft.Fuselage.SEAT_PITCH, 44.2, units="inch") + options.set_val(Aircraft.Fuselage.SEAT_WIDTH, 20.2, units="inch") + + self.prob = om.Problem() + self.prob.model.add_subsystem( + "size", + SizeGroup( + aviary_options=options, + ), + promotes_inputs=["aircraft:*", "mission:*"], + promotes_outputs=[ + "aircraft:*", + ], + ) + self.prob.model.add_subsystem( + "GASP_mass", + MassPremission( + aviary_options=options, + ), + promotes=["*"], + ) + + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.TAPER_RATIO, val=0.352, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MOMENT_RATIO, val=0.13067, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.ASPECT_RATIO, val=4.025, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MOMENT_RATIO, 3.0496, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.TAPER_RATIO, val=0.801, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.REFERENCE_DIAMETER, 8.425, units="ft") + # self.prob.model.set_input_defaults( + # Aircraft.Engine.REFERENCE_SLS_THRUST, 28620, units="lbf" + # ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALE_FACTOR, 0.73934, units='unitless' + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.CORE_DIAMETER_RATIO, 1.2095, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Nacelle.FINENESS, 1.569, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Fuselage.DELTA_DIAMETER, 4.5, units="ft" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.NOSE_FINENESS, 1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PILOT_COMPARTMENT_LENGTH, 6.85, units="ft" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.TAIL_FINENESS, 1.18, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.WETTED_AREA_SCALER, 1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.LOADING, val=96.10, units="lbf/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_TIP, 0.1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.MAX_STRUCTURAL_SPEED, val=402.5, units="mi/h" + ) + + self.prob.model.set_input_defaults( + Aircraft.APU.MASS, val=1014.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Instruments.MASS_COEFFICIENT, val=0.0736, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.FLIGHT_CONTROL_MASS_COEFFICIENT, val=0.085, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Hydraulics.GEAR_MASS_COEFFICIENT, val=0.105, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Avionics.MASS, val=1504.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.AirConditioning.MASS_COEFFICIENT, val=1.65, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.AntiIcing.MASS, val=126.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Furnishings.MASS, val=9114.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.PASSENGER_SERVICE_MASS_PER_PASSENGER, val=5.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.WATER_MASS_PER_OCCUPANT, val=3.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Design.EMERGENCY_EQUIPMENT_MASS, val=0.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CATERING_ITEMS_MASS_PER_PASSENGER, val=10.0, units="lbm") + self.prob.model.set_input_defaults( + Aircraft.Fuel.UNUSABLE_FUEL_MASS_COEFFICIENT, val=12.0, units="unitless") + + self.prob.model.set_input_defaults( + Aircraft.Fuselage.PRESSURE_DIFFERENTIAL, val=7.5, units="psi") + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALED_SLS_THRUST, val=23750.0, units="lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.SCALE_FACTOR, 0.82984, units='unitless' + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.WING_FUEL_FRACTION, 0.5936, units="unitless" + ) + self.prob.model.set_input_defaults(Aircraft.Wing.SWEEP, val=22.47, units="deg") + self.prob.model.set_input_defaults( + Aircraft.Wing.MOUNTING_TYPE, val=.1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.ASPECT_RATIO, val=19.565, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Strut.ATTACHMENT_LOCATION, val=118.0, units="ft" + ) + self.prob.model.set_input_defaults( + Aircraft.CrewPayload.CARGO_MASS, val=15970.0, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SPECIFIC, val=0.2744, units="lbm/lbf" + ) + self.prob.model.set_input_defaults( + Aircraft.Nacelle.MASS_SPECIFIC, val=2.5, units="lbm/ft**2" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.PYLON_FACTOR, val=1.25, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.ADDITIONAL_MASS_FRACTION, val=0.163, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Propulsion.MISC_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Engine.WING_LOCATIONS, val=0.2143, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_LOCATION, val=0, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.ASPECT_RATIO, val=0.825, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.SWEEP, val=0, units='deg' + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_COEFFICIENT, val=0.2076, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TAIL_HOOK_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_COEFFICIENT, val=0.2587, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.THICKNESS_TO_CHORD, val=0.11, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.THICKNESS_TO_CHORD, val=0.1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.HIGH_LIFT_MASS_COEFFICIENT, val=1.9, units="unitless" + ) # Based onlarge single aisle 1for updated flaps mass model + self.prob.model.set_input_defaults( + Mission.Landing.LIFT_COEFFICIENT_MAX, val=2.817, units="unitless" + ) # Based on large single aisle 1 for updated flaps mass model + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_COEFFICIENT, val=0.5936, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.COCKPIT_CONTROL_MASS_COEFFICIENT, val=30.0, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS, val=1, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.Controls.COCKPIT_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Wing.SURFACE_CONTROL_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.STABILITY_AUGMENTATION_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Aircraft.Controls.TOTAL_MASS, val=0, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MASS_COEFFICIENT, val=0.03390, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.DENSITY, val=6.687, units="lbm/galUS" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_MARGIN, val=0.0, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, val=0.060, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_COEFFICIENT, val=96.94, units="unitless" + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.pylon_len", val=0, units='ft' + ) + self.prob.model.set_input_defaults( + "fuel_mass.fus_and_struct.MAT", val=0, units='lbm' + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Fuselage.MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.TOTAL_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Engine.POD_MASS_SCALER, val=1, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Design.STRUCTURAL_MASS_INCREMENT, val=0, units='lbm' + ) + self.prob.model.set_input_defaults( + Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, val=1, units="unitless") + self.prob.model.set_input_defaults( + Mission.Design.GROSS_MASS, val=166100.0, units="lbm" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.MASS_COEFFICIENT, val=78.94, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.TAPER_RATIO, val=0.346, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=0.11, units="unitless" + ) + + self.prob.model.set_input_defaults( + Aircraft.HorizontalTail.VOLUME_COEFFICIENT, val=1.43, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.VerticalTail.VOLUME_COEFFICIENT, 0.066, units="unitless" + ) + self.prob.model.set_input_defaults( + Aircraft.Wing.FOLD_MASS_COEFFICIENT, val=0.2, units="unitless" + ) + # self.prob.model.set_input_defaults( + # Aircraft.Strut.AREA, 553.1, units="ft**2" + # ) + self.prob.model.set_input_defaults( + Aircraft.Strut.MASS_COEFFICIENT, 0.238, units="unitless" + ) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.motor_power", 830, units="kW" + ) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.motor_voltage", 850, units="V" + ) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.max_amp_per_wire", 260, units="A" + ) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.safety_factor", 1, units="unitless" + ) # (not in this GASP code) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.wire_area", 0.0015, units="ft**2" + ) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.rho_wire", 565, units="lbm/ft**3" + ) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.battery_energy", 6077, units="MJ" + ) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.motor_eff", 0.98, units="unitless" + ) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.inverter_eff", 0.99, units="unitless" + ) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.transmission_eff", 0.975, units="unitless" + ) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.battery_eff", 0.975, units="unitless" + ) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.rho_battery", 0.5, units="kW*h/kg" + ) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.motor_spec_mass", 4, units="hp/lbm" + ) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.inverter_spec_mass", 12, units="kW/kg" + ) + self.prob.model.set_input_defaults( + "fixed_mass.augmentation.TMS_spec_mass", 0.125, units="lbm/kW" + ) + + self.prob.model.set_input_defaults(Aircraft.Wing.SPAN, val=0.0, units="ft") + + self.prob.setup(check=False, force_alloc_complex=True) + + def test_case1(self): + + self.prob.run_model() + + tol = 5e-4 + # size values: + assert_near_equal(self.prob["size.fuselage.cabin_height"], 13.1, tol) + assert_near_equal(self.prob["size.fuselage.cabin_len"], 93.9, tol) + assert_near_equal(self.prob["size.fuselage.nose_height"], 8.6, tol) + + assert_near_equal(self.prob[Aircraft.Wing.CENTER_CHORD], 13.97, tol) + assert_near_equal(self.prob[Aircraft.Wing.ROOT_CHORD], 13.53, tol) + assert_near_equal( + self.prob[Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED], 0.1068, tol + ) # (printed out from GASP code to get better precision) + + assert_near_equal( + self.prob[Aircraft.HorizontalTail.AVERAGE_CHORD], 9.644, tol + ) # (printed out from GASP code) + assert_near_equal( + self.prob[Aircraft.VerticalTail.AVERAGE_CHORD], 20.618, tol + ) # (printed out from GASP code) + assert_near_equal(self.prob[Aircraft.Nacelle.AVG_LENGTH], 14.56, tol) + + # fixed mass values: + assert_near_equal( + self.prob[Aircraft.LandingGear.MAIN_GEAR_MASS], 4786.2, tol + ) # (printed out from GASP code) + + assert_near_equal(self.prob[Aircraft.Propulsion.TOTAL_ENGINE_MASS], 13034.0, tol) + assert_near_equal(self.prob[Aircraft.Engine.ADDITIONAL_MASS], 2124.5/2, tol) + + # wing values: + assert_near_equal(self.prob["wing_mass.isolated_wing_mass"], 15895, tol) + assert_near_equal(self.prob[Aircraft.Wing.MASS], 20461.7, tol) + + # fuel values: + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_wingfuel_mass"], 64594.0, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 63707.6 + + assert_near_equal( + self.prob["fuel_mass.fus_mass_full"], 108803.9, tol + ) # (printed out from GASP code), #modified from GASP value to account for updated crew mass. GASP value is 108754.4 + assert_near_equal( + self.prob[Aircraft.Fuel.FUEL_SYSTEM_MASS], 2027.6, 0.00055 + ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 1974.5 + + assert_near_equal(self.prob[Aircraft.Design.STRUCTURE_MASS], 49582, tol) + assert_near_equal( + self.prob[Aircraft.Fuselage.MASS], 16313.0, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 16436.0 + + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS_REQUIRED], 33794.0, 0.00058 + ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 32907.6 + assert_near_equal( + self.prob[Aircraft.Propulsion.MASS], 26565.2, 0.00054 + ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 26527.0 + assert_near_equal( + self.prob[Mission.Design.FUEL_MASS], 33794.0, 0.00056 + ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 32908 + assert_near_equal( + self.prob["fuel_mass.fuel_mass_min"], 17824.0, 0.0012 + ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 16937.6 + assert_near_equal( + self.prob[Aircraft.Fuel.WING_VOLUME_DESIGN], 675.58, 0.00051 + ) # slightly above tol, due to non-integer number of wires, #modified from GASP value to account for updated crew mass. GASP value is 657.9 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.OEM_fuel_vol"], 1291.31, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 1273.6 + assert_near_equal( + self.prob[Aircraft.Design.OPERATING_MASS], 101506.0, tol + ) # modified from GASP value to account for updated crew mass. GASP value is 102392.0 + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.payload_mass_max_fuel"], 30800.0, tol + ) # (printed out from GASP code) + assert_near_equal( + self.prob["fuel_mass.fuel_and_oem.volume_wingfuel_mass"], 35042.1, tol + ) + assert_near_equal(self.prob["fuel_mass.max_wingfuel_mass"], 35042.1, tol) + assert_near_equal(self.prob[Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY], 0, tol) + assert_near_equal( + self.prob["fuel_mass.body_tank.extra_fuel_volume"], 0, tol + ) + assert_near_equal( + self.prob["fuel_mass.body_tank.max_extra_fuel_mass"], 0, tol + ) + + assert_near_equal(self.prob[Aircraft.Electrical.HYBRID_CABLE_LENGTH], 65.6, tol) + assert_near_equal( + self.prob["fixed_mass.aug_mass"], 9394.3, 0.0017 + ) # slightly above tol, due to non-integer number of wires + + partial_data = self.prob.check_partials(out_stream=None, method="cs") + assert_check_partials(partial_data, atol=3e-9, rtol=6e-11) if __name__ == "__main__": From 2107ea5151d47f495e0422163210574c07fd12bc Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 26 Sep 2024 10:24:32 -0400 Subject: [PATCH 075/113] added Design.NUM_PASSENGERS for many test_mass_summation.py tests --- .../mass/gasp_based/test/test_mass_summation.py | 16 ++++++++++++++++ aviary/utils/preprocessors.py | 4 ++-- 2 files changed, 18 insertions(+), 2 deletions(-) diff --git a/aviary/subsystems/mass/gasp_based/test/test_mass_summation.py b/aviary/subsystems/mass/gasp_based/test/test_mass_summation.py index 4101e5325..b1924dac6 100644 --- a/aviary/subsystems/mass/gasp_based/test/test_mass_summation.py +++ b/aviary/subsystems/mass/gasp_based/test/test_mass_summation.py @@ -174,6 +174,8 @@ def setUp(self): options = get_option_defaults() options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') @@ -563,6 +565,8 @@ def setUp(self): options = get_option_defaults() options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') @@ -943,6 +947,8 @@ def setUp(self): options = get_option_defaults() options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') @@ -1324,6 +1330,8 @@ def setUp(self): options = get_option_defaults() options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') @@ -1704,6 +1712,8 @@ def setUp(self): options = get_option_defaults() options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=180, units='unitless') options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=180, units='unitless') options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37500, units='ft') options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') @@ -2086,6 +2096,8 @@ def setUp(self): options.set_val(Aircraft.Wing.HAS_FOLD, val=True, units='unitless') options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=154, units='unitless') options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') options.set_val(Mission.Design.CRUISE_ALTITUDE, val=37100, units='ft') options.set_val(Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, @@ -2474,6 +2486,8 @@ def setUp(self): options.set_val(Aircraft.Wing.HAS_STRUT, val=True, units='unitless') options.set_val(Aircraft.Electrical.HAS_HYBRID_SYSTEM, val=False, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=154, units='unitless') options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') options.set_val(Mission.Design.CRUISE_ALTITUDE, val=43000, units='ft') options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') @@ -2868,6 +2882,8 @@ def setUp(self): options = get_option_defaults() options.set_val(Aircraft.Wing.HAS_FOLD, val=True, units='unitless') options.set_val(Aircraft.Wing.HAS_STRUT, val=True, units='unitless') + options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, + val=154, units='unitless') options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, val=154, units='unitless') options.set_val(Mission.Design.CRUISE_ALTITUDE, val=43000, units='ft') options.set_val(Aircraft.Wing.CHOOSE_FOLD_LOCATION, val=False, units='unitless') diff --git a/aviary/utils/preprocessors.py b/aviary/utils/preprocessors.py index 3e6e1413c..29481c3f2 100644 --- a/aviary/utils/preprocessors.py +++ b/aviary/utils/preprocessors.py @@ -139,8 +139,8 @@ def preprocess_crewpayload(aviary_options: AviaryValues): raise om.AnalysisError( f"ERROR: In preprocesssors.py: NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)}) is larger than the number of seats set by Design.NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS)}) .") - dnp = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) - print(f"INFO: In preprocessor.py: Aircraft has been designed for {dnp} passengers.") + # dnp = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) + # print(f"INFO: In preprocessor.py: Aircraft has been designed for {dnp} passengers.") if Aircraft.CrewPayload.NUM_FLIGHT_ATTENDANTS not in aviary_options: flight_attendants_count = 0 # assume no passengers From ab89254172bc7092fbe0c47183b300ba2fdf6f51 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 26 Sep 2024 11:25:58 -0400 Subject: [PATCH 076/113] fortran_to_aviary fixes --- .../models/large_single_aisle_1/large_single_aisle_1_GwGm.csv | 2 +- aviary/variable_info/variable_meta_data.py | 2 +- 2 files changed, 2 insertions(+), 2 deletions(-) diff --git a/aviary/models/large_single_aisle_1/large_single_aisle_1_GwGm.csv b/aviary/models/large_single_aisle_1/large_single_aisle_1_GwGm.csv index bcdd6d0a0..7a0a23fd2 100644 --- a/aviary/models/large_single_aisle_1/large_single_aisle_1_GwGm.csv +++ b/aviary/models/large_single_aisle_1/large_single_aisle_1_GwGm.csv @@ -9,7 +9,7 @@ aircraft:controls:stability_augmentation_system_mass,0,lbm aircraft:controls:stability_augmentation_system_mass_scaler,1,unitless aircraft:crew_and_payload:cargo_mass,10040,lbm aircraft:crew_and_payload:catering_items_mass_per_passenger,7.6,lbm -aircraft:crew_and_payload:num_passengers,180,unitless +aircraft:crew_and_payload:design:num_passengers,180,unitless aircraft:crew_and_payload:passenger_mass_with_bags,200,lbm aircraft:crew_and_payload:passenger_service_mass_per_passenger,5,lbm aircraft:crew_and_payload:water_mass_per_occupant,3,lbm diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index be75473e2..d8af7858c 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -927,7 +927,7 @@ add_meta_data( Aircraft.CrewPayload.NUM_PASSENGERS, meta_data=_MetaData, - historical_name={"GASP": 'INGASP.PAX', + historical_name={"GASP": None, # 'INGASP.PAX' here we assume previous studies were changing Design.num_pax not as-flown "FLOPS": None, # ['CSTDAT.NSV', '~WEIGHT.NPASS', '~WTSTAT.NPASS'], "LEAPS1": None, # 'aircraft.outputs.L0_crew_and_payload.passenger_count' }, From 38ba1933729efeba95de240a03c7b416c209c0a8 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 26 Sep 2024 11:27:40 -0400 Subject: [PATCH 077/113] fortran to aviary fixes --- aviary/models/small_single_aisle/small_single_aisle_GwGm.csv | 2 +- aviary/variable_info/variable_meta_data.py | 2 +- 2 files changed, 2 insertions(+), 2 deletions(-) diff --git a/aviary/models/small_single_aisle/small_single_aisle_GwGm.csv b/aviary/models/small_single_aisle/small_single_aisle_GwGm.csv index df8ea4f96..505465acd 100644 --- a/aviary/models/small_single_aisle/small_single_aisle_GwGm.csv +++ b/aviary/models/small_single_aisle/small_single_aisle_GwGm.csv @@ -9,7 +9,7 @@ aircraft:controls:stability_augmentation_system_mass,0,lbm aircraft:controls:stability_augmentation_system_mass_scaler,1,unitless aircraft:crew_and_payload:cargo_mass,8598,lbm aircraft:crew_and_payload:catering_items_mass_per_passenger,6,lbm -aircraft:crew_and_payload:num_passengers,96,unitless +aircraft:crew_and_payload:design:num_passengers,96,unitless aircraft:crew_and_payload:passenger_mass_with_bags,210,lbm aircraft:crew_and_payload:passenger_service_mass_per_passenger,7.6,lbm aircraft:crew_and_payload:water_mass_per_occupant,3,lbm diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index d8af7858c..21c920c2f 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -735,7 +735,7 @@ add_meta_data( Aircraft.CrewPayload.Design.NUM_PASSENGERS, meta_data=_MetaData, - historical_name={"GASP": 'INGASP.PAX', + historical_name={"GASP": 'INGASP.PAX', # number of passenger seats excluding crew "FLOPS": None, # ['CSTDAT.NSV', '~WEIGHT.NPASS', '~WTSTAT.NPASS'], "LEAPS1": 'aircraft.outputs.L0_crew_and_payload.passenger_count' }, From b3357a0499ff4cb0b8811051e4e0e562f0b75387 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 26 Sep 2024 11:40:51 -0400 Subject: [PATCH 078/113] resolved test_fortran_to_aviary alphabetical ordering required in .csv --- .../models/N3CC/N3CC_generic_low_speed_polars_FLOPSinp.csv | 6 +++--- 1 file changed, 3 insertions(+), 3 deletions(-) diff --git a/aviary/models/N3CC/N3CC_generic_low_speed_polars_FLOPSinp.csv b/aviary/models/N3CC/N3CC_generic_low_speed_polars_FLOPSinp.csv index e48a34fdc..6244f4015 