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ostk.astrodynamics.Access

class Access(
self: ostk.astrodynamics.Access,
type: ostk.astrodynamics.Access.Type,
acquisition_of_signal: ostk.physics.time.Instant,
time_of_closest_approach: ostk.physics.time.Instant,
loss_of_signal: ostk.physics.time.Instant,
max_elevation: ostk.physics.unit.Angle,
)

Bases: pybind11_object

Object-to-object visibility

This class encapsulates the concept of visibility access between two trajectories.

Constructs an Access object.

Parameters:

  • type (Access.Type) -- Type of the access (Complete, Partial, Undefined)

  • acquisition_of_signal (Instant) -- The instant when the signal is first acquired

  • time_of_closest_approach (Instant) -- The time of closest approach between objects

  • loss_of_signal (Instant) -- The instant when the signal is lost

  • max_elevation (Angle) -- The maximum elevation angle during the access

Methods

get_acquisition_of_signal

Get the acquisition of signal of the access.

get_duration

Get the duration of the access.

get_interval

Get the interval of the access.

get_loss_of_signal

Get the loss of signal of the access.

get_max_elevation

Get the maximum elevation of the access.

get_time_of_closest_approach

Get the time of closest approach of the access.

get_type

Get the type of the access.

is_complete

Check if the access is complete.

is_defined

Check if the Access object is defined.

string_from_type

Returns a string representation of the Access type.

undefined

Creates an undefined Access object.

class Type(self: ostk.astrodynamics.Access.Type, value: int)

Bases: pybind11_object

Access type.

Members:

Undefined : Undefined

Complete : Complete

Partial : Partial

property name
get_acquisition_of_signal(
self: ostk.astrodynamics.Access,
) → ostk.physics.time.Instant

Get the acquisition of signal of the access.

Returns:

The acquisition of signal of the access.

Return type:

Instant

get_duration(self: ostk.astrodynamics.Access) → ostk.physics.time.Duration

Get the duration of the access.

Returns:

The duration of the access.

Return type:

Duration

get_interval(self: ostk.astrodynamics.Access) → ostk.physics.time.Interval

Get the interval of the access.

Returns:

The interval of the access.

Return type:

Interval

get_loss_of_signal(self: ostk.astrodynamics.Access) → ostk.physics.time.Instant

Get the loss of signal of the access.

Returns:

The loss of signal of the access.

Return type:

Instant

get_max_elevation(self: ostk.astrodynamics.Access) → ostk.physics.unit.Angle

Get the maximum elevation of the access.

Returns:

The maximum elevation of the access.

Return type:

Angle

get_time_of_closest_approach(
self: ostk.astrodynamics.Access,
) → ostk.physics.time.Instant

Get the time of closest approach of the access.

Returns:

The time of closest approach of the access.

Return type:

Instant

get_type(self: ostk.astrodynamics.Access) → ostk.astrodynamics.Access.Type

Get the type of the access.

Returns:

The type of the access.

Return type:

Access.Type

is_complete(self: ostk.astrodynamics.Access) → bool

Check if the access is complete.

Returns:

True if complete, False otherwise.

Return type:

bool

is_defined(self: ostk.astrodynamics.Access) → bool

Check if the Access object is defined.

Returns:

True if defined, False otherwise.

Return type:

bool

static string_from_type(type: ostk.astrodynamics.Access.Type) → ostk.core.type.String

Returns a string representation of the Access type.

Parameters:

type (Access.Type) -- The type of the access.

Returns:

A string representation of the type.

Return type:

str

static undefined() → ostk.astrodynamics.Access

Creates an undefined Access object.

Returns:

An undefined Access object.

Return type:

Access

\ No newline at end of file + ostk.astrodynamics.Access — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.Access

class Access(
self: ostk.astrodynamics.Access,
type: ostk.astrodynamics.Access.Type,
acquisition_of_signal: ostk.physics.time.Instant,
time_of_closest_approach: ostk.physics.time.Instant,
loss_of_signal: ostk.physics.time.Instant,
max_elevation: ostk.physics.unit.Angle,
)

Bases: pybind11_object

Object-to-object visibility

This class encapsulates the concept of visibility access between two trajectories.

