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Merge pull request #97 from crecine/flops_sgm
Initial Implementation of Height Energy in SGM
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@@ -109,6 +109,7 @@ venv/ | |
| ENV/ | ||
| env.bak/ | ||
| venv.bak/ | ||
| .github/*_environment.yml | ||
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| # Spyder project settings | ||
| .spyderproject | ||
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204 changes: 204 additions & 0 deletions
204
aviary/mission/flops_based/phases/test/test_time_integration_phases.py
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| import openmdao.api as om | ||
| from openmdao.utils.assert_utils import assert_near_equal | ||
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| from aviary.interface.methods_for_level2 import AviaryGroup | ||
| from aviary.mission.gasp_based.phases.time_integration_traj import FlexibleTraj | ||
| from aviary.mission.flops_based.phases.time_integration_phases import \ | ||
| SGMHeightEnergy, SGMDetailedTakeoff, SGMDetailedLanding | ||
| from aviary.subsystems.premission import CorePreMission | ||
| from aviary.utils.functions import set_aviary_initial_values | ||
| from aviary.variable_info.enums import Verbosity | ||
| from aviary.variable_info.variables import Aircraft, Dynamic, Mission | ||
| from aviary.variable_info.variables_in import VariablesIn | ||
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| from aviary.interface.default_phase_info.height_energy import aero, prop, geom | ||
| from aviary.subsystems.propulsion.engine_deck import EngineDeck | ||
| from aviary.utils.process_input_decks import create_vehicle | ||
| from aviary.utils.preprocessors import preprocess_propulsion | ||
| from aviary.variable_info.variable_meta_data import _MetaData as BaseMetaData | ||
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| import warnings | ||
| import unittest | ||
| import importlib | ||
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| @unittest.skipUnless(importlib.util.find_spec("pyoptsparse") is not None, "pyoptsparse is not installed") | ||
| class HE_SGMDescentTestCase(unittest.TestCase): | ||
| def setUp(self): | ||
| aviary_inputs, initial_guesses = create_vehicle( | ||
| 'models/test_aircraft/aircraft_for_bench_FwFm.csv') | ||
| aviary_inputs.set_val(Aircraft.Engine.SCALED_SLS_THRUST, val=28690, units="lbf") | ||
| aviary_inputs.set_val(Dynamic.Mission.THROTTLE, val=0, units="unitless") | ||
| aviary_inputs.set_val(Mission.Takeoff.ROLLING_FRICTION_COEFFICIENT, | ||
| val=0.0175, units="unitless") | ||
| aviary_inputs.set_val(Mission.Takeoff.BRAKING_FRICTION_COEFFICIENT, | ||
| val=0.35, units="unitless") | ||
| ode_args = dict(aviary_options=aviary_inputs, core_subsystems=[prop, geom, aero]) | ||
| preprocess_propulsion(aviary_inputs, [EngineDeck(options=aviary_inputs)]) | ||
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| ode_args['num_nodes'] = 1 | ||
| ode_args['subsystem_options'] = {'core_aerodynamics': {'method': 'computed'}} | ||
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| self.ode_args = ode_args | ||
| self.aviary_inputs = aviary_inputs | ||
| self.tol = 1e-5 | ||
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| def setup_prob(self, phases) -> om.Problem: | ||
| prob = om.Problem() | ||
| prob.driver = om.pyOptSparseDriver() | ||
| prob.driver.options["optimizer"] = 'IPOPT' | ||
| prob.driver.opt_settings['tol'] = 1.0E-6 | ||
| prob.driver.opt_settings['mu_init'] = 1e-5 | ||
| prob.driver.opt_settings['max_iter'] = 50 | ||
| prob.driver.opt_settings['print_level'] = 5 | ||
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| aviary_options = self.ode_args['aviary_options'] | ||
| subsystems = self.ode_args['core_subsystems'] | ||
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| traj = FlexibleTraj( | ||
| Phases=phases, | ||
| promote_all_auto_ivc=True, | ||
| traj_final_state_output=[Dynamic.Mission.MASS, | ||
| Dynamic.Mission.DISTANCE, | ||
| Dynamic.Mission.ALTITUDE], | ||
| traj_initial_state_input=[ | ||
| Dynamic.Mission.MASS, | ||
| Dynamic.Mission.DISTANCE, | ||
| Dynamic.Mission.ALTITUDE, | ||
| ], | ||
| ) | ||
| prob.model = AviaryGroup(aviary_options=aviary_options, | ||
| aviary_metadata=BaseMetaData) | ||
| prob.model.add_subsystem( | ||
| 'pre_mission', | ||
| CorePreMission(aviary_options=aviary_options, | ||
| subsystems=subsystems), | ||
| promotes_inputs=['aircraft:*', 'mission:*'], | ||
| promotes_outputs=['aircraft:*', 'mission:*'] | ||
| ) | ||
| prob.model.add_subsystem('traj', traj, | ||
| promotes=['aircraft:*', 'mission:*'] | ||
| ) | ||
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| prob.model.add_subsystem( | ||
| "fuel_obj", | ||
| om.ExecComp( | ||
| "reg_objective = overall_fuel/10000", | ||
| reg_objective={"val": 0.0, "units": "unitless"}, | ||
| overall_fuel={"units": "lbm"}, | ||
| ), | ||
| promotes_inputs=[ | ||
| ("overall_fuel", Mission.Summary.TOTAL_FUEL_MASS), | ||
| ], | ||