100644 --- a/aviary/models/N3CC/N3CC_generic_low_speed_polars_FLOPSinp.csv +++ b/aviary/models/N3CC/N3CC_generic_low_speed_polars_FLOPSinp.csv @@ -7,16 +7,16 @@ aircraft:canard:laminar_flow_lower,0,unitless aircraft:canard:laminar_flow_upper,0,unitless aircraft:canard:mass_scaler,1,unitless aircraft:crew_and_payload:baggage_mass_per_passenger,35,lbm +aircraft:crew_and_payload:design:num_business_class,20,unitless +aircraft:crew_and_payload:design:num_first_class,16,unitless +aircraft:crew_and_payload:design:num_tourist_class,118,unitless aircraft:crew_and_payload:flight_crew_mass_scaler,1,unitless aircraft:crew_and_payload:mass_per_passenger,165,lbm aircraft:crew_and_payload:misc_cargo,0,lbm aircraft:crew_and_payload:non_flight_crew_mass_scaler,1,unitless -aircraft:crew_and_payload:num_business_class,20,unitless -aircraft:crew_and_payload:num_first_class,16,unitless aircraft:crew_and_payload:num_flight_attendants,-1,unitless aircraft:crew_and_payload:num_flight_crew,-1,unitless aircraft:crew_and_payload:num_galley_crew,-1,unitless -aircraft:crew_and_payload:num_tourist_class,118,unitless aircraft:crew_and_payload:passenger_service_mass_scaler,1,unitless aircraft:crew_and_payload:wing_cargo,0,lbm aircraft:design:base_area,0,ft**2 From 62bceeace8d5d249373cbe91af361a6d4bc9eb27 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 26 Sep 2024 11:44:29 -0400 Subject: [PATCH 079/113] pep8 --- aviary/subsystems/mass/flops_based/electrical.py | 6 ++++-- aviary/subsystems/mass/flops_based/furnishings.py | 12 ++++++++---- .../subsystems/mass/flops_based/passenger_service.py | 6 ++++-- .../mass/gasp_based/equipment_and_useful_load.py | 6 ++++-- 4 files changed, 20 insertions(+), 10 deletions(-) diff --git a/aviary/subsystems/mass/flops_based/electrical.py b/aviary/subsystems/mass/flops_based/electrical.py index 90f050cbc..1430945f7 100644 --- a/aviary/subsystems/mass/flops_based/electrical.py +++ b/aviary/subsystems/mass/flops_based/electrical.py @@ -33,7 +33,8 @@ def compute(self, inputs, outputs): options: AviaryValues = self.options['aviary_options'] nfuse = options.get_val(Aircraft.Fuselage.NUM_FUSELAGES) ncrew = options.get_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW) - npass = options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') + npass = options.get_val( + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') length = inputs[Aircraft.Fuselage.LENGTH] width = inputs[Aircraft.Fuselage.MAX_WIDTH] num_eng = options.get_val(Aircraft.Propulsion.TOTAL_NUM_ENGINES) @@ -48,7 +49,8 @@ def compute_partials(self, inputs, J): options: AviaryValues = self.options['aviary_options'] nfuse = options.get_val(Aircraft.Fuselage.NUM_FUSELAGES) ncrew = options.get_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW) - npass = options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') + npass = options.get_val( + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') length = inputs[Aircraft.Fuselage.LENGTH] width = inputs[Aircraft.Fuselage.MAX_WIDTH] num_eng = options.get_val(Aircraft.Propulsion.TOTAL_NUM_ENGINES) diff --git a/aviary/subsystems/mass/flops_based/furnishings.py b/aviary/subsystems/mass/flops_based/furnishings.py index 6146caffa..3dfa8416b 100644 --- a/aviary/subsystems/mass/flops_based/furnishings.py +++ b/aviary/subsystems/mass/flops_based/furnishings.py @@ -38,7 +38,8 @@ def compute( aviary_options: AviaryValues = self.options['aviary_options'] flight_crew_count = aviary_options.get_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW) - first_class_count = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) + first_class_count = aviary_options.get_val( + Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) business_class_count = aviary_options.get_val( Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) @@ -67,7 +68,8 @@ def compute_partials(self, inputs, J): aviary_options: AviaryValues = self.options['aviary_options'] flight_crew_count = aviary_options.get_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW) - first_class_count = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) + first_class_count = aviary_options.get_val( + Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) business_class_count = aviary_options.get_val( Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) @@ -135,7 +137,8 @@ def compute( aviary_options: AviaryValues = self.options['aviary_options'] flight_crew_count = aviary_options.get_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW) - first_class_count = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) + first_class_count = aviary_options.get_val( + Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) business_class_count = aviary_options.get_val( Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) @@ -173,7 +176,8 @@ def compute_partials(self, inputs, J): aviary_options: AviaryValues = self.options['aviary_options'] flight_crew_count = aviary_options.get_val(Aircraft.CrewPayload.NUM_FLIGHT_CREW) - first_class_count = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) + first_class_count = aviary_options.get_val( + Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) business_class_count = aviary_options.get_val( Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) diff --git a/aviary/subsystems/mass/flops_based/passenger_service.py b/aviary/subsystems/mass/flops_based/passenger_service.py index 0559c6276..7d1688085 100644 --- a/aviary/subsystems/mass/flops_based/passenger_service.py +++ b/aviary/subsystems/mass/flops_based/passenger_service.py @@ -46,7 +46,8 @@ def setup_partials(self): def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None): aviary_options: AviaryValues = self.options['aviary_options'] - first_class_count = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) + first_class_count = aviary_options.get_val( + Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) business_class_count = \ aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) @@ -72,7 +73,8 @@ def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None): def compute_partials(self, inputs, J, discrete_inputs=None): aviary_options: AviaryValues = self.options['aviary_options'] - first_class_count = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) + first_class_count = aviary_options.get_val( + Aircraft.CrewPayload.Design.NUM_FIRST_CLASS) business_class_count = \ aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS) diff --git a/aviary/subsystems/mass/gasp_based/equipment_and_useful_load.py b/aviary/subsystems/mass/gasp_based/equipment_and_useful_load.py index 2749e2cb5..3d4f1972d 100644 --- a/aviary/subsystems/mass/gasp_based/equipment_and_useful_load.py +++ b/aviary/subsystems/mass/gasp_based/equipment_and_useful_load.py @@ -77,7 +77,8 @@ def setup(self): def compute(self, inputs, outputs): options: AviaryValues = self.options["aviary_options"] - PAX = options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') + PAX = options.get_val( + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') smooth = options.get_val( Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, units='unitless') @@ -388,7 +389,8 @@ def compute(self, inputs, outputs): def compute_partials(self, inputs, partials): options = self.options['aviary_options'] - PAX = options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') + PAX = options.get_val( + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') smooth = options.get_val( Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, units='unitless') gross_wt_initial = inputs[Mission.Design.GROSS_MASS] * GRAV_ENGLISH_LBM From 6af83b6a059d25629356ec517deb4cdb374b7063 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 26 Sep 2024 11:48:36 -0400 Subject: [PATCH 080/113] pep8 2! --- aviary/variable_info/variables.py | 1 + 1 file changed, 1 insertion(+) diff --git a/aviary/variable_info/variables.py b/aviary/variable_info/variables.py index 87e6ece12..15350cfa4 100644 --- a/aviary/variable_info/variables.py +++ b/aviary/variable_info/variables.py @@ -127,6 +127,7 @@ class CrewPayload: TOTAL_PAYLOAD_MASS = 'aircraft:crew_and_payload:total_payload_mass' WATER_MASS_PER_OCCUPANT = 'aircraft:crew_and_payload:water_mass_per_occupant' WING_CARGO = 'aircraft:crew_and_payload:wing_cargo' + class Design: NUM_BUSINESS_CLASS = 'aircraft:crew_and_payload:design:num_business_class' NUM_FIRST_CLASS = 'aircraft:crew_and_payload:design:num_first_class' From 8312d5e752989e85a400bfa8bf1a543c69ee2aed Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 26 Sep 2024 12:22:28 -0400 Subject: [PATCH 081/113] better error messages in preprocessor.py --- aviary/models/test_aircraft/aircraft_for_bench_FwGm.csv | 8 ++++---- aviary/utils/preprocessors.py | 8 ++++++-- 2 files changed, 10 insertions(+), 6 deletions(-) diff --git a/aviary/models/test_aircraft/aircraft_for_bench_FwGm.csv b/aviary/models/test_aircraft/aircraft_for_bench_FwGm.csv index fdd379976..64f8adbfa 100644 --- a/aviary/models/test_aircraft/aircraft_for_bench_FwGm.csv +++ b/aviary/models/test_aircraft/aircraft_for_bench_FwGm.csv @@ -2,7 +2,6 @@ aircraft:controls:cockpit_control_mass_scaler,1,unitless aircraft:controls:control_mass_increment,0,lbm aircraft:controls:stability_augmentation_system_mass,0,lbm aircraft:controls:stability_augmentation_system_mass_scaler,1,unitless -aircraft:crew_and_payload:num_passengers,169,unitless aircraft:crew_and_payload:passenger_mass_with_bags,200,lbm aircraft:design:cg_delta,0.25,unitless aircraft:design:cockpit_control_mass_coefficient,16.5,unitless @@ -163,16 +162,17 @@ aircraft:canard:area,0.0,ft**2 aircraft:canard:aspect_ratio,0.0,unitless aircraft:canard:thickness_to_chord,0.0,unitless aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless +aircraft:crew_and_payload:design:num_business_class,0,unitless +aircraft:crew_and_payload:design:num_first_class,11,unitless +aircraft:crew_and_payload:design:num_passengers,169,unitless +aircraft:crew_and_payload:design:num_tourist_class,158,unitless aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless aircraft:crew_and_payload:mass_per_passenger,180.0,lbm aircraft:crew_and_payload:misc_cargo,0.0,lbm aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:num_business_class,0,unitless -aircraft:crew_and_payload:num_first_class,11,unitless aircraft:crew_and_payload:num_flight_attendants,3,unitless aircraft:crew_and_payload:num_flight_crew,2,unitless aircraft:crew_and_payload:num_galley_crew,0,unitless -aircraft:crew_and_payload:num_tourist_class,158,unitless aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless aircraft:crew_and_payload:wing_cargo,0.0,lbm aircraft:design:base_area,0.0,ft**2 diff --git a/aviary/utils/preprocessors.py b/aviary/utils/preprocessors.py index 29481c3f2..df1b4c05d 100644 --- a/aviary/utils/preprocessors.py +++ b/aviary/utils/preprocessors.py @@ -87,11 +87,15 @@ def preprocess_crewpayload(aviary_options: AviaryValues): # have you give us enough info to determine where people were sitting vs. designed seats if num_pax != 0 and design_passenger_count != 0 and passenger_count == 0: raise om.AnalysisError( - f"ERROR: In preprocessor.py: User must specify CrewPayload.FIRST_CLASS, CrewPayload.NUM_BUSINESS_CLASS, Design.NUM_TOURIST_CLASS in aviary_values.") + f"ERROR: In preprocessor.py: The user has specified CrewPayload.NUM_PASSENGERS, and how many of what types of seats are on the aircraft." + f"However, the user has not specified where those passengers are sitting." + f"User must specify CrewPayload.FIRST_CLASS, CrewPayload.NUM_BUSINESS_CLASS, NUM_TOURIST_CLASS in aviary_values.") # where are the people sitting? is first class full? We know how many seats are in each class. if design_num_pax != 0 and passenger_count != 0 and design_passenger_count == 0: raise om.AnalysisError( - f"ERROR: In preprocessor.py: User must specify Design.FIRST_CLASS, Design.NUM_BUSINESS_CLASS, Design.NUM_TOURIST_CLASS in aviary_values.") + f"ERROR: In preprocessor.py: The user has specified Design.NUM_PASSENGERS, and has specified how many people are sitting in each class of seats." + f"However, the user has not specified how many seats of each class exist in the aircraft." + f"User must specify Design.FIRST_CLASS, Design.NUM_BUSINESS_CLASS, Design.NUM_TOURIST_CLASS in aviary_values.") # we don't know which classes this aircraft has been design for. How many 1st class seats are there? # Copy data over if only one set of data exists From dfd19e8074d5a8c6651dcd0ccdc6b914fbbcc602 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 26 Sep 2024 12:35:36 -0400 Subject: [PATCH 082/113] upd GwGm.csv to have design.num_pax because some tests using this file dont use check_and_preprocess_inputs --- aviary/models/test_aircraft/aircraft_for_bench_GwGm.csv | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/aviary/models/test_aircraft/aircraft_for_bench_GwGm.csv b/aviary/models/test_aircraft/aircraft_for_bench_GwGm.csv index cf6ab17bc..2f3c32e0d 100644 --- a/aviary/models/test_aircraft/aircraft_for_bench_GwGm.csv +++ b/aviary/models/test_aircraft/aircraft_for_bench_GwGm.csv @@ -8,7 +8,7 @@ aircraft:controls:stability_augmentation_system_mass,0,lbm aircraft:controls:stability_augmentation_system_mass_scaler,1,unitless aircraft:crew_and_payload:cargo_mass,10040,lbm aircraft:crew_and_payload:catering_items_mass_per_passenger,7.6,lbm -aircraft:crew_and_payload:num_passengers,180,unitless +aircraft:crew_and_payload:design:num_passengers,180,unitless aircraft:crew_and_payload:passenger_mass_with_bags,200,lbm aircraft:crew_and_payload:passenger_service_mass_per_passenger,5,lbm aircraft:crew_and_payload:water_mass_per_occupant,3,lbm From a5dc79149767e7384f43ed34aced6dc4db400fc0 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 26 Sep 2024 13:45:19 -0400 Subject: [PATCH 083/113] added design.pax values to all .csv in test_aircraft --- aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv | 8 ++++---- .../aircraft_for_bench_FwFm_with_electric.csv | 8 ++++---- aviary/models/test_aircraft/aircraft_for_bench_GwFm.csv | 8 ++++---- .../test_aircraft/aircraft_for_bench_GwGm_lbm_s.csv | 2 +- .../test_aircraft/aircraft_for_bench_solved2dof.csv | 8 ++++---- 5 files changed, 17 insertions(+), 17 deletions(-) diff --git a/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv b/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv index c2fa1d8a1..bd9fa3412 100644 --- a/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv +++ b/aviary/models/test_aircraft/aircraft_for_bench_FwFm.csv @@ -7,17 +7,17 @@ aircraft:canard:aspect_ratio,0.0,unitless aircraft:canard:thickness_to_chord,0.0,unitless aircraft:crew_and_payload:baggage_mass_per_passenger,45.0,lbm aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless +aircraft:crew_and_payload:design:num_business_class,0,unitless +aircraft:crew_and_payload:design:num_first_class,11,unitless +aircraft:crew_and_payload:design:num_passengers,169,unitless +aircraft:crew_and_payload:design:num_tourist_class,158,unitless aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless aircraft:crew_and_payload:mass_per_passenger,180.0,lbm aircraft:crew_and_payload:misc_cargo,0.0,lbm aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:num_business_class,0,unitless -aircraft:crew_and_payload:num_first_class,11,unitless aircraft:crew_and_payload:num_flight_attendants,3,unitless aircraft:crew_and_payload:num_flight_crew,2,unitless aircraft:crew_and_payload:num_galley_crew,0,unitless -aircraft:crew_and_payload:num_passengers,169,unitless -aircraft:crew_and_payload:num_tourist_class,158,unitless aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless aircraft:crew_and_payload:wing_cargo,0.0,lbm aircraft:design:base_area,0.0,ft**2 diff --git a/aviary/models/test_aircraft/aircraft_for_bench_FwFm_with_electric.csv b/aviary/models/test_aircraft/aircraft_for_bench_FwFm_with_electric.csv index 1f408f98b..7dcd99288 100644 --- a/aviary/models/test_aircraft/aircraft_for_bench_FwFm_with_electric.csv +++ b/aviary/models/test_aircraft/aircraft_for_bench_FwFm_with_electric.csv @@ -7,17 +7,17 @@ aircraft:canard:aspect_ratio,0.0,unitless aircraft:canard:thickness_to_chord,0.0,unitless aircraft:crew_and_payload:baggage_mass_per_passenger,45.0,lbm aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless +aircraft:crew_and_payload:design:num_business_class,0,unitless +aircraft:crew_and_payload:design:num_first_class,11,unitless +aircraft:crew_and_payload:design:num_passengers,169,unitless +aircraft:crew_and_payload:design:num_tourist_class,158,unitless aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless aircraft:crew_and_payload:mass_per_passenger,180.0,lbm aircraft:crew_and_payload:misc_cargo,0.0,lbm aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:num_business_class,0,unitless -aircraft:crew_and_payload:num_first_class,11,unitless aircraft:crew_and_payload:num_flight_attendants,3,unitless aircraft:crew_and_payload:num_flight_crew,2,unitless aircraft:crew_and_payload:num_galley_crew,0,unitless -aircraft:crew_and_payload:num_passengers,169,unitless -aircraft:crew_and_payload:num_tourist_class,158,unitless aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless aircraft:crew_and_payload:wing_cargo,0.0,lbm aircraft:design:base_area,0.0,ft**2 diff --git a/aviary/models/test_aircraft/aircraft_for_bench_GwFm.csv b/aviary/models/test_aircraft/aircraft_for_bench_GwFm.csv index d27a939e6..703c223d2 100644 --- a/aviary/models/test_aircraft/aircraft_for_bench_GwFm.csv +++ b/aviary/models/test_aircraft/aircraft_for_bench_GwFm.csv @@ -16,17 +16,17 @@ aircraft:controls:stability_augmentation_system_mass,0,lbm aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless aircraft:crew_and_payload:cargo_mass,10040,lbm aircraft:crew_and_payload:catering_items_mass_per_passenger,7.6,lbm +aircraft:crew_and_payload:design:num_business_class,0,unitless +aircraft:crew_and_payload:design:num_first_class,11,unitless +aircraft:crew_and_payload:design:num_passengers,180,unitless +aircraft:crew_and_payload:design:num_tourist_class,169,unitless aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless aircraft:crew_and_payload:mass_per_passenger,180.0,lbm aircraft:crew_and_payload:misc_cargo,0.0,lbm aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:num_business_class,0,unitless -aircraft:crew_and_payload:num_first_class,11,unitless aircraft:crew_and_payload:num_flight_attendants,3,unitless aircraft:crew_and_payload:num_flight_crew,2,unitless aircraft:crew_and_payload:num_galley_crew,0,unitless -aircraft:crew_and_payload:num_passengers,180,unitless -aircraft:crew_and_payload:num_tourist_class,169,unitless aircraft:crew_and_payload:passenger_mass_with_bags,200,lbm aircraft:crew_and_payload:passenger_service_mass_per_passenger,5,lbm aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless diff --git a/aviary/models/test_aircraft/aircraft_for_bench_GwGm_lbm_s.csv b/aviary/models/test_aircraft/aircraft_for_bench_GwGm_lbm_s.csv index b9f818cbd..50a63d10d 100644 --- a/aviary/models/test_aircraft/aircraft_for_bench_GwGm_lbm_s.csv +++ b/aviary/models/test_aircraft/aircraft_for_bench_GwGm_lbm_s.csv @@ -8,7 +8,7 @@ aircraft:controls:stability_augmentation_system_mass,0,lbm aircraft:controls:stability_augmentation_system_mass_scaler,1,unitless aircraft:crew_and_payload:cargo_mass,10040,lbm aircraft:crew_and_payload:catering_items_mass_per_passenger,7.6,lbm -aircraft:crew_and_payload:num_passengers,180,unitless +aircraft:crew_and_payload:design:num_passengers,180,unitless aircraft:crew_and_payload:passenger_mass_with_bags,200,lbm aircraft:crew_and_payload:passenger_service_mass_per_passenger,5,lbm aircraft:crew_and_payload:water_mass_per_occupant,3,lbm diff --git a/aviary/models/test_aircraft/aircraft_for_bench_solved2dof.csv b/aviary/models/test_aircraft/aircraft_for_bench_solved2dof.csv index 1d2c97329..b6848994f 100644 --- a/aviary/models/test_aircraft/aircraft_for_bench_solved2dof.csv +++ b/aviary/models/test_aircraft/aircraft_for_bench_solved2dof.csv @@ -7,17 +7,17 @@ aircraft:canard:aspect_ratio,0.0,unitless aircraft:canard:thickness_to_chord,0.0,unitless aircraft:crew_and_payload:baggage_mass_per_passenger,45.0,lbm aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless +aircraft:crew_and_payload:design:num_business_class,0,unitless +aircraft:crew_and_payload:design:num_first_class,11,unitless +aircraft:crew_and_payload:design:num_passengers,169,unitless +aircraft:crew_and_payload:design:num_tourist_class,158,unitless aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless aircraft:crew_and_payload:mass_per_passenger,180.0,lbm aircraft:crew_and_payload:misc_cargo,0.0,lbm aircraft:crew_and_payload:non_flight_crew_mass_scaler,1.0,unitless -aircraft:crew_and_payload:num_business_class,0,unitless -aircraft:crew_and_payload:num_first_class,11,unitless aircraft:crew_and_payload:num_flight_attendants,3,unitless aircraft:crew_and_payload:num_flight_crew,2,unitless aircraft:crew_and_payload:num_galley_crew,0,unitless -aircraft:crew_and_payload:num_passengers,169,unitless -aircraft:crew_and_payload:num_tourist_class,158,unitless aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless aircraft:crew_and_payload:wing_cargo,0.0,lbm aircraft:design:base_area,0.0,ft**2 From dc50de671fd95d2937ffaacbb6fd8296ac0b462a Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Fri, 27 Sep 2024 09:21:26 -0400 Subject: [PATCH 084/113] added mission.Summary.Range assignment to 2DOF execution path (not 2DOF solved just 2DOF) --- aviary/interface/methods_for_level2.py | 20 ++++++++++++-------- 1 file changed, 12 insertions(+), 8 deletions(-) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index faad9e9d7..d1b967583 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -358,13 +358,17 @@ def load_inputs( self.cruise_mass_final = aviary_inputs.get_val( Mission.Summary.CRUISE_MASS_FINAL, units='lbm') - # if 'target_range' in self.post_mission_info: - # self.target_range = wrapped_convert_units( - # phase_info['post_mission']['target_range'], 'NM') - # else: - print('WARNING: In methods_for_level2: user has not specified target_range in phase_info. This will be required in future release.') - self.target_range = aviary_inputs.get_val( - Mission.Design.RANGE, units='NM') + if self.post_mission_info is True and 'target_range' in self.post_mission_info: + self.target_range = wrapped_convert_units( + phase_info['post_mission']['target_range'], 'NM') + aviary_inputs.set_val(Mission.Summary.RANGE, + self.target_range, units='NM') + else: + print('WARNING: In methods_for_level2: user has not specified target_range in phase_info. This will be required in future releases.') + self.target_range = aviary_inputs.get_val( + Mission.Design.RANGE, units='NM') + aviary_inputs.set_val(Mission.Summary.RANGE, aviary_inputs.get_val( + Mission.Design.RANGE, units='NM'), units='NM') self.cruise_mach = aviary_inputs.get_val(Mission.Design.MACH) self.require_range_residual = True @@ -379,7 +383,7 @@ def load_inputs( self.target_range = wrapped_convert_units( phase_info['post_mission']['target_range'], 'NM') else: - print('WARNING: In methods_for_level2: user has not specified target_range in phase_info. This will be required in future release.') + print('WARNING: In methods_for_level2: user has not specified target_range in phase_info. This will be required in future releases.') self.require_range_residual = False # still instantiate target_range because used for default guesses for phase comps self.target_range = aviary_inputs.get_val( From a7df3feadad1683fcc4752225f6c80e1026a7ac0 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Mon, 7 Oct 2024 13:55:19 -0400 Subject: [PATCH 085/113] changed target range on test_bench_GwGm_shooting to correctly reflect the value set by Mission.Design.Range --- aviary/validation_cases/benchmark_tests/test_bench_GwGm.