Constructs an Access object.

Parameters:

  • type (Access.Type) -- Type of the access (Complete, Partial, Undefined)

  • acquisition_of_signal (Instant) -- The instant when the signal is first acquired

  • time_of_closest_approach (Instant) -- The time of closest approach between objects

  • loss_of_signal (Instant) -- The instant when the signal is lost

  • max_elevation (Angle) -- The maximum elevation angle during the access

Methods

get_acquisition_of_signal

Get the acquisition of signal of the access.

get_duration

Get the duration of the access.

get_interval

Get the interval of the access.

get_loss_of_signal

Get the loss of signal of the access.

get_max_elevation

Get the maximum elevation of the access.

get_time_of_closest_approach

Get the time of closest approach of the access.

get_type

Get the type of the access.

is_complete

Check if the access is complete.

is_defined

Check if the Access object is defined.

string_from_type

Returns a string representation of the Access type.

undefined

Creates an undefined Access object.

class Type(self: ostk.astrodynamics.Access.Type, value: int)

Bases: pybind11_object

Access type.

Members:

Undefined : Undefined

Complete : Complete

Partial : Partial

property name
get_acquisition_of_signal(
self: ostk.astrodynamics.Access,
) → ostk.physics.time.Instant

Get the acquisition of signal of the access.

Returns:

The acquisition of signal of the access.

Return type:

Instant

get_duration(self: ostk.astrodynamics.Access) → ostk.physics.time.Duration

Get the duration of the access.

Returns:

The duration of the access.

Return type:

Duration

get_interval(self: ostk.astrodynamics.Access) → ostk.physics.time.Interval

Get the interval of the access.

Returns:

The interval of the access.

Return type:

Interval

get_loss_of_signal(self: ostk.astrodynamics.Access) → ostk.physics.time.Instant

Get the loss of signal of the access.

Returns:

The loss of signal of the access.

Return type:

Instant

get_max_elevation(self: ostk.astrodynamics.Access) → ostk.physics.unit.Angle

Get the maximum elevation of the access.

Returns:

The maximum elevation of the access.

Return type:

Angle

get_time_of_closest_approach(
self: ostk.astrodynamics.Access,
) → ostk.physics.time.Instant

Get the time of closest approach of the access.

Returns:

The time of closest approach of the access.

Return type:

Instant

get_type(self: ostk.astrodynamics.Access) → ostk.astrodynamics.Access.Type

Get the type of the access.

Returns:

The type of the access.

Return type:

Access.Type

is_complete(self: ostk.astrodynamics.Access) → bool

Check if the access is complete.

Returns:

True if complete, False otherwise.

Return type:

bool

is_defined(self: ostk.astrodynamics.Access) → bool

Check if the Access object is defined.

Returns:

True if defined, False otherwise.

Return type:

bool

static string_from_type(type: ostk.astrodynamics.Access.Type) → ostk.core.type.String

Returns a string representation of the Access type.

Parameters:

type (Access.Type) -- The type of the access.

Returns:

A string representation of the type.

Return type:

str

static undefined() → ostk.astrodynamics.Access

Creates an undefined Access object.

Returns:

An undefined Access object.

Return type:

Access

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.Dynamics.html b/_build/html/_autosummary/ostk.astrodynamics.Dynamics.html index 96664f551..e4e817df9 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.Dynamics.html +++ b/_build/html/_autosummary/ostk.astrodynamics.Dynamics.html @@ -1 +1 @@ - ostk.astrodynamics.Dynamics — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.Dynamics

class Dynamics(self: ostk.astrodynamics.Dynamics, name: ostk.core.type.String)

Bases: pybind11_object

Abstract interface class for dynamics.

Can inherit and provide the virtual methods:

  • is_defined

  • get_read_coordinate_subsets

  • get_write_coordinate_subsets

  • compute_contribution

to create a custom dynamics class.