| promotes_outputs=[("reg_objective", Mission.Objectives.FUEL)], | ||
| ) | ||
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| prob.model.add_objective(Mission.Objectives.FUEL, ref=1e4) | ||
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| prob.model.add_subsystem( | ||
| 'input_sink', | ||
| VariablesIn(aviary_options=self.aviary_inputs, | ||
| meta_data=BaseMetaData), | ||
| promotes_inputs=['*'], | ||
| promotes_outputs=['*']) | ||
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| with warnings.catch_warnings(): | ||
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| # Set initial default values for all LEAPS aircraft variables. | ||
| set_aviary_initial_values( | ||
| prob.model, self.aviary_inputs, meta_data=BaseMetaData) | ||
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| warnings.simplefilter("ignore", om.PromotionWarning) | ||
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| prob.setup() | ||
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| return prob | ||
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| def run_simulation(self, phases, initial_values: dict): | ||
| prob = self.setup_prob(phases) | ||
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| for key, val in initial_values.items(): | ||
| prob.set_val(key, **val) | ||
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| prob.run_model() | ||
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| distance = prob.get_val('traj.distance_final', units='NM')[0] | ||
| mass = prob.get_val('traj.mass_final', units='lbm')[0] | ||
| alt = prob.get_val('traj.altitude_final', units='ft')[0] | ||
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| final_states = {'distance': distance, 'mass': mass, 'altitude': alt} | ||
| return final_states | ||
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| # def test_takeoff(self): | ||
| # initial_values_takeoff = { | ||
| # "traj.altitude_initial": {'val': 0, 'units': "ft"}, | ||
| # "traj.mass_initial": {'val': 171000, 'units': "lbm"}, | ||
| # "traj.distance_initial": {'val': 0, 'units': "NM"}, | ||
| # "traj.velocity": {'val': .1, 'units': "m/s"}, | ||
| # } | ||
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| # ode_args = self.ode_args | ||
| # ode_args['friction_key'] = Mission.Takeoff.ROLLING_FRICTION_COEFFICIENT | ||
| # brake_release_to_decision = SGMDetailedTakeoff( | ||
| # ode_args, | ||
| # simupy_args=dict(verbosity=Verbosity.DEBUG,) | ||
| # ) | ||
| # brake_release_to_decision.clear_triggers() | ||
| # brake_release_to_decision.add_trigger(Dynamic.Mission.VELOCITY, value=167.85, units='kn') | ||
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| # phases = {'HE': { | ||
| # 'ode': brake_release_to_decision, | ||
| # 'vals_to_set': {} | ||
| # }} | ||
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| # final_states = self.run_simulation(phases, initial_values_takeoff) | ||
| # # assert_near_equal(final_states['altitude'], 500, self.tol) | ||
| # assert_near_equal(final_states['velocity'], 167.85, self.tol) | ||
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| def test_cruise(self): | ||
| initial_values_cruise = { | ||
| "traj.altitude_initial": {'val': 35000, 'units': "ft"}, | ||
| "traj.mass_initial": {'val': 171000, 'units': "lbm"}, | ||
| "traj.distance_initial": {'val': 0, 'units': "NM"}, | ||
| "traj.mach": {'val': .8, 'units': "unitless"}, | ||
| } | ||
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| SGMCruise = SGMHeightEnergy( | ||
| self.ode_args, | ||
| phase_name='cruise', | ||
| simupy_args=dict(verbosity=Verbosity.QUIET,) | ||
| ) | ||
| SGMCruise.triggers[0].value = 160000 | ||
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| phases = {'HE': { | ||
| 'ode': SGMCruise, | ||
| 'vals_to_set': {} | ||
| }} | ||
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| final_states = self.run_simulation(phases, initial_values_cruise) | ||
| assert_near_equal(final_states['mass'], 160000, self.tol) | ||
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| # def test_landing(self): | ||
| # initial_values_landing = { | ||
| # "traj.altitude_initial": {'val': 35000, 'units': "ft"}, | ||
| # "traj.mass_initial": {'val': 171000, 'units': "lbm"}, | ||
| # "traj.distance_initial": {'val': 0, 'units': "NM"}, | ||
| # "traj.velocity": {'val': 300, 'units': "m/s"}, | ||
| # } | ||
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| # ode_args = self.ode_args | ||
| # ode_args['friction_key'] = Mission.Takeoff.BRAKING_FRICTION_COEFFICIENT | ||
| # phases = {'HE': { | ||
| # 'ode': SGMDetailedLanding( | ||
| # ode_args, | ||
| # simupy_args=dict(verbosity=Verbosity.QUIET,) | ||
| # ), | ||
| # 'vals_to_set': {} | ||
| # }} | ||
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| # final_states = self.run_simulation(phases, initial_values_landing) | ||
| # assert_near_equal(final_states['altitude'], 0, self.tol) | ||
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| if __name__ == '__main__': | ||
| unittest.main() |
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