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/aviary/validation_cases/benchmark_tests/test_bench_GwGm.py b/aviary/validation_cases/benchmark_tests/test_bench_GwGm.py index 34b883d7f..1c10dc162 100644 --- a/aviary/validation_cases/benchmark_tests/test_bench_GwGm.py +++ b/aviary/validation_cases/benchmark_tests/test_bench_GwGm.py @@ -212,7 +212,7 @@ def test_bench_GwGm_shooting(self): ) assert_near_equal( - prob.get_val(Mission.Summary.RANGE, units='NM'), 3774.3, tolerance=rtol + prob.get_val(Mission.Summary.RANGE, units='NM'), 3675.0, tolerance=rtol ) assert_near_equal( From 661b01ea7272cc49385096855dcecd05a3356476 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Tue, 8 Oct 2024 09:44:17 -0400 Subject: [PATCH 086/113] restored link_{first_flight_phase_name}_mass.lhs:mass in methods for level2 --- aviary/interface/methods_for_level2.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index 7c962094a..e242f02b4 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -1510,7 +1510,7 @@ def link_phases(self): ref=10000., add_constraint=True) self.model.connect( f'traj.{first_flight_phase_name}.states:mass', - 'link_climb_mass.lhs:mass', + f'link_{first_flight_phase_name}_mass.lhs:mass', src_indices=[0], flat_src_indices=True, ) From 329aa4327dfc5422dcf9765de2c12b7899e9f9f3 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 10 Oct 2024 14:09:00 -0400 Subject: [PATCH 087/113] moved HE mass connections to post_mission --- aviary/interface/methods_for_level2.py | 34 ++++++++++--------- .../test_battery_in_a_mission.py | 4 +-- 2 files changed, 20 insertions(+), 18 deletions(-) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index e242f02b4..2cd4b806b 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -401,7 +401,7 @@ def load_inputs( else: print('WARNING: In methods_for_level2: user has not specified target_range in phase_info. This will be required in future releases.') self.require_range_residual = False - # still instantiate target_range because used for default guesses for phase comps + # still instantiate target_range because it is used for default guesses for phase comps self.target_range = aviary_inputs.get_val( Mission.Design.RANGE, units='NM') @@ -1380,6 +1380,23 @@ def add_post_mission_systems(self, include_landing=True): self.post_mission.add_constraint( Mission.Constraints.MASS_RESIDUAL, equals=0.0, ref=1.e5) + if self.mission_method is HEIGHT_ENERGY: + # connect summary mass to the initial guess of mass in the first phase + if not self.pre_mission_info['include_takeoff']: + first_flight_phase_name = list(self.phase_info.keys())[0] + eq = self.model.add_subsystem(f'link_{first_flight_phase_name}_mass', + om.EQConstraintComp(), + promotes_inputs=[('rhs:mass', + Mission.Summary.GROSS_MASS)]) + eq.add_eq_output('mass', eq_units='lbm', normalize=False, + ref=10000., add_constraint=True) + self.model.connect( + f'traj.{first_flight_phase_name}.states:mass', + f'link_{first_flight_phase_name}_mass.lhs:mass', + src_indices=[0], + flat_src_indices=True, + ) + def _link_phases_helper_with_options(self, phases, option_name, var, **kwargs): # Initialize a list to keep track of indices where option_name is True true_option_indices = [] @@ -1500,21 +1517,6 @@ def link_phases(self): 'actual_range', src_indices=[-1], flat_src_indices=True) - if not self.pre_mission_info['include_takeoff']: - first_flight_phase_name = list(self.phase_info.keys())[0] - eq = self.model.add_subsystem(f'link_{first_flight_phase_name}_mass', - om.EQConstraintComp(), - promotes_inputs=[('rhs:mass', - Mission.Summary.GROSS_MASS)]) - eq.add_eq_output('mass', eq_units='lbm', normalize=False, - ref=10000., add_constraint=True) - self.model.connect( - f'traj.{first_flight_phase_name}.states:mass', - f'link_{first_flight_phase_name}_mass.lhs:mass', - src_indices=[0], - flat_src_indices=True, - ) - elif self.mission_method is SOLVED_2DOF: self.traj.link_phases(phases, [Dynamic.Mission.MASS], connected=True) self.traj.link_phases( diff --git a/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py b/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py index 640507b70..756932e0d 100644 --- a/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py +++ b/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py @@ -89,8 +89,8 @@ def test_subsystems_in_a_mission(self): prob.run_aviary_problem() electric_energy_used = prob.get_val( - f'traj.cruise.timeseries.{ - av.Dynamic.Mission.CUMULATIVE_ELECTRIC_ENERGY_USED}', + f'traj.cruise.timeseries.' + + f'{av.Dynamic.Mission.CUMULATIVE_ELECTRIC_ENERGY_USED}', units='kW*h', ) fuel_burned = prob.get_val(av.Mission.Summary.FUEL_BURNED, units='lbm') From debc6f2057f90b906491f33a25d8cb2fa53674ed Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 10 Oct 2024 14:20:32 -0400 Subject: [PATCH 088/113] removed target_range warnings because unnecessary in cases where goal is to fly as far as possible --- aviary/interface/methods_for_level2.py | 2 -- 1 file changed, 2 deletions(-) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index 2cd4b806b..b42ceef15 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -380,7 +380,6 @@ def load_inputs( aviary_inputs.set_val(Mission.Summary.RANGE, self.target_range, units='NM') else: - print('WARNING: In methods_for_level2: user has not specified target_range in phase_info. This will be required in future releases.') self.target_range = aviary_inputs.get_val( Mission.Design.RANGE, units='NM') aviary_inputs.set_val(Mission.Summary.RANGE, aviary_inputs.get_val( @@ -399,7 +398,6 @@ def load_inputs( self.target_range = wrapped_convert_units( phase_info['post_mission']['target_range'], 'NM') else: - print('WARNING: In methods_for_level2: user has not specified target_range in phase_info. This will be required in future releases.') self.require_range_residual = False # still instantiate target_range because it is used for default guesses for phase comps self.target_range = aviary_inputs.get_val( From 6ae3b46b76aed56771bdc2d455bde000821dab76 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 10 Oct 2024 14:25:07 -0400 Subject: [PATCH 089/113] removed duplicate code --- aviary/interface/methods_for_level2.py | 7 ------- 1 file changed, 7 deletions(-) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index b42ceef15..9c1294312 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -1158,13 +1158,6 @@ def add_subsystem_timeseries_outputs(phase, phase_name): first_flight_phase.set_state_options(Dynamic.Mission.MASS, fix_initial=False) - if self.mission_method is HEIGHT_ENERGY: - if not self.pre_mission_info['include_takeoff']: - first_flight_phase_name = list(phase_info.keys())[0] - first_flight_phase = traj._phases[first_flight_phase_name] - first_flight_phase.set_state_options(Dynamic.Mission.MASS, - fix_initial=False) - self.traj = traj return traj From b0cf08f7791e825f251315d5a0bc417a643516ac Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 10 Oct 2024 14:55:27 -0400 Subject: [PATCH 090/113] added comments back into methods for level2 --- aviary/interface/methods_for_level2.py | 69 +++++++++++++++++++++++++- 1 file changed, 68 insertions(+), 1 deletion(-) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index 9c1294312..c4290d82b 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -1380,7 +1380,7 @@ def add_post_mission_systems(self, include_landing=True): promotes_inputs=[('rhs:mass', Mission.Summary.GROSS_MASS)]) eq.add_eq_output('mass', eq_units='lbm', normalize=False, - ref=10000., add_constraint=True) + ref=100000., add_constraint=True) self.model.connect( f'traj.{first_flight_phase_name}.states:mass', f'link_{first_flight_phase_name}_mass.lhs:mass', @@ -2031,6 +2031,19 @@ def setup(self, **kwargs): super().setup(**kwargs) def set_initial_guesses(self, parent_prob=None, parent_prefix=""): + """ + Call `set_val` on the trajectory for states and controls to seed + the problem with reasonable initial guesses. This is especially + important for collocation methods. + This method first identifies all phases in the trajectory then + loops over each phase. Specific initial guesses + are added depending on the phase and mission method. Cruise is treated + as a special phase for GASP-based missions because it is an AnalyticPhase + in Dymos. For this phase, we handle the initial guesses first separately + and continue to the next phase after that. For other phases, we set the initial + guesses for states and controls according to the information available + in the 'initial_guesses' attribute of the phase. + """ setvalprob = self if parent_prob is not None and parent_prefix != "": setvalprob = parent_prob @@ -2092,6 +2105,28 @@ def set_initial_guesses(self, parent_prob=None, parent_prefix=""): self._add_guesses(phase_name, phase, guesses, setvalprob, parent_prefix) def _process_guess_var(self, val, key, phase): + """ + Process the guess variable, which can either be a float or an array of floats. + This method is responsible for interpolating initial guesses when the user + provides a list or array of values rather than a single float. It interpolates + the guess values across the phase's domain for a given variable, be it a control + or a state variable. The interpolation is performed between -1 and 1 (representing + the normalized phase time domain), using the numpy linspace function. + The result of this method is a single value or an array of interpolated values + that can be used to seed the optimization problem with initial guesses. + Parameters + ---------- + val : float or list/array of floats + The initial guess value(s) for a particular variable. + key : str + The key identifying the variable for which the initial guess is provided. + phase : Phase + The phase for which the variable is being set. + Returns + ------- + val : float or array of floats + The processed guess value(s) to be used in the optimization problem. + """ # Check if val is not a single float if not isinstance(val, float): # If val is an array of values @@ -2118,6 +2153,21 @@ def _process_guess_var(self, val, key, phase): return val def _add_subsystem_guesses(self, phase_name, phase, setvalprob, parent_prefix): + """ + Adds the initial guesses for each subsystem of a given phase to the problem. + This method first fetches all subsystems associated with the given phase. + It then loops over each subsystem and fetches its initial guesses. For each + guess, it identifies whether the guess corresponds to a state or a control + variable and then processes the guess variable. After this, the initial + guess is set in the problem using the `set_val` method. + Parameters + ---------- + phase_name : str + The name of the phase for which the subsystem guesses are being added. + phase : Phase + The phase object for which the subsystem guesses are being added. + """ + # Get all subsystems associated with the phase all_subsystems = self._get_all_subsystems( self.phase_info[phase_name]['external_subsystems']) @@ -2144,6 +2194,23 @@ def _add_subsystem_guesses(self, phase_name, phase, setvalprob, parent_prefix): parent_prefix+f'traj.{phase_name}.{path_string}:{key}', **val) def _add_guesses(self, phase_name, phase, guesses, setvalprob, parent_prefix): + """ + Adds the initial guesses for each variable of a given phase to the problem. + This method sets the initial guesses for time, control, state, and problem-specific + variables for a given phase. If using the GASP model, it also handles some special + cases that are not covered in the `phase_info` object. These include initial guesses + for mass, time, and distance, which are determined based on the phase name and other + mission-related variables. + Parameters + ---------- + phase_name : str + The name of the phase for which the guesses are being added. + phase : Phase + The phase object for which the guesses are being added. + guesses : dict + A dictionary containing the initial guesses for the phase. + """ + # If using the GASP model, set initial guesses for the rotation mass and flight duration if self.mission_method is TWO_DEGREES_OF_FREEDOM: rotation_mass = self.initialization_guesses['rotation_mass'] From 83b31370e78899292605863dea4373f39781482d Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Fri, 11 Oct 2024 09:38:49 -0400 Subject: [PATCH 091/113] language and comments changes --- .../run_multimission_example_large_single_aisle.py | 10 +++++++++- aviary/interface/methods_for_level2.py | 4 ++-- 2 files changed, 11 insertions(+), 3 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py index 5cc253dbb..7aa845820 100644 --- a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py @@ -2,6 +2,13 @@ authors: Jatin Soni, Eliot Aretskin Multi Mission Optimization Example using Aviary +In this example, Two seperate aviary problems are instantiated using the typical aviaryProblem calls like load_inputs, +check_and_preprocess_payload, etc.. Once those problems are setup and all of their phases are linked together, +we copy those problems as group into a super_problem. We then promote GROSS_MASS, RANGE, SPAN, and wing AREA from each +of those sub-groups (group1 and group2) up to the super_probem so the optimizer can control them. The fuel_burn results +from each of the group1 and group2 dymos missions are summed and weighted to create the objective function the +optimizer sees. + For the deadhead mission: aircraft:crew_and_payload:num_passengers,0,unitless aircraft:crew_and_payload:num_tourist_class,0,unitless @@ -319,5 +326,6 @@ def createN2(fileref, prob): super_prob = large_single_aisle_example(makeN2=makeN2) + # Uncomment the following lines to see further details on each mission. # super_prob.model.group_1.list_vars(val=True, units=True, print_arrays=False) - # https://openmdao.org/newdocs/versions/latest/features/debugging/listing_variables.html?highlight=list_driver_vars + # super_prob.model.group_2.list_vars(val=True, units=True, print_arrays=False) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index e99db361a..5d17e4518 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -2183,7 +2183,7 @@ def _add_subsystem_guesses(self, phase_name, phase, setvalprob, parent_prefix): parent_prefix+f'traj.{phase_name}.{path_string}:{key}', **val) def _add_guesses(self, phase_name, phase, guesses, setvalprob, parent_prefix): - """ + """ Adds the initial guesses for each variable of a given phase to the problem. This method sets the initial guesses for time, control, state, and problem-specific variables for a given phase. If using the GASP model, it also handles some special @@ -2199,7 +2199,7 @@ def _add_guesses(self, phase_name, phase, guesses, setvalprob, parent_prefix): guesses : dict A dictionary containing the initial guesses for the phase. """ - + # If using the GASP model, set initial guesses for the rotation mass and flight duration if self.mission_method is TWO_DEGREES_OF_FREEDOM: rotation_mass = self.initialization_guesses['rotation_mass'] From c32b57b30528d6ba357658493a72a940185752e8 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Fri, 11 Oct 2024 09:47:31 -0400 Subject: [PATCH 092/113] removed unneeded print statement --- .../run_multimission_example_large_single_aisle.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py index 7aa845820..0b3539a0b 100644 --- a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py @@ -30,7 +30,7 @@ from aviary.subsystems.mass.flops_based.furnishings import TransportFurnishingsGroupMass from aviary.api import SubsystemBuilderBase from aviary.validation_cases.validation_tests import get_flops_inputs -print("========== Starting Run ===============") + # fly the same mission twice with two different passenger loads phase_info_primary = copy.deepcopy(phase_info) phase_info_deadhead = copy.deepcopy(phase_info) From 92080a9971151acd49ea2966273bc244f0fd76db Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Fri, 11 Oct 2024 10:00:09 -0400 Subject: [PATCH 093/113] comments changes --- aviary/interface/methods_for_level2.py | 1 - 1 file changed, 1 deletion(-) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index 5d17e4518..ac7ed46c7 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -2199,7 +2199,6 @@ def _add_guesses(self, phase_name, phase, guesses, setvalprob, parent_prefix): guesses : dict A dictionary containing the initial guesses for the phase. """ - # If using the GASP model, set initial guesses for the rotation mass and flight duration if self.mission_method is TWO_DEGREES_OF_FREEDOM: rotation_mass = self.initialization_guesses['rotation_mass'] From cb880066748fe022ca9690e1250cf3d4026e9d2c Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Fri, 11 Oct 2024 12:57:55 -0400 Subject: [PATCH 094/113] reverted two files related to battery that should not have been changed, removed unneeded comments --- aviary/subsystems/energy/battery_builder.py | 49 +++++-------------- .../test_battery_in_a_mission.py | 26 ++-------- aviary/variable_info/variable_meta_data.py | 3 -- 3 files changed, 16 insertions(+), 62 deletions(-) diff --git a/aviary/subsystems/energy/battery_builder.py b/aviary/subsystems/energy/battery_builder.py index 03583ea77..173c28a88 100644 --- a/aviary/subsystems/energy/battery_builder.py +++ b/aviary/subsystems/energy/battery_builder.py @@ -58,48 +58,23 @@ def build_mission(self, num_nodes, aviary_inputs=None) -> om.Group: return battery_group def get_states(self): - # need to add subsystem name to target name ('battery.') for state due - # to issue where non aircraft or mission variables are not fully promoted - # TODO fix this by not promoting only 'aircraft:*' and 'mission:*' - state_dict = { - Dynamic.Mission.CUMULATIVE_ELECTRIC_ENERGY_USED: { - 'fix_initial': True, - 'fix_final': False, - 'lower': 0.0, - 'ref': 1e4, - 'defect_ref': 1e6, - 'units': 'kJ', - 'rate_source': Dynamic.Mission.ELECTRIC_POWER_IN_TOTAL, - 'input_initial': 0.0, - 'targets': f'{self.name}.{Dynamic.Mission.CUMULATIVE_ELECTRIC_ENERGY_USED}', - } - } + state_dict = {Dynamic.Mission.CUMULATIVE_ELECTRIC_ENERGY_USED: {'fix_initial': True, + 'fix_final': False, + 'lower': 0.0, + 'ref': 1e4, + 'defect_ref': 1e6, + 'units': 'kJ', + 'rate_source': Dynamic.Mission.ELECTRIC_POWER_IN_TOTAL, + 'input_initial': 0.0}} return state_dict def get_constraints(self): constraint_dict = { # Can add constraints here; state of charge is a common one in many battery applications - f'{self.name}.{Dynamic.Mission.BATTERY_STATE_OF_CHARGE}': { - 'type': 'boundary', - 'loc': 'final', - 'lower': 0.2, - }, + f'battery.