Construct a new Dynamics object.

Parameters:

name (str) -- The name of the dynamics.

Returns:

The new Dynamics object.

Return type:

dynamics (Dynamics)

Methods

compute_contribution

Compute the contribution of the dynamics at a given instant.

from_environment

Create a list of Dynamics objects from an environment.

get_name

Get the name of the dynamics.

get_read_coordinate_subsets

Get the coordinate subsets that the dynamics reads.

get_write_coordinate_subsets

Get the coordinate subsets that the dynamics writes.

is_defined

Check if the dynamics is defined.

compute_contribution(
self: ostk.astrodynamics.Dynamics,
instant: ostk.physics.time.Instant,
state_vector: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, 1]]

Compute the contribution of the dynamics at a given instant.

Parameters:

  • instant (Instant) -- The instant at which to compute the contribution.

  • state_vector (numpy.ndarray) -- The state vector at the instant.

  • frame (Frame) -- The reference frame in which to compute the contribution.

Returns:

The contribution of the dynamics at the instant.

Return type:

contribution (numpy.ndarray)

static from_environment(
environment: ostk.physics.Environment,
) → List[ostk.astrodynamics.Dynamics]

Create a list of Dynamics objects from an environment.

Parameters:

environment (Environment) -- The environment to create the dynamics from.

Returns:

The list of Dynamics objects created from the environment.

Return type:

dynamics (list[Dynamics])

get_name(self: ostk.astrodynamics.Dynamics) → ostk.core.type.String

Get the name of the dynamics.

Returns:

The name of the dynamics.

Return type:

name (str)

get_read_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics reads.

Returns:

The coordinate subsets that the dynamics reads.

Return type:

read_coordinate_subsets (Array<CoordinateSubset>)

get_write_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics writes.

Returns:

The coordinate subsets that the dynamics writes.

Return type:

write_coordinate_subsets (Array<CoordinateSubset>)

is_defined(self: ostk.astrodynamics.Dynamics) → bool

Check if the dynamics is defined.

Returns:

True if the dynamics is defined, False otherwise.

Return type:

is_defined (bool)

\ No newline at end of file + ostk.astrodynamics.Dynamics — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.Dynamics

class Dynamics(self: ostk.astrodynamics.Dynamics, name: ostk.core.type.String)

Bases: pybind11_object

Abstract interface class for dynamics.

Can inherit and provide the virtual methods:

  • is_defined

  • get_read_coordinate_subsets

  • get_write_coordinate_subsets

  • compute_contribution

to create a custom dynamics class.

Construct a new Dynamics object.

Parameters:

name (str) -- The name of the dynamics.

Returns:

The new Dynamics object.

Return type:

dynamics (Dynamics)

Methods

compute_contribution

Compute the contribution of the dynamics at a given instant.

from_environment

Create a list of Dynamics objects from an environment.

get_name

Get the name of the dynamics.

get_read_coordinate_subsets

Get the coordinate subsets that the dynamics reads.

get_write_coordinate_subsets

Get the coordinate subsets that the dynamics writes.

is_defined

Check if the dynamics is defined.

compute_contribution(
self: ostk.astrodynamics.Dynamics,
instant: ostk.physics.time.Instant,
state_vector: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, 1]]

Compute the contribution of the dynamics at a given instant.

Parameters:

  • instant (Instant) -- The instant at which to compute the contribution.

  • state_vector (numpy.ndarray) -- The state vector at the instant.

  • frame (Frame) -- The reference frame in which to compute the contribution.

Returns:

The contribution of the dynamics at the instant.

Return type:

contribution (numpy.ndarray)

static from_environment(
environment: ostk.physics.Environment,
) → List[ostk.astrodynamics.Dynamics]

Create a list of Dynamics objects from an environment.

Parameters:

environment (Environment) -- The environment to create the dynamics from.

Returns:

The list of Dynamics objects created from the environment.