{Dynamic.Mission.BATTERY_STATE_OF_CHARGE}': + {'type': 'boundary', + 'loc': 'final', + 'lower': 0.2}, } return constraint_dict - - def get_parameters(self, aviary_inputs=None, phase_info=None): - params = { - Aircraft.Battery.ENERGY_CAPACITY: { - 'val': 0.0, - 'units': 'kJ', - 'static_target': True, - }, - Aircraft.Battery.EFFICIENCY: { - 'val': 0.0, - 'units': 'unitless', - 'static_target': True, - }, - } - - return params diff --git a/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py b/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py index 756932e0d..ce3552174 100644 --- a/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py +++ b/aviary/validation_cases/benchmark_tests/test_battery_in_a_mission.py @@ -41,13 +41,13 @@ def setUp(self): "constrain_final": False, "fix_duration": False, "initial_bounds": ((0.0, 0.0), "min"), - "duration_bounds": ((10.0, 30.0), "min"), + "duration_bounds": ((10., 30.), "min"), }, }, 'post_mission': { 'include_landing': False, 'external_subsystems': [], - }, + } } def test_subsystems_in_a_mission(self): @@ -56,8 +56,7 @@ def test_subsystems_in_a_mission(self): prob = av.AviaryProblem() prob.load_inputs( - "models/test_aircraft/aircraft_for_bench_FwFm_with_electric.csv", phase_info - ) + "models/test_aircraft/aircraft_for_bench_FwFm_with_electric.csv", phase_info) # Preprocess inputs prob.check_and_preprocess_inputs() @@ -84,33 +83,16 @@ def test_subsystems_in_a_mission(self): prob.set_val(av.Aircraft.Battery.PACK_ENERGY_DENSITY, 550, units='kJ/kg') prob.set_val(av.Aircraft.Battery.PACK_MASS, 1000, units='lbm') prob.set_val(av.Aircraft.Battery.ADDITIONAL_MASS, 115, units='lbm') - prob.set_val(av.Aircraft.Battery.EFFICIENCY, 0.95, units='unitless') prob.run_aviary_problem() electric_energy_used = prob.get_val( - f'traj.cruise.timeseries.' + - f'{av.Dynamic.Mission.CUMULATIVE_ELECTRIC_ENERGY_USED}', - units='kW*h', - ) + f'traj.cruise.timeseries.{av.Dynamic.Mission.CUMULATIVE_ELECTRIC_ENERGY_USED}', units='kW*h') fuel_burned = prob.get_val(av.Mission.Summary.FUEL_BURNED, units='lbm') - soc = prob.get_val( - 'traj.cruise.rhs_all.battery.battery_state_of_charge', units='unitless' - ) # Check outputs - # indirectly check mission trajectory by checking total fuel/electric split assert_near_equal(electric_energy_used[-1], 38.60538132, 1.e-7) assert_near_equal(fuel_burned, 676.87235486, 1.e-7) - # check battery state-of-charge over mission - assert_near_equal( - soc, - [0.99999578, 0.97551324, 0.94173584, 0.93104625, 0.93104625, - 0.8810605, 0.81210498, 0.79028433, 0.79028433, 0.73088701, - 0.64895148, 0.62302415, 0.62302415, 0.57309323, 0.50421334, - 0.48241661, 0.48241661, 0.45797918, 0.42426402, 0.41359413], - 1e-7, - ) if __name__ == "__main__": diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index 4d99c69db..e8fdd205e 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -616,9 +616,6 @@ # |___/ # ====================================================================================== -# TODO: Set initial defaults better -# from aviary.utils.aviary_values import AviaryValues - add_meta_data( Aircraft.CrewPayload.BAGGAGE_MASS, meta_data=_MetaData, From 3c29bbe1e2fd0b09757e64a7a28ea6f381ad6adc Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Tue, 15 Oct 2024 15:07:26 -0400 Subject: [PATCH 095/113] first cut at docs and examples for multi-mission --- aviary/docs/examples/images/multi_mission.png | Bin 0 -> 1224707 bytes aviary/docs/examples/multi-missions.ipynb | 147 ++++++++++++++++++ aviary/docs/user_guide/multi-mission.ipynb | 81 ++++++++++ ...multimission_example_large_single_aisle.py | 4 +- 4 files changed, 230 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z@}o5O&#&-P&i=on%0IvV|G)faF1SDa{|WhjF(KdlTT&JKM4svN5Z^}DHqgr6edyx< E0ek=C#sB~S literal 0 HcmV?d00001 diff --git a/aviary/docs/examples/multi-missions.ipynb b/aviary/docs/examples/multi-missions.ipynb new file mode 100644 index 000000000..ebc83354f --- /dev/null +++ b/aviary/docs/examples/multi-missions.ipynb @@ -0,0 +1,147 @@ +{ + "cells": [ + { + "cell_type": "code", + "execution_count": null, + "metadata": { + "tags": [ + "remove-cell" + ] + }, + "outputs": [], + "source": [ + "# Testing Cell\n", + "from aviary.docs.tests.utils import glue_variable\n", + "from aviary.api import Aircraft, Mission, AviaryProblem\n", + "from aviary.examples.multi_missions import run_multimission_example_large_single_aisle\n", + "\n", + "glue_variable('Design.RANGE',f'{Mission.Design.RANGE=}'.split('=')[0], md_code=True)\n", + "glue_variable('Design.NUM_PASSENGERS', f'{Aircraft.CrewPayload.Design.NUM_PASSENGERS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.CrewPayload.NUM_PASSENGERS=}'.split('=')[0], md_code=True)\n", + "\n", + "glue_variable('capi',AviaryProblem.check_and_preprocess_inputs.__name__+'()',md_code=True)\n", + "glue_variable(Aircraft.CrewPayload.NUM_BUSINESS_CLASS.split(':')[-1])\n", + "\n" + ] + }, + { + "cell_type": "markdown", + "metadata": {}, + "source": [ + "# Multi-Mission Example\n", + "\n", + "The [Multi-mission Example](\n", + "https://github.com/OpenMDAO/Aviary/tree/main/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py) demonstrates the capability to optimize an aircraft design considering two missions that the aircraft will perform. For a background on this example see [Multi-Mission Overview](../user_guide/multi-mission).\n", + "\n", + "## Implementation\n", + "The user must supply the following inputs for a multi-mission:\n", + "* 2 aircraft configuration examples (i.e. .csv files)\n", + "* 2 `phase_info` describing the different aircraft missions\n", + "* a weighting of the relative importance of each mission\n", + "* {glue:md}`Design.RANGE`\n", + "* {glue:md}`Design.NUM_PASSENGERS`\n", + "* `LANDING_TO_TAKEOFF_MASS_RATIO` or `Summary.CRUISE_MACH`\n", + "\n", + "### Aircraft Configuration\n", + "In the example, we import a single aircraft configuration (LargeSingleAisle2FLOPS) and then modify it to create a primary mission which carries 162 passengers and a deadhead mission. The deadhead mission is a mission without passengers, but it still has the same number of seats in the aircraft, even though those seats are empty. The number of seats for passenters in the aircraft, as well as some other systems like passenger airconditioning mass, is set by `Aircraft.CrewPayload.Design` values of {glue:md}`Design.NUM_PASSENGERS`, `num_tourist_class`, `num_business_class`, and `num_first_class`. Whereas the actual number of passengers on the flight is specified by those same variables but in `Aircraft.CrewPayload` i.e. `AircraftCrewPayload.NUM_PASSENGERS`. \n", + "\n", + "### Phase Info\n", + "The same mission distance and profile (takeoff, climb, cruise, descent, landing) is being flown for both missions. To enable this, a single phase_info is imported and then copied. The user could modify the deadhead mission to be different from the primary mission by changing the target_range of the deadhead mission to a different value. \n", + "I.E. `phase_info_deadhead['post_mission']['target_range'] = [1500, \"nmi\"]` \n", + "\n", + "### Weighting\n", + "The `weights` input value describes the relative importance or frequence of one mission over the other. In the example, the the weigting is [9,1] indicating that for every nine times the aircraft flies a full passenger load, it flies a single deadhead leg. These weightings are based on user input and are converted into fractions. This weighting can be estimated from examining historical passenger loads on a typical aircraf route of interest. The objective function is based on combining the fuel-burn values from both missions and multiplying that by the weights. Other objectives, like max range, have not been tested yet.\n", + "\n", + "### Setting Values\n", + "The {glue:md}`Mission.Design.RANGE` value must be set to size some of Aviary's subsystems. These subsystems, such as avionics, have increasing mass as {glue:md}`Mission.Design.RANGE` increases. These are first order approximations that come with aviary. But because of these, we must ensure that both pre-missions have the same {glue:md}`Mission.Design.RANGE`, even if the actual range flown buy each mission (target_rage) is different. Without this, the avoinics mass calculated in pre-mission would be different for the two missions, resulting in a different aircraft design, which is counter to what is intended with the multi-mission feature. \n", + "\n", + "The total number of passengers (`Aircraft.CrewPayload.Design.NUM_PASENGERS`) and the design number of passengers of each type (business, tourist, first class), help to define the passenger air conditioning subsystems and the passenger support mass (seats) respectively. Thus when these values are set equal in the primary and deadhead missions, we ensure the aircraft will be designed similarly. \n", + "\n", + "It is good practice, but not required, to set `LANDING_TO_TAKEOFF_MASS_RATIO` in Aviary Values to ensure consistent design of the landing gear for both missions. This combined with Design.GROSS_MASS helps to ensure that `MAIN_GEAR_MASS` and `NOSE_GEAR_MASSES` are the same for both missions. If `LANDING_TO_TAKEOFF_MASS_RATIO` is not set, it will be caluclated based on `Summary.CRUISE_MACH` and {glue:md}`Mission.Design.RANGE`. This is potentially problematic because `Summary.CRUISE_MACH` may not be set, and instead cruse mach may be optimized. In that case, `Summary.CRUISE_MACH` could vary between the Primary and Deadhead missions, which would then cascade into differeing `MAIN_GEAR_MASS` which causes the aircraft designs to diverge.\n", + "\n", + "## Theory\n", + "Each of the two missions in the example are instantiated as aviary problems, so there are two pre-missions, two missions run in parallel. Two get the pre-missions to have the same aircraft design, `Mission.Design.GROSS_MASS`, {glue:md}`Mission.Design.RANGE`, `Aircraft.Wing.SPAN`, and `Aircraft.Wing.AREA`, are promoted out of the pre-missions to a single values. This ensures that the aircrafts in both pre-missions have the same design even though their passenger count and fuel mass are different. There is no post-mission for the example, but if one was required for calculating cost or acoustic constraints, there would need to be two post-mission systems as well.\n", + "\n", + "To impact the structure of aviary problems as little as possible, after instantiation of the pre-mission, mission, and post-mission systems, the connections between those systems are created. Then those groups are then copied over into a regular openmdao problem called `super_prob`. This enables the use all the basic aviary connection and checking functions with minimal modification. \n", + "\n", + "Initialization of states and variables is conducted last through `prob.set_initial_guesses()`. This has to be completed after the aviary groups are added to `super_prob`. Setting initial guesses and then copying over a group into `super_prob` will not work in this case because initial guesses is set on the problem, not the group. \n", + "\n", + "Some custom graphing and print functions were added to this example because the basic aviary graphing programs have not yet been modified to handle two database file from two separate missions. The user can see detailed info of each mission result using the `super_prob.model.group_1.list_vars()` commands listed in the comments at the bottom of the example.\n", + "\n", + "## Best Pratices\n", + "The user should be cognizant of the implications of having two pre-mission systems, one for each mission. Both of the pre-mission systems should be nearly identical in setup, save fuel-mass, passenger, and payload calculations. There are numerous opportunities for the user to get this wrong, and accidentally create two different aircraft as a result. For example, in a previous iteration of this example, `LANDING_TO_TAKEOFF_MASS_RATIO` was not specified, which resulted in two different landing gears being designed, one for the Primary mission, one for the Deadhead mission.\n", + "\n", + "If you are having trouble getting your `Aircraft.Design.EMPTY_MASS` (the final drymass mass summation from pre-mission) to be equal for both pre-missions, use the following OpenMDAO commends at the end of the example to list out and compare the mass from each subsystem.\n", + "\n", + "```\n", + "super_prob.model.group_1.list_vars(val=True, units=True, print_arrays=False)\n", + "super_prob.model.group_2.list_vars(val=True, units=True, print_arrays=False)\n", + "```\n" + ] + }, + { + "cell_type": "markdown", + "metadata": {}, + "source": [ + "## Results\n", + "The results of the [Multi-mission Example](\n", + "https://github.com/OpenMDAO/Aviary/tree/main/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py) are included in the data table and plots below.\n", + "\n", + "From the table results we can see that the Primary mission have the same `Design.EMPTY_MASS` and `Design.GROSS_MASS`. However, the `Summary.GROSS_MASS` varies as expected because these represent \"as-flown\" values. The Primary mission has the higher `Summary.GROSS_MASS` which corresponds to the full passenger load and bags. Consequently, the `Summary.FUEL_BURNED` for each mission is different, higher for the Primary mission, as expected because this mission is carrying more mass for the same mission. `Design.FUEL_MASS` is automatically calculated, it is higher for the Deadhead mission, indicating that the aircraft could hold more fuel, however, that fuel is not needed for the mission. `Wing.SPAN` and `Wing.AERA` are the same for both missions, indicating that the aircraft has been designed similarly in both cases. We do not want to see different values for the wing design because it would mean that the two pre-mission systems are not mirroring eachother. If they were not the same it would mean we are designing two different aircraft. \n", + "\n", + "The Landing_gear masses were also displayed because they are sensitive to `LANDING_TO_TAKEOFF_MASS_RATIO` and `Summary.CRUISE_MACH`, which the user may or may not have specified in Aviary_values. We expect these landing gear masses to be the same and they are which is good news for us and indicates that both pre-mission designs are mirroring eachother.\n", + "\n", + "Lastly the `Furnishings.MASS` and `CREW_AND_PAYLOAD.PASSENGER_SERVICE_MASS` are displayed. These values represent the weight of the seats and the air conditioning system for the passengers. They are both the same which is what we expect to see.\n", + "\n", + "A summary colum called 'Expectations' is included as a summary of what we want to see when evaluating this data. \n", + "\n", + "| Variable | Primary | Deadhead | Expectations |\n", + "|:-------------------------------------------------|:-----------------------------:|:--------------------:|---:|\n", + "|MISSION.DESIGN.GROSS_MASS | 174200.00 (lbm) | 174200.00 (lbm) | Equal |\n", + "|AIRCRAFT.DESIGN.EMPTY_MASS | 88183.64 (lbm) | 88183.64 (lbm) | Equal |\n", + "|MISSION.SUMMARY.GROSS_MASS | 158666.39 (lbm) | 152894.30 (lbm) | Different |\n", + "|MISSION.SUMMARY.FUEL_BURNED | 27508.15 (lbm) | 26679.17 (lbm) | Different |\n", + "|MISSION.DESIGN.FUEL_MASS | 43041.75 (lbm) | 47984.87 (lbm) | Different |\n", + "|MISSION.SUMMARY.TOTAL_FUEL_MASS | 27508.15 (lbm) | 26679.17 (lbm) | Different |\n", + "|AIRCRAFT.WING.SPAN | 112.58 (ft) | 112.58 (ft) | Equal |\n", + "|AIRCRAFT.WING.AREA | 1340.98 (ft**2) | 1340.98(ft**2) | Equal |\n", + "|AIRCRAFT.LANDING_GEAR.MAIN_GEAR_MASS | 6348.73 (lbm) | 6348.73 (lbm) | Equal |\n", + "|AIRCRAFT.LANDING_GEAR.NOSE_GEAR_MASS | 799.54 (lbm) | 799.54 (lbm) | Equal |\n", + "|AIRCRAFT.DESIGN.LANDING_TO_TAKEOFF_MASS_RATIO | 0.84 (unitless) | 0.84 (unitless) | Equal |\n", + "|MISSION.SUMMARY.CRUISE_MACH | 0.785 (unitless) | 0.785 (unitless) | Equal |\n", + "|AIRCRAFT.FURNISHINGS.MASS | 14690.34 (lbm) | 14690.34 (lbm) | Equal |\n", + "|AIRCRAFT.CREW_AND_PAYLOAD.PASSENGER_SERVICE_MASS | 2524.48 (lbm) | 2524.48 (lbm) | Equal |\n", + "\n", + "In the graph below The Altitude, Drag force, Throttle command, Mass, Distance, and Mach number of the Primary and Deadhead missions are displayed. The Deadhead mission shows a characteristic smaller mass throughout the flight as expected since we have fewer passengers, and a slightly lower throttle profile to match, indicating the engine is not being pushed as hard to meet the demands of a lighter plane. Otherwise the missions themselves match, showing Mach, Distance, and Altitude all identical for every part of the mission. We did not allow the mach or altitude to be optimized for this mission so these results are not surprising. \n", + "\n", + "![Results](images/multi_mission.png \"Primary vs. Deadhead mission results\")" + ] + }, + { + "cell_type": "markdown", + "metadata": {}, + "source": [] + } + ], + "metadata": { + "kernelspec": { + "display_name": "latest_env", + "language": "python", + "name": "python3" + }, + "language_info": { + "codemirror_mode": { + "name": "ipython", + "version": 3 + }, + "file_extension": ".py", + "mimetype": "text/x-python", + "name": "python", + "nbconvert_exporter": "python", + "pygments_lexer": "ipython3", + "version": "3.10.13" + } + }, + "nbformat": 4, + "nbformat_minor": 2 +} diff --git a/aviary/docs/user_guide/multi-mission.ipynb b/aviary/docs/user_guide/multi-mission.ipynb new file mode 100644 index 000000000..ebb649b0e --- /dev/null +++ b/aviary/docs/user_guide/multi-mission.ipynb @@ -0,0 +1,81 @@ +{ + "cells": [ + { + "cell_type": "code", + "execution_count": null, + "metadata": { + "tags": [ + "remove-cell" + ] + }, + "outputs": [ + { + "ename": "", + "evalue": "", + "output_type": "error", + "traceback": [ + "\u001b[1;31mRunning cells with 'base (Python 3.12.5)' requires the ipykernel package.\n", + "\u001b[1;31mRun the following command to install 'ipykernel' into the Python environment. \n", + "\u001b[1;31mCommand: 'conda install -n base ipykernel --update-deps --force-reinstall'" + ] + } + ], + "source": [ + "# Testing Cell\n", + "\n", + "from aviary.docs.tests.utils import glue_variable\n", + "from aviary.api import Aircraft, AviaryProblem\n", + "\n", + "glue_variable(f'{Aircraft.CrewPayload.Design.NUM_PASSENGERS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.CrewPayload.NUM_PASSENGERS=}'.split('=')[0], md_code=True)\n", + "\n", + "glue_variable('capi',AviaryProblem.check_and_preprocess_inputs.__name__+'()',md_code=True)\n", + "glue_variable(Aircraft.CrewPayload.NUM_BUSINESS_CLASS.split(':')[-1])\n" + ] + }, + { + "cell_type": "markdown", + "metadata": {}, + "source": [ + "# Multi-Mission Optimization\n", + "\n", + "## Overview\n", + "\n", + "Multi-missions adds the capability to optimize an aircraft design considering two or more missions that the aircraft will perform. This is in contrast to designing an aircraft for a single mission, and hopefully helps to represent the conditions the aircraft will be flying in better. In the example provided, a large single aisle passenger aircraft is designed based on a mission with every seat filled, and a second 'deadhead' mission where there are no passengers. A weighting is provided by the user to determine how often the missions are full of passengers vs. how often the flights are empty. A cargo example could be constructed where one mission is designed for maximum range and a second mission designed for maximum payload. \n", + "\n", + "To impact the structure of aviaryproblems as little as possible, after instantiation of the pre-mission, mission, and post-mission systems, the connections between those systems are created. Then those groups are then copied over into a regular openmdao problem. This enables the use all the basic aviary connection and checking functions with minimal modification. \n", + "\n", + "The objective function is based on combining the fuel-burn values from both missions and the optimizers objective is to minimize the weighted fuel-burn. Other objectives, like max range, have not been tested yet.\n", + "\n", + "## Design vs. As-Flown\n", + "To support the need to design an aircraft with a certain number of seats, but then possibly fly missions with unfilled seats, a distinction in the metadata was introduced between {glue:md}`Aircraft.CrewPayload.Design.NUM_PASSENGERS` and {glue:md}`Aircraft.CrewPayload.NUM_PASSENGERS`. The individual passenger classes (num_first_class, {glue:md}`num_buisness_class`, num_tourist_class) also have these distinctions. The Design values represent how many seats are available in the aircraft. Whereas the non-design values represent an as-flow value of how many passengers are on a particular flight. \n", + "\n", + "A number of checks exist in {glue:md}`capi` to help the user in the case that incomplete as-flow or design passenger information is provided. This was done to provide backward compatability for older aircraft models.