Return type:

dynamics (list[Dynamics])

get_name(self: ostk.astrodynamics.Dynamics) → ostk.core.type.String

Get the name of the dynamics.

Returns:

The name of the dynamics.

Return type:

name (str)

get_read_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics reads.

Returns:

The coordinate subsets that the dynamics reads.

Return type:

read_coordinate_subsets (Array<CoordinateSubset>)

get_write_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics writes.

Returns:

The coordinate subsets that the dynamics writes.

Return type:

write_coordinate_subsets (Array<CoordinateSubset>)

is_defined(self: ostk.astrodynamics.Dynamics) → bool

Check if the dynamics is defined.

Returns:

True if the dynamics is defined, False otherwise.

Return type:

is_defined (bool)

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.GuidanceLaw.html b/_build/html/_autosummary/ostk.astrodynamics.GuidanceLaw.html index bcd9908cb..fa88f6748 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.GuidanceLaw.html +++ b/_build/html/_autosummary/ostk.astrodynamics.GuidanceLaw.html @@ -1 +1 @@ - ostk.astrodynamics.GuidanceLaw — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.GuidanceLaw

class GuidanceLaw(self: ostk.astrodynamics.GuidanceLaw, name: ostk.core.type.String)

Bases: pybind11_object

Guidance law base class.

A guidance law is a mathematical model that computes the acceleration based on specific guidance law logic.

Constructor.

Parameters:

name (str) -- The name of the guidance law.

Methods

calculate_thrust_acceleration_at

Compute the acceleration.

get_name

Get the name of the guidance law.

calculate_thrust_acceleration_at(
self: ostk.astrodynamics.GuidanceLaw,
instant: ostk.physics.time.Instant,
position_coordinates: numpy.ndarray[numpy.float64[3, 1]],
velocity_coordinates: numpy.ndarray[numpy.float64[3, 1]],
thrust_acceleration: ostk.core.type.Real,
output_frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[3, 1]]

Compute the acceleration.

Parameters:

  • instant (Instant) -- Instant of computation.

  • position_coordinates (np.array) -- Position coordinates.

  • velocity_coordinates (np.array) -- Velocity coordinates.

  • thrust_acceleration (float) -- Thrust acceleration magnitude.

  • output_frame (Frame) -- The frame the acceleration is expressed in.

Returns:

The acceleration.

Return type:

np.array

get_name(self: ostk.astrodynamics.GuidanceLaw) → ostk.core.type.String

Get the name of the guidance law.

Returns:

The name of the guidance law.

Return type:

str

\ No newline at end of file + ostk.astrodynamics.GuidanceLaw — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.GuidanceLaw

class GuidanceLaw(self: ostk.astrodynamics.GuidanceLaw, name: ostk.core.type.String)

Bases: pybind11_object

Guidance law base class.

A guidance law is a mathematical model that computes the acceleration based on specific guidance law logic.

Constructor.

Parameters:

name (str) -- The name of the guidance law.

Methods

calculate_thrust_acceleration_at

Compute the acceleration.

get_name

Get the name of the guidance law.

calculate_thrust_acceleration_at(
self: ostk.astrodynamics.GuidanceLaw,
instant: ostk.physics.time.Instant,
position_coordinates: numpy.ndarray[numpy.float64[3, 1]],
velocity_coordinates: numpy.ndarray[numpy.float64[3, 1]],
thrust_acceleration: ostk.core.type.Real,
output_frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[3, 1]]

Compute the acceleration.

Parameters:

  • instant (Instant) -- Instant of computation.

  • position_coordinates (np.array) -- Position coordinates.

  • velocity_coordinates (np.array) -- Velocity coordinates.

  • thrust_acceleration (float) -- Thrust acceleration magnitude.

  • output_frame (Frame) -- The frame the acceleration is expressed in.

Returns:

The acceleration.

Return type:

np.array

get_name(self: ostk.astrodynamics.GuidanceLaw) → ostk.core.type.String

Get the name of the guidance law.

Returns:

The name of the guidance law.