\n", + "\n", + "## Example\n", + "An example of a multi-mission as well as Setup, Theory, and Results, is presented in [Multi-Mission Examples](../examples/multi-mission)." + ] + } + ], + "metadata": { + "kernelspec": { + "display_name": "base", + "language": "python", + "name": "python3" + }, + "language_info": { + "codemirror_mode": { + "name": "ipython", + "version": 3 + }, + "file_extension": ".py", + "mimetype": "text/x-python", + "name": "python", + "nbconvert_exporter": "python", + "pygments_lexer": "ipython3", + "version": "3.12.5" + } + }, + "nbformat": 4, + "nbformat_minor": 2 +} diff --git a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py index 0b3539a0b..98515f70e 100644 --- a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py @@ -57,7 +57,7 @@ 'aircraft:crew_and_payload:num_first_class', 0, 'unitless') aviary_inputs_deadhead.set_val(Aircraft.CrewPayload.MISC_CARGO, 0.0, 'lbm') - +# Use this to change the target range of the deadhead mission # phase_info_deadhead['post_mission']['target_range'] = [1500, "nmi"] @@ -326,6 +326,6 @@ def createN2(fileref, prob): super_prob = large_single_aisle_example(makeN2=makeN2) - # Uncomment the following lines to see further details on each mission. + # Uncomment the following lines to see mass breakdown details for each mission. # super_prob.model.group_1.list_vars(val=True, units=True, print_arrays=False) # super_prob.model.group_2.list_vars(val=True, units=True, print_arrays=False) From f89276ec19eb04bdd9eb4f2308c89d08aee79db8 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Thu, 17 Oct 2024 11:33:28 -0400 Subject: [PATCH 096/113] added ProblemType.MULTI_MISSION, and modified multi-mission problem to have 1 passenger --- ...multimission_example_large_single_aisle.py | 21 +++-------- aviary/interface/methods_for_level2.py | 36 +++++++++++++++++++ aviary/variable_info/enums.py | 8 +++++ 3 files changed, 48 insertions(+), 17 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py index 98515f70e..19f069add 100644 --- a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py @@ -34,31 +34,18 @@ # fly the same mission twice with two different passenger loads phase_info_primary = copy.deepcopy(phase_info) phase_info_deadhead = copy.deepcopy(phase_info) -# phase_info_deadhead['post_mission']['target_range'] = [500, "nmi"] - # get large single aisle values aviary_inputs_primary = get_flops_inputs('LargeSingleAisle2FLOPS') -aviary_inputs_primary.set_val( - Aircraft.CrewPayload.Design.NUM_PASSENGERS, 162, 'unitless') -aviary_inputs_primary.set_val( - 'aircraft:crew_and_payload:design:num_tourist_class', 150, 'unitless') -aviary_inputs_primary.set_val( - 'aircraft:crew_and_payload:design:num_business_class', 0, 'unitless') -aviary_inputs_primary.set_val( - 'aircraft:crew_and_payload:design:num_first_class', 12, 'unitless') +aviary_inputs_primary.set_val(Mission.Design.GROSS_MASS, val=100000, units='lbm') aviary_inputs_deadhead = copy.deepcopy(aviary_inputs_primary) -aviary_inputs_deadhead.set_val('aircraft:crew_and_payload:num_passengers', 0, 'unitless') +aviary_inputs_deadhead.set_val('aircraft:crew_and_payload:num_passengers', 1, 'unitless') aviary_inputs_deadhead.set_val( - 'aircraft:crew_and_payload:num_tourist_class', 0, 'unitless') + 'aircraft:crew_and_payload:num_tourist_class', 1, 'unitless') aviary_inputs_deadhead.set_val( 'aircraft:crew_and_payload:num_business_class', 0, 'unitless') aviary_inputs_deadhead.set_val( 'aircraft:crew_and_payload:num_first_class', 0, 'unitless') -aviary_inputs_deadhead.set_val(Aircraft.CrewPayload.MISC_CARGO, 0.0, 'lbm') - -# Use this to change the target range of the deadhead mission -# phase_info_deadhead['post_mission']['target_range'] = [1500, "nmi"] class MultiMissionProblem(om.Problem): @@ -95,7 +82,7 @@ def __init__(self, aviary_values, phase_infos, weights): prob.link_phases() # alternate prevents use of equality constraint b/w design and summary gross mass - prob.problem_type = ProblemType.ALTERNATE + prob.problem_type = ProblemType.MULTI_MISSION prob.add_design_variables() self.probs.append(prob) # phase names for each traj (can be used later to make plots/print outputs) diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py index 4306a05cb..7613d612b 100644 --- a/aviary/interface/methods_for_level2.py +++ b/aviary/interface/methods_for_level2.py @@ -1863,6 +1863,42 @@ def add_design_variables(self): elif self.problem_type is ProblemType.FALLOUT: print('No design variables for Fallout missions') + elif self.problem_type is ProblemType.MULTI_MISSION: + self.model.add_design_var( + Mission.Summary.GROSS_MASS, + lower=10., + upper=900e3, + units='lbm', + ref=175e3, + ) + + self.model.add_constraint( + Mission.Constraints.RANGE_RESIDUAL, equals=0, ref=10 + ) + + # We must ensure that design.gross_mass is greater than mission.summary.gross_mass + # and this must hold true for each of the different missions that is flown + # the result will be the design.gross_mass should be equal to the mission.summary.gross_mass + # of the heaviest mission + self.model.add_subsystem( + "GROSS_MASS_constraint", + om.ExecComp( + "gross_mass_resid = design_mass - actual_mass", + design_mass={"val": 1, "units": "kg"}, + actual_mass={"val": 0, "units": "kg"}, + gross_mass_resid={"val": 30, "units": "kg"}, + ), + promotes_inputs=[ + ("design_mass", Mission.Design.GROSS_MASS), + ("actual_mass", Mission.Summary.GROSS_MASS), + ], + promotes_outputs=["gross_mass_resid"], + ) + + self.model.add_constraint( + "gross_mass_resid", lower=0 + ) + if self.mission_method is TWO_DEGREES_OF_FREEDOM and self.analysis_scheme is AnalysisScheme.COLLOCATION: # problem formulation to make the trajectory work self.model.add_design_var(Mission.Takeoff.ASCENT_T_INTIIAL, diff --git a/aviary/variable_info/enums.py b/aviary/variable_info/enums.py index e4583609f..75d7392b7 100644 --- a/aviary/variable_info/enums.py +++ b/aviary/variable_info/enums.py @@ -151,10 +151,18 @@ class ProblemType(Enum): weight and empty weight constant. Using the specified actual gross weight, it will then find the maximum distance the off-design aircraft can fly. + + MULTI_MISSION: Similar to a SIZING mission, however it varies the + design gross weight and actual gross weight across multiple missions + to and closes design range for each mission. This causes the empty + weight and the fuel weight to change. The final result will be a + single empty weight, for all the different missions, and multiple + values for fuel weight, unique to each mission. """ SIZING = 'sizing' ALTERNATE = 'alternate' FALLOUT = 'fallout' + MULTI_MISSION = 'multimission' class SpeedType(Enum): From 78a2320c7c91f43024aaa45decdf610b135e9816 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Tue, 29 Oct 2024 11:34:18 -0400 Subject: [PATCH 097/113] Correctly connected inputs to objectiv from group0 and group1. Changed to sweep a design variable. added SNOPT option. Faster convergance with SLSQP but SNOPT returns the same answer --- ...multimission_example_large_single_aisle.py | 30 +++++++++++++------ 1 file changed, 21 insertions(+), 9 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py index 19f069add..a18a6ba24 100644 --- a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py @@ -4,7 +4,7 @@ In this example, Two seperate aviary problems are instantiated using the typical aviaryProblem calls like load_inputs, check_and_preprocess_payload, etc.. Once those problems are setup and all of their phases are linked together, -we copy those problems as group into a super_problem. We then promote GROSS_MASS, RANGE, SPAN, and wing AREA from each +we copy those problems as group into a super_problem. We then promote GROSS_MASS, RANGE, and wing SWEEP from each of those sub-groups (group1 and group2) up to the super_probem so the optimizer can control them. The fuel_burn results from each of the group1 and group2 dymos missions are summed and weighted to create the objective function the optimizer sees. @@ -47,6 +47,8 @@ aviary_inputs_deadhead.set_val( 'aircraft:crew_and_payload:num_first_class', 0, 'unitless') +Optimizer = 'SLSQP' # SLSQP or SNOPT + class MultiMissionProblem(om.Problem): def __init__(self, aviary_values, phase_infos, weights): @@ -98,20 +100,27 @@ def __init__(self, aviary_values, phase_infos, weights): self.group_prefix + f'_{i}', prob.model, promotes_inputs=[Mission.Design.GROSS_MASS, Mission.Design.RANGE, - Aircraft.Wing.SPAN, - Aircraft.Wing.AREA], + Aircraft.Wing.SWEEP], promotes_outputs=[(Mission.Objectives.FUEL, promoted_name)]) def add_design_variables(self): self.model.add_design_var(Mission.Design.GROSS_MASS, lower=10., upper=900e3, units='lbm') - self.model.add_design_var(Aircraft.Wing.SPAN, lower=100., upper=500., units='ft') - self.model.add_design_var(Aircraft.Wing.AREA, lower=10., - upper=1e6, units='ft**2') + self.model.add_design_var(Aircraft.Wing.SWEEP, lower=20., upper=35., units='deg') def add_driver(self): self.driver = om.pyOptSparseDriver() - self.driver.options["optimizer"] = "SLSQP" + if Optimizer == "SLSQP": + self.driver.options["optimizer"] = "SLSQP" + elif Optimizer == "SNOPT": + self.driver.options["optimizer"] = "SNOPT" + self.driver.opt_settings["Major optimality tolerance"] = 1e-7 + self.driver.opt_settings["Major feasibility tolerance"] = 1e-7 + # self.driver.opt_settings["Major iterations"] = 0 + self.driver.opt_settings["iSumm"] = 6 + self.driver.opt_settings["iPrint"] = 9 + self.driver.opt_settings['Verify level'] = -1 + self.driver.opt_settings["Nonderivative linesearch"] = None self.driver.declare_coloring() # linear solver causes nan entry error for landing to takeoff mass ratio param # self.model.linear_solver = om.DirectSolver() @@ -128,7 +137,9 @@ def add_objective(self): # adding compound execComp to super problem self.model.add_subsystem('compound_fuel_burn_objective', om.ExecComp( - "compound = "+weighted_str, has_diag_partials=True), promotes=["compound"]) + "compound = "+weighted_str, has_diag_partials=True), + promotes_inputs=self.fuel_vars, + promotes_outputs=["compound"]) self.model.add_objective('compound') def setup_wrapper(self): @@ -291,7 +302,8 @@ def createN2(fileref, prob): (Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, 'unitless'), (Mission.Summary.CRUISE_MACH, 'unitless'), (Aircraft.Furnishings.MASS, 'lbm'), - (Aircraft.CrewPayload.PASSENGER_SERVICE_MASS, 'lbm')] + (Aircraft.CrewPayload.PASSENGER_SERVICE_MASS, 'lbm'), + (Aircraft.Wing.SWEEP, 'deg')] super_prob.print_vars(vars=printoutputs) plotvars = [('altitude', 'ft'), From a745cf5004befec097e510c9141dca7b9a5994a9 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Tue, 29 Oct 2024 14:27:22 -0400 Subject: [PATCH 098/113] completed changes from 1st round of reviews except for changing detection method of user input suggested by jason --- ...multimission_example_large_single_aisle.py | 2 +- aviary/utils/preprocessors.py | 25 ++++++++++++------- aviary/variable_info/variable_meta_data.py | 6 +++++ 3 files changed, 23 insertions(+), 10 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py index a18a6ba24..9a0c465e4 100644 --- a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py @@ -198,7 +198,7 @@ def create_timeseries_plots(self, plotvars=[], show=True): plt.xlabel("Time (s)") plt.ylabel(f"{var.title()} ({unit})") plt.grid() - plt.figlegend([f"Plane {i}" for i in range(self.num_missions)]) + plt.figlegend([f"Mission {i}" for i in range(self.num_missions)]) if show: plt.show() diff --git a/aviary/utils/preprocessors.py b/aviary/utils/preprocessors.py index 42e4f962d..0a10312ed 100644 --- a/aviary/utils/preprocessors.py +++ b/aviary/utils/preprocessors.py @@ -1,3 +1,4 @@ +from aviary.variable_info.enums import Verbosity import warnings import numpy as np @@ -66,11 +67,13 @@ def preprocess_crewpayload(aviary_options: AviaryValues): # or if it was set to it's default value of zero if passenger_count != 0 and aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) == 0: aviary_options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, passenger_count) - print("INFO: In preprocessor.py: User has specified supporting values for NUM_PASSENGERS but has left NUM_PASSENGERS=0. Replacing NUM_PASSENGERS with passenger_count.") + if Verbosity >= 2: + print("User has specified supporting values for NUM_PASSENGERS but has left NUM_PASSENGERS=0. Replacing NUM_PASSENGERS with passenger_count.") if design_passenger_count != 0 and aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) == 0: aviary_options.set_val( Aircraft.CrewPayload.Design.NUM_PASSENGERS, design_passenger_count) - print("INFO: In preprocessor.py: User has specified supporting values for Design.NUM_PASSENGERS but has left Design.NUM_PASSENGERS=0. Replacing Design.NUM_PASSENGERS with design_passenger_count.") + if Verbosity >= 2: + print("User has specified supporting values for Design.NUM_PASSENGERS but has left Design.NUM_PASSENGERS=0. Replacing Design.NUM_PASSENGERS with design_passenger_count.") num_pax = aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) design_num_pax = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) @@ -101,7 +104,9 @@ def preprocess_crewpayload(aviary_options: AviaryValues): # Copy data over if only one set of data exists # User has given detailed values for 1TB as flow and NO design values at all if passenger_count != 0 and design_num_pax == 0 and design_passenger_count == 0: - print("INFO: In preprocessor.py: User has not input design passengers data. Assuming design is equal to as-flow passenger data.") + if Verbosity >= 2: + print( + "User has not input design passengers data. Assuming design is equal to as-flow passenger data.") aviary_options.set_val( Aircraft.CrewPayload.Design.NUM_PASSENGERS, passenger_count) aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, @@ -112,10 +117,13 @@ def preprocess_crewpayload(aviary_options: AviaryValues): aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS)) # user has not supplied detailed information on design but has supplied summary information on passengers elif num_pax != 0 and design_num_pax == 0: - print("INFO: In preprocessor.py: User has specified as-flown NUM_PASSENGERS but not how many passengers the aircraft was designed for in Design.NUM_PASSENGERS. Assuming they are equal.") + if Verbosity >= 2: + print("User has specified as-flown NUM_PASSENGERS but not how many passengers the aircraft was designed for in Design.NUM_PASSENGERS. Assuming they are equal.") aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, num_pax) elif design_passenger_count != 0 and num_pax == 0 and passenger_count == 0: - print("INFO: In preprocessor.py: User has not input as-flown passengers data. Assuming as-flow is equal to design passenger data.") + if Verbosity >= 1: + print("User has not input as-flown passengers data. Assuming as-flow is equal to design passenger data.") + print("If you intended to have no passengers on this flight, please set Aircraft.CrewPayload.PASSENGER_PAYLOAD_MASS to zero in aviary_values.") aviary_options.set_val( Aircraft.CrewPayload.NUM_PASSENGERS, design_passenger_count) aviary_options.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, @@ -126,7 +134,9 @@ def preprocess_crewpayload(aviary_options: AviaryValues): aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS)) # user has not supplied detailed information on design but has supplied summary information on passengers elif design_num_pax != 0 and num_pax == 0: - print("INFO: In preprocessor.py: User has specified Design.NUM_PASSENGERS but not how many passengers are on the flight in NUM_PASSENGERS. Assuming they are equal.") + if Verbosity >= 1: + print("User has specified Design.NUM_PASSENGERS but not how many passengers are on the flight in NUM_PASSENGERS. Assuming they are equal.") + print("If you intended to have no passengers on this flight, please set Aircraft.CrewPayload.PASSENGER_PAYLOAD_MASS to zero in aviary_values.") aviary_options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, design_num_pax) # Performe checks on the final data tables to ensure Design is always large then As-Flow @@ -143,9 +153,6 @@ def preprocess_crewpayload(aviary_options: AviaryValues): raise om.AnalysisError( f"ERROR: In preprocesssors.py: NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS)}) is larger than the number of seats set by Design.NUM_PASSENGERS ({aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS)}) .") - # dnp = aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) - # print(f"INFO: In preprocessor.py: Aircraft has been designed for {dnp} passengers.") - if Aircraft.CrewPayload.NUM_FLIGHT_ATTENDANTS not in aviary_options: flight_attendants_count = 0 # assume no passengers diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index e8fdd205e..4830653e3 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -699,6 +699,12 @@ default_value=0.7, ) +# ___ _ +# | \ ___ ___ (_) __ _ _ _ +# | |) | / -_) (_-< | | / _` | | ' \ +# |___/ \___| /__/ |_| \__, | |_||_| +# ====================== |___/ ====== + add_meta_data( Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, meta_data=_MetaData, From 48b6a050477de803a5d8c27228f255c48d8d7943 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Tue, 29 Oct 2024 14:47:13 -0400 Subject: [PATCH 099/113] small tweak to verbosity code call --- aviary/utils/preprocessors.py | 20 ++++++++++---------- 1 file changed, 10 insertions(+), 10 deletions(-) diff --git a/aviary/utils/preprocessors.py b/aviary/utils/preprocessors.py index 0a10312ed..02c52353f 100644 --- a/aviary/utils/preprocessors.py +++ b/aviary/utils/preprocessors.py @@ -1,4 +1,3 @@ -from aviary.variable_info.enums import Verbosity import warnings import numpy as np @@ -7,9 +6,8 @@ from aviary.utils.aviary_values import AviaryValues from aviary.utils.named_values import get_keys from aviary.variable_info.variable_meta_data import _MetaData -from aviary.variable_info.variables import Aircraft, Mission +from aviary.variable_info.variables import Aircraft, Mission, Settings from aviary.utils.test_utils.variable_test import get_names_from_hierarchy -from aviary.variable_info.variable_meta_data import _MetaData as BaseMetaData def preprocess_options(aviary_options: AviaryValues, **kwargs): @@ -37,6 +35,8 @@ def preprocess_crewpayload(aviary_options: AviaryValues): returns the modified collection. """ + verbosity = aviary_options.get_val(Settings.VERBOSITY) + # Grab Default all values for num_pax and 1TB (1st class, Tourist Class, Business Class Passengers) to make # sure they are accessible so we don't have to run checks if they exist again for key in ( @@ -49,7 +49,7 @@ def preprocess_crewpayload(aviary_options: AviaryValues): Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS,): if key not in aviary_options: - aviary_options.set_val(key, BaseMetaData[key]['default_value']) + aviary_options.set_val(key, _MetaData[key]['default_value']) # Sum passenger Counts for later checks and assignments passenger_count = 0 @@ -67,12 +67,12 @@ def preprocess_crewpayload(aviary_options: AviaryValues): # or if it was set to it's default value of zero if passenger_count != 0 and aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) == 0: aviary_options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, passenger_count) - if Verbosity >= 2: + if verbosity >= 2: print("User has specified supporting values for NUM_PASSENGERS but has left NUM_PASSENGERS=0. Replacing NUM_PASSENGERS with passenger_count.") if design_passenger_count != 0 and aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS) == 0: aviary_options.set_val( Aircraft.CrewPayload.Design.NUM_PASSENGERS, design_passenger_count) - if Verbosity >= 2: + if verbosity >= 2: print("User has specified supporting values for Design.NUM_PASSENGERS but has left Design.NUM_PASSENGERS=0. Replacing Design.NUM_PASSENGERS with design_passenger_count.") num_pax = aviary_options.get_val(Aircraft.CrewPayload.NUM_PASSENGERS) @@ -104,7 +104,7 @@ def preprocess_crewpayload(aviary_options: AviaryValues): # Copy data over if only one set of data exists # User has given detailed values for 1TB as flow and NO design values at all if passenger_count != 0 and design_num_pax == 0 and design_passenger_count == 0: - if Verbosity >= 2: + if verbosity >= 2: print( "User has not input design passengers data. Assuming design is equal to as-flow passenger data.") aviary_options.set_val( @@ -117,11 +117,11 @@ def preprocess_crewpayload(aviary_options: AviaryValues): aviary_options.get_val(Aircraft.CrewPayload.NUM_TOURIST_CLASS)) # user has not supplied detailed information on design but has supplied summary information on passengers elif num_pax != 0 and design_num_pax == 0: - if Verbosity >= 2: + if verbosity >= 2: print("User has specified as-flown NUM_PASSENGERS but not how many passengers the aircraft was designed for in Design.NUM_PASSENGERS. Assuming they are equal.") aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, num_pax) elif design_passenger_count != 0 and num_pax == 0 and passenger_count == 0: - if Verbosity >= 1: + if verbosity >= 1: print("User has not input as-flown passengers data. Assuming as-flow is equal to design passenger data.") print("If you intended to have no passengers on this flight, please set Aircraft.CrewPayload.PASSENGER_PAYLOAD_MASS to zero in aviary_values.") aviary_options.set_val( @@ -134,7 +134,7 @@ def preprocess_crewpayload(aviary_options: AviaryValues): aviary_options.get_val(Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS)) # user has not supplied detailed information on design but has supplied summary information on passengers elif design_num_pax != 0 and num_pax == 0: - if Verbosity >= 1: + if verbosity >= 1: print("User has specified Design.NUM_PASSENGERS but not how many passengers are on the flight in NUM_PASSENGERS. Assuming they are equal.") print("If you intended to have no passengers on this flight, please set Aircraft.CrewPayload.PASSENGER_PAYLOAD_MASS to zero in aviary_values.") aviary_options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, design_num_pax) From 096e77ed6cc9b97a45d16b4233f12edd3196c64e Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Tue, 29 Oct 2024 15:15:33 -0400 Subject: [PATCH 100/113] fixed settings verbosity and removed proprocess_options() from N3CC model --- .../run_multimission_example_large_single_aisle.py | 1 + aviary/models/N3CC/N3CC_data.py | 4 ++-- aviary/utils/preprocessors.py | 4 ++++ 3 files changed, 7 insertions(+), 2 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py index 9a0c465e4..44527e823 100644 --- a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py @@ -78,6 +78,7 @@ def __init__(self, aviary_values, phase_infos, weights): prob = av.AviaryProblem() prob.load_inputs(aviary_values, phase_info) prob.check_and_preprocess_inputs() + exit() prob.add_pre_mission_systems() prob.add_phases() prob.add_post_mission_systems() diff --git a/aviary/models/N3CC/N3CC_data.py b/aviary/models/N3CC/N3CC_data.py index cfffe854e..3c90ae261 100644 --- a/aviary/models/N3CC/N3CC_data.py +++ b/aviary/models/N3CC/N3CC_data.py @@ -20,7 +20,6 @@ from aviary.subsystems.propulsion.utils import build_engine_deck from aviary.utils.aviary_values import AviaryValues from aviary.utils.test_utils.default_subsystems import get_default_premission_subsystems, get_default_mission_subsystems -from aviary.utils.preprocessors import preprocess_options from aviary.utils.functions import get_path from aviary.variable_info.variables import Aircraft, Dynamic, Mission, Settings from aviary.variable_info.enums import EquationsOfMotion, LegacyCode @@ -447,7 +446,8 @@ # Create engine model engine = build_engine_deck(aviary_options=inputs) -preprocess_options(inputs, engine_models=engine) +# Calls to preprocess_options() in this location should be avoided because they +# # will trigger when get_flops_inputs() is imported # build subsystems default_premission_subsystems = get_default_premission_subsystems('FLOPS', engine) diff --git a/aviary/utils/preprocessors.py b/aviary/utils/preprocessors.py index 02c52353f..5b7e20b5f 100644 --- a/aviary/utils/preprocessors.py +++ b/aviary/utils/preprocessors.py @@ -24,6 +24,10 @@ def preprocess_options(aviary_options: AviaryValues, **kwargs): except KeyError: engine_models = None + if Settings.VERBOSITY not in aviary_options: + aviary_options.set_val( + Settings.VERBOSITY, _MetaData[Settings.VERBOSITY]['default_value']) + preprocess_crewpayload(aviary_options) preprocess_propulsion(aviary_options, engine_models) From 631c4b4296e93110b75357a0e455af3039747a3b Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Wed, 30 Oct 2024 12:36:34 -0400 Subject: [PATCH 101/113] fixed preprocess_options inports for multiple N3CC related tests. removed exit from multimission --- .../run_multimission_example_large_single_aisle.py | 1 - aviary/mission/flops_based/ode/test/test_landing_eom.py | 4 ++++ aviary/mission/flops_based/ode/test/test_landing_ode.py | 7 ++++++- aviary/mission/flops_based/ode/test/test_takeoff_ode.py | 6 +++++- aviary/models/N3CC/N3CC_data.py | 2 ++ .../subsystems/mass/flops_based/test/test_landing_gear.py | 4 ++++ 6 files changed, 21 insertions(+), 3 deletions(-) diff --git a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py index 44527e823..9a0c465e4 100644 --- a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py @@ -78,7 +78,6 @@ def __init__(self, aviary_values, phase_infos, weights): prob = av.AviaryProblem() prob.load_inputs(aviary_values, phase_info) prob.check_and_preprocess_inputs() - exit() prob.add_pre_mission_systems() prob.add_phases() prob.add_post_mission_systems() diff --git a/aviary/mission/flops_based/ode/test/test_landing_eom.py b/aviary/mission/flops_based/ode/test/test_landing_eom.py index 1b0a58be7..220effc62 100644 --- a/aviary/mission/flops_based/ode/test/test_landing_eom.py +++ b/aviary/mission/flops_based/ode/test/test_landing_eom.py @@ -12,6 +12,8 @@ from aviary.utils.test_utils.variable_test import assert_match_varnames from aviary.validation_cases.validation_tests import do_validation_test from aviary.variable_info.variables import Dynamic +from aviary.subsystems.propulsion.utils import build_engine_deck +from aviary.utils.preprocessors import preprocess_options class FlareEOMTest(unittest.TestCase): @@ -25,6 +27,8 @@ def setUp(self): time, _ = detailed_landing_flare.get_item('time') nn = len(time) aviary_options = inputs + engine = build_engine_deck(aviary_options) + preprocess_options(aviary_options, engine_models=engine) prob.model.add_subsystem( "landing_flare_eom", diff --git a/aviary/mission/flops_based/ode/test/test_landing_ode.py b/aviary/mission/flops_based/ode/test/test_landing_ode.py index 0c863e6d5..00310a904 100644 --- a/aviary/mission/flops_based/ode/test/test_landing_ode.py +++ b/aviary/mission/flops_based/ode/test/test_landing_ode.py @@ -11,6 +11,7 @@ detailed_landing_flare, inputs, landing_subsystem_options) from aviary.validation_cases.validation_tests import do_validation_test from aviary.variable_info.variables import Dynamic, Aircraft +from aviary.utils.preprocessors import preprocess_options class FlareODETest(unittest.TestCase): @@ -24,8 +25,12 @@ def test_case(self): nn = len(time) aviary_options = inputs + engine = build_engine_deck(aviary_options) + + preprocess_options(aviary_options, engine_models=engine) + default_mission_subsystems = get_default_mission_subsystems( - 'FLOPS', build_engine_deck(aviary_options)) + 'FLOPS', engine) prob.model.add_subsystem( "landing_flare_ode", diff --git a/aviary/mission/flops_based/ode/test/test_takeoff_ode.py b/aviary/mission/flops_based/ode/test/test_takeoff_ode.py index daecf73cb..460680614 100644 --- a/aviary/mission/flops_based/ode/test/test_takeoff_ode.py +++ b/aviary/mission/flops_based/ode/test/test_takeoff_ode.py @@ -11,6 +11,7 @@ detailed_takeoff_climbing, detailed_takeoff_ground, takeoff_subsystem_options, inputs) from aviary.validation_cases.validation_tests import do_validation_test from aviary.variable_info.variables import Dynamic, Mission, Aircraft +from aviary.utils.preprocessors import preprocess_options takeoff_subsystem_options = deepcopy(takeoff_subsystem_options) @@ -75,9 +76,12 @@ def _make_prob(climbing): time, _ = detailed_takeoff_climbing.get_item('time') nn = len(time) aviary_options = inputs + engine = build_engine_deck(aviary_options) + + preprocess_options(aviary_options, engine_models=engine) default_mission_subsystems = get_default_mission_subsystems( - 'FLOPS', build_engine_deck(aviary_options)) + 'FLOPS', engine) prob.model.add_subsystem( "takeoff_ode", diff --git a/aviary/models/N3CC/N3CC_data.py b/aviary/models/N3CC/N3CC_data.py index 3c90ae261..ccea7fb00 100644 --- a/aviary/models/N3CC/N3CC_data.py +++ b/aviary/models/N3CC/N3CC_data.py @@ -23,6 +23,7 @@ from aviary.utils.functions import get_path from aviary.variable_info.variables import Aircraft, Dynamic, Mission, Settings from aviary.variable_info.enums import EquationsOfMotion, LegacyCode +# from aviary.utils.preprocessors import preprocess_options N3CC = {} inputs = N3CC['inputs'] = AviaryValues() @@ -448,6 +449,7 @@ engine = build_engine_deck(aviary_options=inputs) # Calls to preprocess_options() in this location should be avoided because they # # will trigger when get_flops_inputs() is imported +# preprocess_options(inputs, engine_models=engine) # build subsystems default_premission_subsystems = get_default_premission_subsystems('FLOPS', engine) diff --git a/aviary/subsystems/mass/flops_based/test/test_landing_gear.py b/aviary/subsystems/mass/flops_based/test/test_landing_gear.py index a02d8b923..59a056984 100644 --- a/aviary/subsystems/mass/flops_based/test/test_landing_gear.py +++ b/aviary/subsystems/mass/flops_based/test/test_landing_gear.py @@ -1,3 +1,5 @@ +from aviary.subsystems.propulsion.utils import build_engine_deck +from aviary.utils.preprocessors import preprocess_options import unittest import openmdao.api as om @@ -157,6 +159,8 @@ def test_derivs(self, case_name): prob = self.prob model = prob.model flops_inputs = get_flops_inputs(case_name) + engine = build_engine_deck(flops_inputs) + preprocess_options(flops_inputs, engine_models=engine) model.add_subsystem( 'main', MainGearLength(aviary_options=flops_inputs), promotes=['*']) From 1021d6388d2ba2739f124f0b0a57686ff39bc72a Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Wed, 30 Oct 2024 14:56:24 -0400 Subject: [PATCH 102/113] glue updates and variable_meta_data spaces removed --- aviary/docs/examples/multi-missions.ipynb | 45 ++++++++++++++-------- aviary/docs/user_guide/multi-mission.ipynb | 6 ++- aviary/variable_info/variable_meta_data.py | 8 ++-- 3 files changed, 37 insertions(+), 22 deletions(-) diff --git a/aviary/docs/examples/multi-missions.ipynb b/aviary/docs/examples/multi-missions.ipynb index ebc83354f..be48f5cc0 100644 --- a/aviary/docs/examples/multi-missions.ipynb +++ b/aviary/docs/examples/multi-missions.ipynb @@ -15,12 +15,26 @@ "from aviary.api import Aircraft, Mission, AviaryProblem\n", "from aviary.examples.multi_missions import run_multimission_example_large_single_aisle\n", "\n", - "glue_variable('Design.RANGE',f'{Mission.Design.RANGE=}'.split('=')[0], md_code=True)\n", - "glue_variable('Design.NUM_PASSENGERS', f'{Aircraft.CrewPayload.Design.NUM_PASSENGERS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Mission.Design.RANGE=}'.split('=')[0], md_code=True)\n", + "\n", "glue_variable(f'{Aircraft.CrewPayload.NUM_PASSENGERS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.CrewPayload.NUM_BUSINESS_CLASS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.CrewPayload.NUM_FIRST_CLASS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.CrewPayload.NUM_TOURIST_CLASS=}'.split('=')[0], md_code=True)\n", + "\n", + "glue_variable(f'{Aircraft.CrewPayload.Design.NUM_PASSENGERS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.CrewPayload.Design.NUM_FIRST_CLASS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS=}'.split('=')[0], md_code=True)\n", "\n", "glue_variable('capi',AviaryProblem.check_and_preprocess_inputs.__name__+'()',md_code=True)\n", - "glue_variable(Aircraft.CrewPayload.NUM_BUSINESS_CLASS.split(':')[-1])\n", + "glue_variable(f'{Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Mission.Summary.CRUISE_MACH=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.LandingGear.MAIN_GEAR_MASS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.LandingGear.NOSE_GEAR_MASS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.Wing.SWEEP=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Mission.Design.GROSS_MASS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.Design.EMPTY_MASS=}'.split('=')[0], md_code=True)\n", "\n" ] }, @@ -34,20 +48,19 @@ "https://github.com/OpenMDAO/Aviary/tree/main/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py) demonstrates the capability to optimize an aircraft design considering two missions that the aircraft will perform. For a background on this example see [Multi-Mission Overview](../user_guide/multi-mission).\n", "\n", "## Implementation\n", - "The user must supply the following inputs for a multi-mission:\n", + "At a minimum, the user must supply the following inputs for a multi-mission:\n", "* 2 aircraft configuration examples (i.e. .csv files)\n", "* 2 `phase_info` describing the different aircraft missions\n", "* a weighting of the relative importance of each mission\n", - "* {glue:md}`Design.RANGE`\n", - "* {glue:md}`Design.NUM_PASSENGERS`\n", - "* `LANDING_TO_TAKEOFF_MASS_RATIO` or `Summary.CRUISE_MACH`\n", + "* {glue:md}`Mission.Design.RANGE`\n", + "* {glue:md}`Aircraft.CrewPayload.Design.NUM_PASSENGERS`\n", + "* {glue:md}`Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO`\n", "\n", "### Aircraft Configuration\n", - "In the example, we import a single aircraft configuration (LargeSingleAisle2FLOPS) and then modify it to create a primary mission which carries 162 passengers and a deadhead mission. The deadhead mission is a mission without passengers, but it still has the same number of seats in the aircraft, even though those seats are empty. The number of seats for passenters in the aircraft, as well as some other systems like passenger airconditioning mass, is set by `Aircraft.CrewPayload.Design` values of {glue:md}`Design.NUM_PASSENGERS`, `num_tourist_class`, `num_business_class`, and `num_first_class`. Whereas the actual number of passengers on the flight is specified by those same variables but in `Aircraft.CrewPayload` i.e. `AircraftCrewPayload.NUM_PASSENGERS`. \n", + "In the example, we import a single aircraft configuration (LargeSingleAisle2FLOPS) and then modify it to create a primary mission which carries 162 passengers and a deadhead mission. The deadhead mission is a mission without passengers, but it still has the same number of seats in the aircraft, even though those seats are empty. The number of seats for passenters in the aircraft, as well as some other systems like passenger airconditioning mass, is set by values of {glue:md}`Aircraft.CrewPayload.Design.NUM_PASSENGERS`, {glue:md}`Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS`, {glue:md}`Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS`, and {glue:md}`Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS`. Whereas the actual number of passengers on the flight is specified by variables of {glue:md}`Aircraft.CrewPayload.NUM_PASSENGERS`, {glue:md}`Aircraft.CrewPayload.NUM_TOURIST_CLASS`, {glue:md}`Aircraft.CrewPayload.NUM_BUSINESS_CLASS`, and {glue:md}`Aircraft.CrewPayload.NUM_BUSINESS_CLASS`.\n", "\n", "### Phase Info\n", - "The same mission distance and profile (takeoff, climb, cruise, descent, landing) is being flown for both missions. To enable this, a single phase_info is imported and then copied. The user could modify the deadhead mission to be different from the primary mission by changing the target_range of the deadhead mission to a different value. \n", - "I.E. `phase_info_deadhead['post_mission']['target_range'] = [1500, \"nmi\"]` \n", + "The same mission distance and profile (takeoff, climb, cruise, descent, landing) is being flown for both missions. To enable this, a single phase_info is imported and then deepcopied. The user could modify the deadhead mission to be different from the primary mission by changing the target_range of the deadhead mission to a different value, for example by changing `phase_info_deadhead['post_mission']['target_range'] = [1500, \"nmi\"]` \n", "\n", "### Weighting\n", "The `weights` input value describes the relative importance or frequence of one mission over the other. In the example, the the weigting is [9,1] indicating that for every nine times the aircraft flies a full passenger load, it flies a single deadhead leg. These weightings are based on user input and are converted into fractions. This weighting can be estimated from examining historical passenger loads on a typical aircraf route of interest. The objective function is based on combining the fuel-burn values from both missions and multiplying that by the weights. Other objectives, like max range, have not been tested yet.\n", @@ -55,23 +68,23 @@ "### Setting Values\n", "The {glue:md}`Mission.Design.RANGE` value must be set to size some of Aviary's subsystems. These subsystems, such as avionics, have increasing mass as {glue:md}`Mission.Design.RANGE` increases. These are first order approximations that come with aviary. But because of these, we must ensure that both pre-missions have the same {glue:md}`Mission.Design.RANGE`, even if the actual range flown buy each mission (target_rage) is different. Without this, the avoinics mass calculated in pre-mission would be different for the two missions, resulting in a different aircraft design, which is counter to what is intended with the multi-mission feature. \n", "\n", - "The total number of passengers (`Aircraft.CrewPayload.Design.NUM_PASENGERS`) and the design number of passengers of each type (business, tourist, first class), help to define the passenger air conditioning subsystems and the passenger support mass (seats) respectively. Thus when these values are set equal in the primary and deadhead missions, we ensure the aircraft will be designed similarly. \n", + "The total number of passengers ({glue:md}`Aircraft.CrewPayload.Design.NUM_PASENGERS`) and the design number of passengers of each type (business, tourist, first class), help to define the passenger air conditioning subsystems and the passenger support mass (seats) respectively. Thus when these values are set equal in the primary and deadhead missions, we ensure the aircraft will be designed similarly. \n", "\n", - "It is good practice, but not required, to set `LANDING_TO_TAKEOFF_MASS_RATIO` in Aviary Values to ensure consistent design of the landing gear for both missions. This combined with Design.GROSS_MASS helps to ensure that `MAIN_GEAR_MASS` and `NOSE_GEAR_MASSES` are the same for both missions. If `LANDING_TO_TAKEOFF_MASS_RATIO` is not set, it will be caluclated based on `Summary.CRUISE_MACH` and {glue:md}`Mission.Design.RANGE`. This is potentially problematic because `Summary.CRUISE_MACH` may not be set, and instead cruse mach may be optimized. In that case, `Summary.CRUISE_MACH` could vary between the Primary and Deadhead missions, which would then cascade into differeing `MAIN_GEAR_MASS` which causes the aircraft designs to diverge.\n", + "It is good practice, but not required, to set {glue:md}`Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO` in Aviary Values to ensure consistent design of the landing gear for both missions. This combined with Design.GROSS_MASS helps to ensure that {glue:md}`Aircraft.LandingGear.MAIN_GEAR_MASS` and {glue:md}`Aircraft.LandingGear.NOSE_GEAR_MASS` are the same for both missions. If {glue:md}`Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO` is not set, Landing Gear Masses will be caluclated based on {glue:md}`Mission.Summary.CRUISE_MACH` and {glue:md}`Mission.Design.RANGE`. This is potentially problematic because {glue:md}`Mission.Summary.CRUISE_MACH` may not be set, and instead cruse mach may be optimized. In that case, {glue:md}`Mission.Summary.CRUISE_MACH` could vary between the Primary and Deadhead missions, which would then cascade into differeing {glue:md}`Aircraft.LandingGear.MAIN_GEAR_MASS` which causes the aircraft designs to diverge.\n", "\n", "## Theory\n", - "Each of the two missions in the example are instantiated as aviary problems, so there are two pre-missions, two missions run in parallel. Two get the pre-missions to have the same aircraft design, `Mission.Design.GROSS_MASS`, {glue:md}`Mission.Design.RANGE`, `Aircraft.Wing.SPAN`, and `Aircraft.Wing.AREA`, are promoted out of the pre-missions to a single values. This ensures that the aircrafts in both pre-missions have the same design even though their passenger count and fuel mass are different. There is no post-mission for the example, but if one was required for calculating cost or acoustic constraints, there would need to be two post-mission systems as well.\n", + "Each of the two missions in the example are instantiated as separate aviary problems before copying those two groups over to a single `super_prob`. This means there are two pre-missions, two missions run in parallel. Two get the pre-missions to have the same aircraft design, {glue:md}`Mission.Design.GROSS_MASS`, {glue:md}`Mission.Design.RANGE`, {glue:md}`Aircraft.Wing.SWEEP`, are promoted out of the pre-missions to a single values. This ensures that the aircrafts in both pre-missions have the same design even though their passenger count and fuel mass are different. There is no post-mission for the example, but if one was required for calculating cost or acoustic constraints, there would need to be two post-mission systems as well.\n", "\n", - "To impact the structure of aviary problems as little as possible, after instantiation of the pre-mission, mission, and post-mission systems, the connections between those systems are created. Then those groups are then copied over into a regular openmdao problem called `super_prob`. This enables the use all the basic aviary connection and checking functions with minimal modification. \n", + "To impact the structure of aviary problems as little as possible, after instantiation of the pre-mission, mission, and post-mission systems, the connections between those systems are created. Then those groups are then copied over into a regular openmdao problem called `super_prob`. This enables the use all the basic aviary connection and checking functions with minimal modification. There originally was a desire to use openmdao subproblems for this implementation but derivatives through subproblems were not available at that time.\n", "\n", "Initialization of states and variables is conducted last through `prob.set_initial_guesses()`. This has to be completed after the aviary groups are added to `super_prob`. Setting initial guesses and then copying over a group into `super_prob` will not work in this case because initial guesses is set on the problem, not the group. \n", "\n", "Some custom graphing and print functions were added to this example because the basic aviary graphing programs have not yet been modified to handle two database file from two separate missions. The user can see detailed info of each mission result using the `super_prob.model.group_1.list_vars()` commands listed in the comments at the bottom of the example.\n", "\n", "## Best Pratices\n", - "The user should be cognizant of the implications of having two pre-mission systems, one for each mission. Both of the pre-mission systems should be nearly identical in setup, save fuel-mass, passenger, and payload calculations. There are numerous opportunities for the user to get this wrong, and accidentally create two different aircraft as a result. For example, in a previous iteration of this example, `LANDING_TO_TAKEOFF_MASS_RATIO` was not specified, which resulted in two different landing gears being designed, one for the Primary mission, one for the Deadhead mission.