Return type:

str

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.Trajectory.html b/_build/html/_autosummary/ostk.astrodynamics.Trajectory.html index 84bf0b5f8..a94dcfa15 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.Trajectory.html +++ b/_build/html/_autosummary/ostk.astrodynamics.Trajectory.html @@ -1 +1 @@ - ostk.astrodynamics.Trajectory — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.Trajectory

class Trajectory(*args, **kwargs)

Bases: pybind11_object

Path followed by an object through space as a function of time.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.Trajectory, model: ostk::astrodynamics::trajectory::Model) -> None

    Construct a Trajectory object from a model.

    Args:

    model (trajectory.Model): The model of the trajectory.

    Returns:

    Trajectory: The Trajectory object.

  2. __init__(self: ostk.astrodynamics.Trajectory, states: List[ostk::astrodynamics::trajectory::State]) -> None

    Construct a Trajectory object from an array of states.

    Args:

    states (list[State]): The states of the trajectory.

    Returns:

    Trajectory: The Trajectory object.

Methods

get_state_at

Get the state of the trajectory at a given instant.

get_states_at

Get the states of the trajectory at a given set of instants.

is_defined

Check if the trajectory is defined.

position

Create a Trajectory object representing a position.

undefined

Create an undefined Trajectory object.

get_state_at(
self: ostk.astrodynamics.Trajectory,
instant: ostk.physics.time.Instant,
) → ostk::astrodynamics::trajectory::State

Get the state of the trajectory at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state of the trajectory at the given instant.

Return type:

State

get_states_at(
self: ostk.astrodynamics.Trajectory,
instants: List[ostk.physics.time.Instant],
) → List[ostk::astrodynamics::trajectory::State]

Get the states of the trajectory at a given set of instants. It can be more performant than looping calculate_state_at for multiple instants.

Parameters:

instants (list[Instant]) -- The instants.

Returns:

The states of the trajectory at the given instants.

Return type:

list[State]

is_defined(self: ostk.astrodynamics.Trajectory) → bool

Check if the trajectory is defined.

Returns:

True if the trajectory is defined, False otherwise.

Return type:

bool

static position(
position: ostk.physics.coordinate.Position,
) → ostk.astrodynamics.Trajectory

Create a Trajectory object representing a position.

Parameters:

position (Position) -- The position.

Returns:

The Trajectory object representing the position.

Return type:

Trajectory

static undefined() → ostk.astrodynamics.Trajectory

Create an undefined Trajectory object.

Returns:

The undefined Trajectory object.

Return type:

Trajectory

\ No newline at end of file + ostk.astrodynamics.Trajectory — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.Trajectory

class Trajectory(*args, **kwargs)

Bases: pybind11_object

Path followed by an object through space as a function of time.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.Trajectory, model: ostk::astrodynamics::trajectory::Model) -> None

    Construct a Trajectory object from a model.

    Args:

    model (trajectory.Model): The model of the trajectory.

    Returns:

    Trajectory: The Trajectory object.

  2. __init__(self: ostk.astrodynamics.Trajectory, states: List[ostk::astrodynamics::trajectory::State]) -> None

    Construct a Trajectory object from an array of states.

    Args:

    states (list[State]): The states of the trajectory.

    Returns:

    Trajectory: The Trajectory object.

Methods

get_state_at

Get the state of the trajectory at a given instant.

get_states_at

Get the states of the trajectory at a given set of instants.

is_defined

Check if the trajectory is defined.

position

Create a Trajectory object representing a position.

undefined

Create an undefined Trajectory object.

get_state_at(
self: ostk.astrodynamics.Trajectory,
instant: ostk.physics.time.Instant,
) → ostk::astrodynamics::trajectory::State

Get the state of the trajectory at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state of the trajectory at the given instant.

Return type:

State

get_states_at(
self: ostk.astrodynamics.Trajectory,
instants: List[ostk.physics.time.Instant],
) → List[ostk::astrodynamics::trajectory::State]

Get the states of the trajectory at a given set of instants. It can be more performant than looping calculate_state_at for multiple instants.