\n", + "The user should be cognizant of the implications of having two pre-mission systems, one for each mission. Both of the pre-mission systems should be nearly identical in setup, save fuel-mass, passenger, and payload calculations. There are numerous opportunities for the user to get this wrong, and accidentally create two different aircraft as a result. For example, in a previous iteration of this example, {glue:md}`Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO` was not specified, which resulted in two different landing gears being designed, one for the Primary mission, one for the Deadhead mission.\n", "\n", - "If you are having trouble getting your `Aircraft.Design.EMPTY_MASS` (the final drymass mass summation from pre-mission) to be equal for both pre-missions, use the following OpenMDAO commends at the end of the example to list out and compare the mass from each subsystem.\n", + "If you are having trouble getting your {glue:md}`Aircraft.Design.EMPTY_MASS` (the final drymass mass summation from pre-mission) to be equal for both pre-missions, use the following OpenMDAO commends at the end of the example to list out and compare the mass from each subsystem.\n", "\n", "```\n", "super_prob.model.group_1.list_vars(val=True, units=True, print_arrays=False)\n", diff --git a/aviary/docs/user_guide/multi-mission.ipynb b/aviary/docs/user_guide/multi-mission.ipynb index ebb649b0e..ac2126ac0 100644 --- a/aviary/docs/user_guide/multi-mission.ipynb +++ b/aviary/docs/user_guide/multi-mission.ipynb @@ -30,7 +30,9 @@ "glue_variable(f'{Aircraft.CrewPayload.NUM_PASSENGERS=}'.split('=')[0], md_code=True)\n", "\n", "glue_variable('capi',AviaryProblem.check_and_preprocess_inputs.__name__+'()',md_code=True)\n", - "glue_variable(Aircraft.CrewPayload.NUM_BUSINESS_CLASS.split(':')[-1])\n" + "glue_variable(f'{Aircraft.CrewPayload.NUM_BUSINESS_CLASS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.CrewPayload.NUM_FIRST_CLASS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.CrewPayload.NUM_TOURIST_CLASS=}'.split('=')[0], md_code=True)\n" ] }, { @@ -48,7 +50,7 @@ "The objective function is based on combining the fuel-burn values from both missions and the optimizers objective is to minimize the weighted fuel-burn. Other objectives, like max range, have not been tested yet.\n", "\n", "## Design vs. As-Flown\n", - "To support the need to design an aircraft with a certain number of seats, but then possibly fly missions with unfilled seats, a distinction in the metadata was introduced between {glue:md}`Aircraft.CrewPayload.Design.NUM_PASSENGERS` and {glue:md}`Aircraft.CrewPayload.NUM_PASSENGERS`. The individual passenger classes (num_first_class, {glue:md}`num_buisness_class`, num_tourist_class) also have these distinctions. The Design values represent how many seats are available in the aircraft. Whereas the non-design values represent an as-flow value of how many passengers are on a particular flight. \n", + "To support the need to design an aircraft with a certain number of seats, but then possibly fly missions with unfilled seats, a distinction in the metadata was introduced between {glue:md}`Aircraft.CrewPayload.Design.NUM_PASSENGERS` and {glue:md}`Aircraft.CrewPayload.NUM_PASSENGERS`. The individual passenger classes ({glue:md}`Aircraft.CrewPayload.NUM_FIRST_CLASS`, {glue:md}`Aircraft.CrewPayload.NUM_BUSINESS_CLASS`, {glue:md}`Aircraft.CrewPayload.NUM_TOURIST_CLASS`) also have these distinctions. The Design values represent how many seats are available in the aircraft. Whereas the non-design values represent an as-flow value of how many passengers are on a particular flight. \n", "\n", "A number of checks exist in {glue:md}`capi` to help the user in the case that incomplete as-flow or design passenger information is provided. This was done to provide backward compatability for older aircraft models.\n", "\n", diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index 4830653e3..673383eb3 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -699,11 +699,11 @@ default_value=0.7, ) -# ___ _ -# | \ ___ ___ (_) __ _ _ _ -# | |) | / -_) (_-< | | / _` | | ' \ +# ___ _ +# | \ ___ ___ (_) __ _ _ _ +# | |) | / -_) (_-< | | / _` | | ' \ # |___/ \___| /__/ |_| \__, | |_||_| -# ====================== |___/ ====== +# ====================== |___/ ====== add_meta_data( Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, From 98ccb21eab68a9052c1eee02f8393fcc668dca98 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Wed, 30 Oct 2024 15:22:42 -0400 Subject: [PATCH 103/113] added more glue, removed printing of span and area and Design.Fuel_mass from multi_mission example because not useful outputs. --- 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z@}o5O&#&-P&i=on%0IvV|G)faF1SDa{|WhjF(KdlTT&JKM4svN5Z^}DHqgr6edyx< E0ek=C#sB~S diff --git a/aviary/docs/examples/multi-missions.ipynb b/aviary/docs/examples/multi-missions.ipynb index be48f5cc0..1b7be980f 100644 --- a/aviary/docs/examples/multi-missions.ipynb +++ b/aviary/docs/examples/multi-missions.ipynb @@ -34,8 +34,12 @@ "glue_variable(f'{Aircraft.LandingGear.NOSE_GEAR_MASS=}'.split('=')[0], md_code=True)\n", "glue_variable(f'{Aircraft.Wing.SWEEP=}'.split('=')[0], md_code=True)\n", "glue_variable(f'{Mission.Design.GROSS_MASS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Mission.Summary.GROSS_MASS=}'.split('=')[0], md_code=True)\n", "glue_variable(f'{Aircraft.Design.EMPTY_MASS=}'.split('=')[0], md_code=True)\n", - "\n" + "glue_variable(f'{Mission.Summary.FUEL_BURNED=}'.split('=')[0], md_code=True)\n", + "\n", + "glue_variable(f'{Aircraft.Furnishings.MASS=}'.split('=')[0], md_code=True)\n", + "glue_variable(f'{Aircraft.CrewPayload.PASSENGER_SERVICE_MASS=}'.split('=')[0], md_code=True)\n" ] }, { @@ -100,30 +104,31 @@ "The results of the [Multi-mission Example](\n", "https://github.com/OpenMDAO/Aviary/tree/main/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py) are included in the data table and plots below.\n", "\n", - "From the table results we can see that the Primary mission have the same `Design.EMPTY_MASS` and `Design.GROSS_MASS`. However, the `Summary.GROSS_MASS` varies as expected because these represent \"as-flown\" values. The Primary mission has the higher `Summary.GROSS_MASS` which corresponds to the full passenger load and bags. Consequently, the `Summary.FUEL_BURNED` for each mission is different, higher for the Primary mission, as expected because this mission is carrying more mass for the same mission. `Design.FUEL_MASS` is automatically calculated, it is higher for the Deadhead mission, indicating that the aircraft could hold more fuel, however, that fuel is not needed for the mission. `Wing.SPAN` and `Wing.AERA` are the same for both missions, indicating that the aircraft has been designed similarly in both cases. We do not want to see different values for the wing design because it would mean that the two pre-mission systems are not mirroring eachother. If they were not the same it would mean we are designing two different aircraft. \n", + "From the table results we can see that the Primary mission have the same {glue:md}`Aircraft.Design.EMPTY_MASS` and {glue:md}`Mission.Design.GROSS_MASS`. However, the {glue:md}`Mission.Summary.GROSS_MASS` varies as expected because these represent \"as-flown\" values. The Primary mission has the higher {glue:md}`Mission.Summary.GROSS_MASS` which corresponds to the full passenger load and bags. Consequently, the {glue:md}`Mission.Summary.FUEL_BURNED` for each mission is different, higher for the Primary mission, as expected because this mission is carrying more mass for the same mission. {glue:md}`Aircraft.Wing.SWEEP`is the same for both missions, indicating that the aircraft has been designed similarly in both cases. We do not want to see different values for the wing design because it would mean that the two pre-mission systems are not mirroring eachother. If they were not the same it would mean we are designing two different aircraft. \n", "\n", - "The Landing_gear masses were also displayed because they are sensitive to `LANDING_TO_TAKEOFF_MASS_RATIO` and `Summary.CRUISE_MACH`, which the user may or may not have specified in Aviary_values. We expect these landing gear masses to be the same and they are which is good news for us and indicates that both pre-mission designs are mirroring eachother.\n", + "The Landing_gear masses were also displayed because they are sensitive to {glue:md}`Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO` and {glue:md}`Mission.Summary.CRUISE_MACH`, which the user may or may not have specified in Aviary_values. We expect these landing gear masses to be the same and they are which is good news for us and indicates that both pre-mission designs are mirroring eachother.\n", "\n", - "Lastly the `Furnishings.MASS` and `CREW_AND_PAYLOAD.PASSENGER_SERVICE_MASS` are displayed. These values represent the weight of the seats and the air conditioning system for the passengers. They are both the same which is what we expect to see.\n", + "Lastly the {glue:md}`Aircraft.Furnishings.MASS` and {glue:md}`Aircraft.CrewPayload.PASSENGER_SERVICE_MASS` are displayed. These values represent the weight of the seats and the air conditioning system for the passengers. They are both the same which is what we expect to see.\n", "\n", "A summary colum called 'Expectations' is included as a summary of what we want to see when evaluating this data. \n", "\n", "| Variable | Primary | Deadhead | Expectations |\n", "|:-------------------------------------------------|:-----------------------------:|:--------------------:|---:|\n", - "|MISSION.DESIGN.GROSS_MASS | 174200.00 (lbm) | 174200.00 (lbm) | Equal |\n", - "|AIRCRAFT.DESIGN.EMPTY_MASS | 88183.64 (lbm) | 88183.64 (lbm) | Equal |\n", - "|MISSION.SUMMARY.GROSS_MASS | 158666.39 (lbm) | 152894.30 (lbm) | Different |\n", - "|MISSION.SUMMARY.FUEL_BURNED | 27508.15 (lbm) | 26679.17 (lbm) | Different |\n", - "|MISSION.DESIGN.FUEL_MASS | 43041.75 (lbm) | 47984.87 (lbm) | Different |\n", - "|MISSION.SUMMARY.TOTAL_FUEL_MASS | 27508.15 (lbm) | 26679.17 (lbm) | Different |\n", - "|AIRCRAFT.WING.SPAN | 112.58 (ft) | 112.58 (ft) | Equal |\n", - "|AIRCRAFT.WING.AREA | 1340.98 (ft**2) | 1340.98(ft**2) | Equal |\n", - "|AIRCRAFT.LANDING_GEAR.MAIN_GEAR_MASS | 6348.73 (lbm) | 6348.73 (lbm) | Equal |\n", - "|AIRCRAFT.LANDING_GEAR.NOSE_GEAR_MASS | 799.54 (lbm) | 799.54 (lbm) | Equal |\n", - "|AIRCRAFT.DESIGN.LANDING_TO_TAKEOFF_MASS_RATIO | 0.84 (unitless) | 0.84 (unitless) | Equal |\n", - "|MISSION.SUMMARY.CRUISE_MACH | 0.785 (unitless) | 0.785 (unitless) | Equal |\n", - "|AIRCRAFT.FURNISHINGS.MASS | 14690.34 (lbm) | 14690.34 (lbm) | Equal |\n", - "|AIRCRAFT.CREW_AND_PAYLOAD.PASSENGER_SERVICE_MASS | 2524.48 (lbm) | 2524.48 (lbm) | Equal |\n", + "|Variable: MISSION.DESIGN.GROSS_MASS | 157271.61813452866 (lbm) | 157271.61813452866 (lbm) | Equal |\n", + "|Variable: AIRCRAFT.DESIGN.EMPTY_MASS | 87405.28415563758 (lbm) | 87405.28415563758 (lbm) | Equal |\n", + "|Variable: MISSION.SUMMARY.GROSS_MASS | 157271.61813452866 (lbm) | 120124.3931958877 (lbm) | Different |\n", + "|Variable: MISSION.SUMMARY.FUEL_BURNED | 26891.72449433127 (lbm) | 22994.499555690258 (lbm) | Different |\n", + "|Variable: MISSION.DESIGN.FUEL_MASS | 26891.724494351714 (lbm) | 60141.724494351714 (lbm) | Different |\n", + "|Variable: MISSION.SUMMARY.TOTAL_FUEL_MASS| 26891.72449433127 (lbm) | 22994.499555690258 (lbm) | Different |\n", + "|Variable: AIRCRAFT.LANDING_GEAR.MAIN_GEAR_MASS| 5761.149085460596 (lbm) | 5761.149085460596 (lbm) | Equal |\n", + "|Variable: AIRCRAFT.LANDING_GEAR.NOSE_GEAR_MASS| 746.6143746941743 (lbm) | 746.6143746941743 (lbm) | Equal |\n", + "|Variable: AIRCRAFT.DESIGN.LANDING_TO_TAKEOFF_MASS_RATIO| 0.84 (unitless) | 0.84 (unitless) | Equal |\n", + "|Variable: MISSION.SUMMARY.CRUISE_MACH | 0.785 (unitless) | 0.785 (unitless) | Equal |\n", + "|Variable: AIRCRAFT.FURNISHINGS.MASS | 14690.33988 (lbm) | 14690.33988 (lbm) | Equal |\n", + "|Variable: AIRCRAFT.CREW_AND_PAYLOAD.PASSENGER_SERVICE_MASS| 2524.475592961527 (lbm) | 2524.475592961527 (lbm) | Equal |\n", + "|Variable: AIRCRAFT.WING.SWEEP | 20.0 (deg) | 20.0 (deg) | Equal |\n", + "\n", + "\n", "\n", "In the graph below The Altitude, Drag force, Throttle command, Mass, Distance, and Mach number of the Primary and Deadhead missions are displayed. The Deadhead mission shows a characteristic smaller mass throughout the flight as expected since we have fewer passengers, and a slightly lower throttle profile to match, indicating the engine is not being pushed as hard to meet the demands of a lighter plane. Otherwise the missions themselves match, showing Mach, Distance, and Altitude all identical for every part of the mission. We did not allow the mach or altitude to be optimized for this mission so these results are not surprising. \n", "\n", diff --git a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py index 9a0c465e4..b36cb5664 100644 --- a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py @@ -293,10 +293,7 @@ def createN2(fileref, prob): (Aircraft.Design.EMPTY_MASS, 'lbm'), (Mission.Summary.GROSS_MASS, 'lbm'), (Mission.Summary.FUEL_BURNED, 'lbm'), - (Mission.Design.FUEL_MASS, 'lbm'), (Mission.Summary.TOTAL_FUEL_MASS, 'lbm'), - (Aircraft.Wing.SPAN, 'ft'), - (Aircraft.Wing.AREA, 'ft**2'), (Aircraft.LandingGear.MAIN_GEAR_MASS, 'lbm'), (Aircraft.LandingGear.NOSE_GEAR_MASS, 'lbm'), (Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO, 'unitless'), From bf5a284620abe7ec091287bfe910ef6e050d4f17 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Wed, 30 Oct 2024 15:32:32 -0400 Subject: [PATCH 104/113] added preprocess_options to N3CC examples in docs. typo in glue fixed for multimission docs --- aviary/docs/examples/multi-missions.ipynb | 2 +- ...S_based_detailed_takeoff_and_landing.ipynb | 19 ++++++++++++++++--- 2 files changed, 17 insertions(+), 4 deletions(-) diff --git a/aviary/docs/examples/multi-missions.ipynb b/aviary/docs/examples/multi-missions.ipynb index 1b7be980f..343e86321 100644 --- a/aviary/docs/examples/multi-missions.ipynb +++ b/aviary/docs/examples/multi-missions.ipynb @@ -72,7 +72,7 @@ "### Setting Values\n", "The {glue:md}`Mission.Design.RANGE` value must be set to size some of Aviary's subsystems. These subsystems, such as avionics, have increasing mass as {glue:md}`Mission.Design.RANGE` increases. These are first order approximations that come with aviary. But because of these, we must ensure that both pre-missions have the same {glue:md}`Mission.Design.RANGE`, even if the actual range flown buy each mission (target_rage) is different. Without this, the avoinics mass calculated in pre-mission would be different for the two missions, resulting in a different aircraft design, which is counter to what is intended with the multi-mission feature. \n", "\n", - "The total number of passengers ({glue:md}`Aircraft.CrewPayload.Design.NUM_PASENGERS`) and the design number of passengers of each type (business, tourist, first class), help to define the passenger air conditioning subsystems and the passenger support mass (seats) respectively. Thus when these values are set equal in the primary and deadhead missions, we ensure the aircraft will be designed similarly. \n", + "The total number of passengers ({glue:md}`Aircraft.CrewPayload.Design.NUM_PASSENGERS`) and the design number of passengers of each type (business, tourist, first class), help to define the passenger air conditioning subsystems and the passenger support mass (seats) respectively. Thus when these values are set equal in the primary and deadhead missions, we ensure the aircraft will be designed similarly. \n", "\n", "It is good practice, but not required, to set {glue:md}`Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO` in Aviary Values to ensure consistent design of the landing gear for both missions. This combined with Design.GROSS_MASS helps to ensure that {glue:md}`Aircraft.LandingGear.MAIN_GEAR_MASS` and {glue:md}`Aircraft.LandingGear.NOSE_GEAR_MASS` are the same for both missions. If {glue:md}`Aircraft.Design.LANDING_TO_TAKEOFF_MASS_RATIO` is not set, Landing Gear Masses will be caluclated based on {glue:md}`Mission.Summary.CRUISE_MACH` and {glue:md}`Mission.Design.RANGE`. This is potentially problematic because {glue:md}`Mission.Summary.CRUISE_MACH` may not be set, and instead cruse mach may be optimized. In that case, {glue:md}`Mission.Summary.CRUISE_MACH` could vary between the Primary and Deadhead missions, which would then cascade into differeing {glue:md}`Aircraft.LandingGear.MAIN_GEAR_MASS` which causes the aircraft designs to diverge.\n", "\n", diff --git a/aviary/docs/user_guide/FLOPS_based_detailed_takeoff_and_landing.ipynb b/aviary/docs/user_guide/FLOPS_based_detailed_takeoff_and_landing.ipynb index e346a650b..c33d2dbdf 100644 --- a/aviary/docs/user_guide/FLOPS_based_detailed_takeoff_and_landing.ipynb +++ b/aviary/docs/user_guide/FLOPS_based_detailed_takeoff_and_landing.ipynb @@ -38,13 +38,25 @@ "execution_count": null, "id": "5fe75e1d", "metadata": {}, - "outputs": [], + "outputs": [ + { + "ename": "", + "evalue": "", + "output_type": "error", + "traceback": [ + "\u001b[1;31mRunning cells with 'base (Python 3.12.5)' requires the ipykernel package.\n", + "\u001b[1;31mRun the following command to install 'ipykernel' into the Python environment. \n", + "\u001b[1;31mCommand: 'conda install -n base ipykernel --update-deps --force-reinstall'" + ] + } + ], "source": [ "from aviary.api import Dynamic, Mission\n", "\n", "import aviary.api as av\n", "\n", "from aviary.models.N3CC.N3CC_data import inputs\n", + "from aviary.utils.preprocessors import preprocess_options\n", "\n", "aviary_options = inputs.deepcopy()\n", "\n", @@ -82,6 +94,7 @@ "# We also need propulsion analysis for takeoff and landing. No additional configuration\n", "# is needed for this builder\n", "engine = av.build_engine_deck(aviary_options)\n", + "preprocess_options(aviary_options, engine_models=engine)\n", "prop_builder = av.CorePropulsionBuilder(engine_models=engine)" ] }, @@ -633,7 +646,7 @@ ], "metadata": { "kernelspec": { - "display_name": "Python 3 (ipykernel)", + "display_name": "base", "language": "python", "name": "python3" }, @@ -647,7 +660,7 @@ "name": "python", "nbconvert_exporter": "python", "pygments_lexer": "ipython3", - "version": "3.10.13" + "version": "3.12.5" } }, "nbformat": 4, From 4b24874a73f196138d70ae6c6a3200081d2f6d0d Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Wed, 30 Oct 2024 15:40:47 -0400 Subject: [PATCH 105/113] updated toc.yml with multi_missions references --- aviary/docs/_toc.yml | 2 ++ 1 file changed, 2 insertions(+) diff --git a/aviary/docs/_toc.yml b/aviary/docs/_toc.yml index 4c53a7e9c..06b8d8da5 100644 --- a/aviary/docs/_toc.yml +++ b/aviary/docs/_toc.yml @@ -45,6 +45,7 @@ parts: - file: user_guide/features/overriding - file: user_guide/FLOPS_based_detailed_takeoff_and_landing - file: user_guide/reserve_missions + - file: user_guide/multi_missions - file: user_guide/off_design_missions - file: user_guide/SGM_capabilities - file: user_guide/troubleshooting @@ -57,6 +58,7 @@ parts: - file: examples/coupled_aircraft_mission_optimization - file: examples/additional_flight_phases - file: examples/reserve_missions + - file: examples/multi_missions - file: examples/off_design_example - file: examples/OAS_subsystem - file: examples/level_2_detailed_takeoff_and_landing From 9a598c50f29eea3553c87fc5e619728916222951 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Wed, 30 Oct 2024 16:21:17 -0400 Subject: [PATCH 106/113] consolidated naming for multi_mission and updated references --- aviary/docs/_toc.yml | 4 ++-- .../examples/{multi-missions.ipynb => multi_mission.ipynb} | 6 +++--- .../user_guide/{multi-mission.ipynb => multi_mission.ipynb} | 2 +- .../run_multimission_example_large_single_aisle.py | 0 4 files changed, 6 insertions(+), 6 deletions(-) rename aviary/docs/examples/{multi-missions.ipynb => multi_mission.ipynb} (96%) rename aviary/docs/user_guide/{multi-mission.ipynb => multi_mission.ipynb} (99%) rename aviary/examples/{multi_missions => multi_mission}/run_multimission_example_large_single_aisle.py (100%) diff --git a/aviary/docs/_toc.yml b/aviary/docs/_toc.yml index 06b8d8da5..37137df5a 100644 --- a/aviary/docs/_toc.yml +++ b/aviary/docs/_toc.yml @@ -45,7 +45,7 @@ parts: - file: user_guide/features/overriding - file: user_guide/FLOPS_based_detailed_takeoff_and_landing - file: user_guide/reserve_missions - - file: user_guide/multi_missions + - file: user_guide/multi_mission - file: user_guide/off_design_missions - file: user_guide/SGM_capabilities - file: user_guide/troubleshooting @@ -58,7 +58,7 @@ parts: - file: examples/coupled_aircraft_mission_optimization - file: examples/additional_flight_phases - file: examples/reserve_missions - - file: examples/multi_missions + - file: examples/multi_mission - file: examples/off_design_example - file: examples/OAS_subsystem - file: examples/level_2_detailed_takeoff_and_landing diff --git a/aviary/docs/examples/multi-missions.ipynb b/aviary/docs/examples/multi_mission.ipynb similarity index 96% rename from aviary/docs/examples/multi-missions.ipynb rename to aviary/docs/examples/multi_mission.ipynb index 343e86321..65c0dab52 100644 --- a/aviary/docs/examples/multi-missions.ipynb +++ b/aviary/docs/examples/multi_mission.ipynb @@ -13,7 +13,7 @@ "# Testing Cell\n", "from aviary.docs.tests.utils import glue_variable\n", "from aviary.api import Aircraft, Mission, AviaryProblem\n", - "from aviary.examples.multi_missions import run_multimission_example_large_single_aisle\n", + "from aviary.examples.multi_mission import run_multimission_example_large_single_aisle\n", "\n", "glue_variable(f'{Mission.Design.RANGE=}'.split('=')[0], md_code=True)\n", "\n", @@ -49,7 +49,7 @@ "# Multi-Mission Example\n", "\n", "The [Multi-mission Example](\n", - "https://github.com/OpenMDAO/Aviary/tree/main/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py) demonstrates the capability to optimize an aircraft design considering two missions that the aircraft will perform. For a background on this example see [Multi-Mission Overview](../user_guide/multi-mission).\n", + "https://github.com/OpenMDAO/Aviary/tree/main/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py) demonstrates the capability to optimize an aircraft design considering two missions that the aircraft will perform. For a background on this example see [Multi-Mission Overview](../user_guide/multi_mission).\n", "\n", "## Implementation\n", "At a minimum, the user must supply the following inputs for a multi-mission:\n", @@ -102,7 +102,7 @@ "source": [ "## Results\n", "The results of the [Multi-mission Example](\n", - "https://github.com/OpenMDAO/Aviary/tree/main/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py) are included in the data table and plots below.\n", + "https://github.com/OpenMDAO/Aviary/tree/main/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py) are included in the data table and plots below.\n", "\n", "From the table results we can see that the Primary mission have the same {glue:md}`Aircraft.Design.EMPTY_MASS` and {glue:md}`Mission.Design.GROSS_MASS`. However, the {glue:md}`Mission.Summary.GROSS_MASS` varies as expected because these represent \"as-flown\" values. The Primary mission has the higher {glue:md}`Mission.Summary.GROSS_MASS` which corresponds to the full passenger load and bags. Consequently, the {glue:md}`Mission.Summary.FUEL_BURNED` for each mission is different, higher for the Primary mission, as expected because this mission is carrying more mass for the same mission. {glue:md}`Aircraft.Wing.SWEEP`is the same for both missions, indicating that the aircraft has been designed similarly in both cases. We do not want to see different values for the wing design because it would mean that the two pre-mission systems are not mirroring eachother. If they were not the same it would mean we are designing two different aircraft. \n", "\n", diff --git a/aviary/docs/user_guide/multi-mission.ipynb b/aviary/docs/user_guide/multi_mission.ipynb similarity index 99% rename from aviary/docs/user_guide/multi-mission.ipynb rename to aviary/docs/user_guide/multi_mission.ipynb index ac2126ac0..d05b50796 100644 --- a/aviary/docs/user_guide/multi-mission.ipynb +++ b/aviary/docs/user_guide/multi_mission.ipynb @@ -55,7 +55,7 @@ "A number of checks exist in {glue:md}`capi` to help the user in the case that incomplete as-flow or design passenger information is provided. This was done to provide backward compatability for older aircraft models.\n", "\n", "## Example\n", - "An example of a multi-mission as well as Setup, Theory, and Results, is presented in [Multi-Mission Examples](../examples/multi-mission)." + "An example of a multi-mission as well as Setup, Theory, and Results, is presented in [Multi-Mission Examples](../examples/multi_mission)." ] } ], diff --git a/aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py similarity index 100% rename from aviary/examples/multi_missions/run_multimission_example_large_single_aisle.py rename to aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py From 65b4778e5df743ff6ff3321e0f616b2993e3ff52 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Mon, 4 Nov 2024 11:32:26 -0500 Subject: [PATCH 107/113] set verbosity, removed checks on keys because they are already set by default, updated warning messages. --- ...multimission_example_large_single_aisle.py | 7 +++--- aviary/utils/preprocessors.py | 22 +++++-------------- 2 files changed, 10 insertions(+), 19 deletions(-) diff --git a/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py index b36cb5664..d72fffdd0 100644 --- a/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py @@ -17,7 +17,7 @@ """ import copy as copy from aviary.examples.example_phase_info import phase_info -from aviary.variable_info.variables import Mission, Aircraft +from aviary.variable_info.variables import Mission, Aircraft, Settings from aviary.variable_info.enums import ProblemType import aviary.api as av import openmdao.api as om @@ -37,6 +37,7 @@ # get large single aisle values aviary_inputs_primary = get_flops_inputs('LargeSingleAisle2FLOPS') aviary_inputs_primary.set_val(Mission.Design.GROSS_MASS, val=100000, units='lbm') +aviary_inputs_primary.set_val(Settings.VERBOSITY, val=1) aviary_inputs_deadhead = copy.deepcopy(aviary_inputs_primary) aviary_inputs_deadhead.set_val('aircraft:crew_and_payload:num_passengers', 1, 'unitless') @@ -153,8 +154,8 @@ def setup_wrapper(self): # some warnings related to variable promotion. Replicating that here with # setup for the super problem with warnings.catch_warnings(): - warnings.simplefilter("ignore", om.OpenMDAOWarning) - warnings.simplefilter("ignore", om.PromotionWarning) + # warnings.simplefilter("ignore", om.OpenMDAOWarning) + # warnings.simplefilter("ignore", om.PromotionWarning) self.setup(check='all') def run(self): diff --git a/aviary/utils/preprocessors.py b/aviary/utils/preprocessors.py index 5b7e20b5f..9344e1554 100644 --- a/aviary/utils/preprocessors.py +++ b/aviary/utils/preprocessors.py @@ -41,20 +41,6 @@ def preprocess_crewpayload(aviary_options: AviaryValues): verbosity = aviary_options.get_val(Settings.VERBOSITY) - # Grab Default all values for num_pax and 1TB (1st class, Tourist Class, Business Class Passengers) to make - # sure they are accessible so we don't have to run checks if they exist again - for key in ( - Aircraft.CrewPayload.NUM_PASSENGERS, - Aircraft.CrewPayload.NUM_FIRST_CLASS, - Aircraft.CrewPayload.NUM_BUSINESS_CLASS, - Aircraft.CrewPayload.NUM_TOURIST_CLASS, - Aircraft.CrewPayload.Design.NUM_PASSENGERS, - Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, - Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, - Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS,): - if key not in aviary_options: - aviary_options.set_val(key, _MetaData[key]['default_value']) - # Sum passenger Counts for later checks and assignments passenger_count = 0 for key in (Aircraft.CrewPayload.NUM_FIRST_CLASS, @@ -126,7 +112,9 @@ def preprocess_crewpayload(aviary_options: AviaryValues): aviary_options.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, num_pax) elif design_passenger_count != 0 and num_pax == 0 and passenger_count == 0: if verbosity >= 1: - print("User has not input as-flown passengers data. Assuming as-flow is equal to design passenger data.") + print("User has specified Design.NUM_* passenger values but CrewPyaload.NUM_* has been left blank or set to zero.") + print( + "Assuming they are equal to maintain backwards compatibility with GASP and FLOPS output files.") print("If you intended to have no passengers on this flight, please set Aircraft.CrewPayload.PASSENGER_PAYLOAD_MASS to zero in aviary_values.") aviary_options.set_val( Aircraft.CrewPayload.NUM_PASSENGERS, design_passenger_count) @@ -139,7 +127,9 @@ def preprocess_crewpayload(aviary_options: AviaryValues): # user has not supplied detailed information on design but has supplied summary information on passengers elif design_num_pax != 0 and num_pax == 0: if verbosity >= 1: - print("User has specified Design.NUM_PASSENGERS but not how many passengers are on the flight in NUM_PASSENGERS. Assuming they are equal.") + print("User has specified Design.NUM_PASSENGERS but CrewPayload.NUM_PASSENGERS has been left blank or set to zero.") + print( + "Assuming they are equal to maintain backwards compatibility with GASP and FLOPS output files.") print("If you intended to have no passengers on this flight, please set Aircraft.CrewPayload.PASSENGER_PAYLOAD_MASS to zero in aviary_values.") aviary_options.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, design_num_pax) From 6ad6148040bd7683f3b53bea382d9425acca82e7 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Mon, 4 Nov 2024 11:37:00 -0500 Subject: [PATCH 108/113] added in warning suppression for openmdao --- .../run_multimission_example_large_single_aisle.py | 4 ++-- 1 file changed, 2 insertions(+), 2 deletions(-) diff --git a/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py index d72fffdd0..42a8cd72c 100644 --- a/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py @@ -154,8 +154,8 @@ def setup_wrapper(self): # some warnings related to variable promotion. Replicating that here with # setup for the super problem with warnings.catch_warnings(): - # warnings.simplefilter("ignore", om.OpenMDAOWarning) - # warnings.simplefilter("ignore", om.PromotionWarning) + warnings.simplefilter("ignore", om.OpenMDAOWarning) + warnings.simplefilter("ignore", om.PromotionWarning) self.setup(check='all') def run(self): From 8a7a1d97687f72c03d85325bd15e35d9ae3b0a42 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Mon, 4 Nov 2024 12:13:36 -0500 Subject: [PATCH 109/113] updated objective to Mission.Summary.FUEL_BURNED and still got good results --- .../run_multimission_example_large_single_aisle.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py b/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py index 42a8cd72c..b0316bf8b 100644 --- a/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py +++ b/aviary/examples/multi_mission/run_multimission_example_large_single_aisle.py @@ -102,7 +102,7 @@ def __init__(self, aviary_values, phase_infos, weights): promotes_inputs=[Mission.Design.GROSS_MASS, Mission.Design.RANGE, Aircraft.Wing.SWEEP], - promotes_outputs=[(Mission.Objectives.FUEL, promoted_name)]) + promotes_outputs=[(Mission.Summary.FUEL_BURNED, promoted_name)]) def add_design_variables(self): self.model.add_design_var(Mission.Design.GROSS_MASS, From ae0915aaf6cd3124708581c1f1a2402a171b39b2 Mon Sep 17 00:00:00 2001 From: Eliot Aretskin-Hariton Date: Mon, 4 Nov 2024 13:06:12 -0500 Subject: [PATCH 110/113] reverted setting default_values of passenger counts because some sub-tests do not successfully set these --- aviary/utils/preprocessors.py | 15 +++++++++++++++ 1 file changed, 15 insertions(+) diff --git a/aviary/utils/preprocessors.py b/aviary/utils/preprocessors.py index 9344e1554..89fef61af 100644 --- a/aviary/utils/preprocessors.py +++ b/aviary/utils/preprocessors.py @@ -41,6 +41,21 @@ def preprocess_crewpayload(aviary_options: AviaryValues): verbosity = aviary_options.get_val(Settings.VERBOSITY) + # Some tests, but not all, do not correctly set default values + # # so we need to ensure all these values are available. + + for key in ( + Aircraft.CrewPayload.NUM_PASSENGERS, + Aircraft.CrewPayload.NUM_FIRST_CLASS, + Aircraft.CrewPayload.NUM_BUSINESS_CLASS, + Aircraft.CrewPayload.NUM_TOURIST_CLASS, + Aircraft.CrewPayload.Design.NUM_PASSENGERS, + Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, + Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, + Aircraft.CrewPayload.Design.NUM_TOURIST_CLASS,): + if key not in aviary_options: + aviary_options.set_val(key, _MetaData[key]['default_value']) + # Sum passenger Counts for later checks and assignments passenger_count = 0 for key in (Aircraft.CrewPayload.NUM_FIRST_CLASS, From e4a1917ae7480417f55e54847863d34a6a207af5 Mon Sep 17 00:00:00 2001 From: Bennett Date: Mon, 4 Nov 2024 13:54:29 -0500 Subject: [PATCH 111/113] off design payload work in progress --- aviary/subsystems/mass/gasp_based/fixed.py | 6 ++++-- aviary/subsystems/mass/gasp_based/fuel.py | 2 +- 2 files changed, 5 insertions(+), 3 deletions(-) diff --git a/aviary/subsystems/mass/gasp_based/fixed.py b/aviary/subsystems/mass/gasp_based/fixed.py index 3f083f3b3..aecbe131d 100644 --- a/aviary/subsystems/mass/gasp_based/fixed.py +++ b/aviary/subsystems/mass/gasp_based/fixed.py @@ -294,12 +294,14 @@ def compute(self, inputs, outputs): Aircraft.CrewPayload.PASSENGER_MASS_WITH_BAGS, units='lbm') PAX = aviary_options.get_val( Aircraft.CrewPayload.NUM_PASSENGERS, units='unitless') + PAX_des = aviary_options.get_val( + Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') cargo_mass = inputs[Aircraft.CrewPayload.CARGO_MASS] outputs[Aircraft.CrewPayload.PASSENGER_PAYLOAD_MASS] = \ payload_mass = pax_mass * PAX - outputs["payload_mass_des"] = payload_mass - outputs["payload_mass_max"] = pax_mass * PAX + cargo_mass + outputs["payload_mass_des"] = pax_mass * PAX_des + outputs["payload_mass_max"] = pax_mass * PAX_des + cargo_mass class ElectricAugmentationMass(om.ExplicitComponent): diff --git a/aviary/subsystems/mass/gasp_based/fuel.py b/aviary/subsystems/mass/gasp_based/fuel.py index b9b973fc9..806905929 100644 --- a/aviary/subsystems/mass/gasp_based/fuel.py +++ b/aviary/subsystems/mass/gasp_based/fuel.py @@ -1344,7 +1344,7 @@ def compute(self, inputs, outputs): - control_wt - fixed_equip_wt - useful_wt - - payload_wt + - payload_wt_des - fuel_sys_wt ) / GRAV_ENGLISH_LBM outputs["fuel_mass_min"] = ( From 8c038042245087bf885e34e0d0b15ca5dd937141 Mon Sep 17 00:00:00 2001 From: cmbenne3 Date: Mon, 18 Nov 2024 17:09:11 -0500 Subject: [PATCH 112/113] wip adding design and as flown cargo_mass distinction for gasp based missions --- aviary/subsystems/mass/gasp_based/fixed.py | 11 ++++++----- aviary/subsystems/mass/gasp_based/fuel.py | 17 +++++++---------- .../mass/gasp_based/mass_premission.py | 2 +- aviary/variable_info/variable_meta_data.py | 14 +++++++++++++- aviary/variable_info/variables.py | 1 + 5 files changed, 28 insertions(+), 17 deletions(-) diff --git a/aviary/subsystems/mass/gasp_based/fixed.py b/aviary/subsystems/mass/gasp_based/fixed.py index aecbe131d..4e757d624 100644 --- a/aviary/subsystems/mass/gasp_based/fixed.py +++ b/aviary/subsystems/mass/gasp_based/fixed.py @@ -276,7 +276,7 @@ def setup(self): "payload_mass_des", val=0, units="lbm", desc="WPLDES: design payload" ) self.add_output( - "payload_mass_max", + "payload_mass", val=0, units="lbm", desc="WPLMAX: maximum payload that the aircraft is being asked to carry" @@ -284,7 +284,7 @@ def setup(self): ) self.declare_partials( - "payload_mass_max", [ + "payload_mass", [ Aircraft.CrewPayload.CARGO_MASS], val=1.0) @@ -297,11 +297,12 @@ def compute(self, inputs, outputs): PAX_des = aviary_options.get_val( Aircraft.CrewPayload.Design.NUM_PASSENGERS, units='unitless') cargo_mass = inputs[Aircraft.CrewPayload.CARGO_MASS] + cargo_mass_des = inputs[Aircraft.CrewPayload.Design.CARGO_MASS] outputs[Aircraft.CrewPayload.PASSENGER_PAYLOAD_MASS] = \ payload_mass = pax_mass * PAX - outputs["payload_mass_des"] = pax_mass * PAX_des - outputs["payload_mass_max"] = pax_mass * PAX_des + cargo_mass + outputs["payload_mass_des"] = pax_mass * PAX_des + cargo_mass_des + outputs["payload_mass"] = pax_mass * PAX + cargo_mass class ElectricAugmentationMass(om.ExplicitComponent): @@ -2490,7 +2491,7 @@ def setup(self): "payload", PayloadMass(aviary_options=aviary_options), promotes_inputs=["aircraft:*"], - promotes_outputs=["payload_mass_des", "payload_mass_max", ] + ["aircraft:*"], + promotes_outputs=["payload_mass_des", "payload_mass", ] + ["aircraft:*"], ) self.add_subsystem( diff --git a/aviary/subsystems/mass/gasp_based/fuel.py b/aviary/subsystems/mass/gasp_based/fuel.py index 806905929..062a812b6 100644 --- a/aviary/subsystems/mass/gasp_based/fuel.py +++ b/aviary/subsystems/mass/gasp_based/fuel.py @@ -1237,7 +1237,7 @@ def setup(self): add_aviary_input(self, Aircraft.CrewPayload.PASSENGER_PAYLOAD_MASS, val=36000) self.add_input( - "payload_mass_max", + "payload_mass", val=46040, units="lbm", desc="WPLMAX: maximum payload that the aircraft is being asked to carry (design payload + cargo)", @@ -1265,6 +1265,7 @@ def setup(self): Aircraft.Design.FIXED_EQUIPMENT_MASS, Aircraft.Design.FIXED_USEFUL_LOAD, "payload_mass_des", + "payload_mass", Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT, Aircraft.Fuel.DENSITY, @@ -1297,7 +1298,7 @@ def setup(self): Aircraft.Controls.TOTAL_MASS, Aircraft.Design.FIXED_EQUIPMENT_MASS, Aircraft.Design.FIXED_USEFUL_LOAD, - "payload_mass_max", + "payload_mass_des", Aircraft.Fuel.FUEL_SYSTEM_MASS, ], val=-1, @@ -1318,9 +1319,7 @@ def compute(self, inputs, outputs): CK21 = inputs[Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER] c_mass_trend_fuel_sys = inputs[Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT] rho_fuel = inputs[Aircraft.Fuel.DENSITY] * GRAV_ENGLISH_LBM - payload_wt = inputs[Aircraft.CrewPayload.PASSENGER_PAYLOAD_MASS] * \ - GRAV_ENGLISH_LBM - payload_wt_max = inputs["payload_mass_max"] * GRAV_ENGLISH_LBM + payload_wt = inputs["payload_mass"] * GRAV_ENGLISH_LBM fuel_margin = inputs[Aircraft.Fuel.FUEL_MARGIN] outputs[Mission.Design.FUEL_MASS] = ( @@ -1354,7 +1353,7 @@ def compute(self, inputs, outputs): - control_wt - fixed_equip_wt - useful_wt - - payload_wt_max + - payload_wt_des - fuel_sys_wt ) / GRAV_ENGLISH_LBM @@ -1373,9 +1372,7 @@ def compute_partials(self, inputs, J): CK21 = inputs[Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER] c_mass_trend_fuel_sys = inputs[Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT] rho_fuel = inputs[Aircraft.Fuel.DENSITY] * GRAV_ENGLISH_LBM - payload_wt = inputs[Aircraft.CrewPayload.PASSENGER_PAYLOAD_MASS] * \ - GRAV_ENGLISH_LBM - payload_wt_max = inputs["payload_mass_max"] * GRAV_ENGLISH_LBM + payload_wt = inputs["payload_mass"] * GRAV_ENGLISH_LBM fuel_margin = inputs[Aircraft.Fuel.FUEL_MARGIN] J[Mission.Design.FUEL_MASS, Mission.Design.GROSS_MASS] = 1 / ( @@ -1531,7 +1528,7 @@ def setup(self): ] higher_level_inputs3 = [ "payload_mass_des", - "payload_mass_max", + "payload_mass", "eng_comb_mass", ] diff --git a/aviary/subsystems/mass/gasp_based/mass_premission.py b/aviary/subsystems/mass/gasp_based/mass_premission.py index 187df60a2..fc19a5aa7 100644 --- a/aviary/subsystems/mass/gasp_based/mass_premission.py +++ b/aviary/subsystems/mass/gasp_based/mass_premission.py @@ -43,7 +43,7 @@ def setup(self): # output values from fixed_mass that are connected to fuel_mass via promotion fuel_mass_fixed_mass_values = [ "payload_mass_des", - "payload_mass_max", + "payload_mass", "wing_mounted_mass", "eng_comb_mass", ] diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index 673383eb3..333ba6e5e 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -684,7 +684,19 @@ ] }, units='lbm', - desc='total mass of cargo' + desc='total mass of as-flown cargo' +) + +add_meta_data( + Aircraft.CrewPayload.Design.CARGO_MASS, + meta_data=_MetaData, + historical_name={"GASP": None, + "FLOPS": None, + "LEAPS1": None + }, + units='lbm', + desc='total mass of cargo for the design mission', + default_value=10040, ) add_meta_data( diff --git a/aviary/variable_info/variables.py b/aviary/variable_info/variables.py index 2cdb61d30..f4e9c0c82 100644 --- a/aviary/variable_info/variables.py +++ b/aviary/variable_info/variables.py @@ -133,6 +133,7 @@ class Design: NUM_FIRST_CLASS = 'aircraft:crew_and_payload:design:num_first_class' NUM_TOURIST_CLASS = 'aircraft:crew_and_payload:design:num_tourist_class' NUM_PASSENGERS = 'aircraft:crew_and_payload:design:num_passengers' + CARGO_MASS = 'aircraft:crew_and_payload:design:cargo_mass' class Design: # These variables are values that do not fall into a particular aircraft From d742f27485d03451d6fad6637ce05c0f96958896 Mon Sep 17 00:00:00 2001 From: cmbenne3 Date: Mon, 18 Nov 2024 17:19:14 -0500 Subject: [PATCH 113/113] wip - optimization running for GwGm with design cargo --- aviary/models/test_aircraft/aircraft_for_bench_GwGm.csv | 1 + aviary/subsystems/mass/gasp_based/fixed.py | 1 + 2 files changed, 2 insertions(+) diff --git a/aviary/models/test_aircraft/aircraft_for_bench_GwGm.csv b/aviary/models/test_aircraft/aircraft_for_bench_GwGm.csv index 2f3c32e0d..3039a89f9 100644 --- a/aviary/models/test_aircraft/aircraft_for_bench_GwGm.csv +++ b/aviary/models/test_aircraft/aircraft_for_bench_GwGm.csv @@ -7,6 +7,7 @@ aircraft:controls:control_mass_increment,0,lbm aircraft:controls:stability_augmentation_system_mass,0,lbm aircraft:controls:stability_augmentation_system_mass_scaler,1,unitless aircraft:crew_and_payload:cargo_mass,10040,lbm +aircraft:crew_and_payload:design:cargo_mass,10040,lbm aircraft:crew_and_payload:catering_items_mass_per_passenger,7.6,lbm aircraft:crew_and_payload:design:num_passengers,180,unitless aircraft:crew_and_payload:passenger_mass_with_bags,200,lbm diff --git a/aviary/subsystems/mass/gasp_based/fixed.py b/aviary/subsystems/mass/gasp_based/fixed.py index 4e757d624..b1d64ff56 100644 --- a/aviary/subsystems/mass/gasp_based/fixed.py +++ b/aviary/subsystems/mass/gasp_based/fixed.py @@ -269,6 +269,7 @@ def initialize(self): def setup(self): add_aviary_input(self, Aircraft.CrewPayload.CARGO_MASS, val=10040) + add_aviary_input(self, Aircraft.CrewPayload.Design.CARGO_MASS, val=10040) add_aviary_output(self, Aircraft.CrewPayload.PASSENGER_PAYLOAD_MASS, val=0)

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