Parameters:

instants (list[Instant]) -- The instants.

Returns:

The states of the trajectory at the given instants.

Return type:

list[State]

is_defined(self: ostk.astrodynamics.Trajectory) → bool

Check if the trajectory is defined.

Returns:

True if the trajectory is defined, False otherwise.

Return type:

bool

static position(
position: ostk.physics.coordinate.Position,
) → ostk.astrodynamics.Trajectory

Create a Trajectory object representing a position.

Parameters:

position (Position) -- The position.

Returns:

The Trajectory object representing the position.

Return type:

Trajectory

static undefined() → ostk.astrodynamics.Trajectory

Create an undefined Trajectory object.

Returns:

The undefined Trajectory object.

Return type:

Trajectory

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.access.Generator.html b/_build/html/_autosummary/ostk.astrodynamics.access.Generator.html index 387725fe9..1c8687334 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.access.Generator.html +++ b/_build/html/_autosummary/ostk.astrodynamics.access.Generator.html @@ -1 +1 @@ - ostk.astrodynamics.access.Generator — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.access.Generator

class Generator(
self: ostk.astrodynamics.access.Generator,
environment: ostk.physics.Environment,
aer_filter: Callable[[ostk.physics.coordinate.spherical.AER], bool] = None,
access_filter: Callable[[ostk.astrodynamics.Access], bool] = None,
state_filter: Callable[[ostk.astrodynamics.trajectory.State, ostk.astrodynamics.trajectory.State], bool] = None,
step: ostk.physics.time.Duration = Duration.minutes(1.0),
tolerance: ostk.physics.time.Duration = Duration.microseconds(1.0),
)

Bases: pybind11_object

An access generator.

Constructor.

Parameters:

  • environment (Environment) -- The environment.

  • aer_filter (function) -- The AER filter.

  • access_filter (function) -- The access filter.

  • state_filter (function) -- The state filter.

  • step (Duration) -- The step.

  • tolerance (Duration) -- The tolerance.

Methods

aer_mask

Create an AER generator with a mask.

aer_ranges

Create an AER generator with ranges.

compute_accesses

Compute the accesses.

get_access_filter

Get the access filter.

get_aer_filter

Get the AER filter.

get_condition_function

Get the condition function.

get_state_filter

Get the state filter.

get_step

Get the step.

get_tolerance

Get the tolerance.

is_defined

Check if the generator is defined.

set_access_filter

Set the access filter.

set_aer_filter

Set the AER filter.

set_state_filter

Set the state filter.

set_step

Set the step.

set_tolerance

Set the tolerance.

undefined

Get an undefined generator.

static aer_mask(
azimuth_elevation_mask: Dict[ostk.core.type.Real, ostk.core.type.Real],
range_range: ostk.mathematics.object.RealInterval,
environment: ostk.physics.Environment,
) → ostk.astrodynamics.access.Generator

Create an AER generator with a mask.

Parameters:

  • azimuth_elevation_mask (Interval) -- The azimuth-elevation mask.

  • range_range (Interval) -- The range range.

  • environment (Environment) -- The environment.

Returns:

The AER generator.

Return type:

Generator

static aer_ranges(
azimuth_range: ostk.mathematics.object.RealInterval,
elevation_range: ostk.mathematics.object.RealInterval,
range_range: ostk.mathematics.object.RealInterval,
environment: ostk.physics.Environment,
) → ostk.astrodynamics.access.Generator

Create an AER generator with ranges.

Parameters:

  • azimuth_range (Interval) -- The azimuth range.

  • elevation_range (Interval) -- The elevation range.

  • range_range (Interval) -- The range range.

  • environment (Environment) -- The environment.

Returns:

The AER generator.

Return type:

Generator

compute_accesses(
self: ostk.astrodynamics.access.Generator,
interval: ostk.physics.time.Interval,
from_trajectory: ostk.astrodynamics.Trajectory,
to_trajectory: ostk.astrodynamics.Trajectory,
) → List[ostk.astrodynamics.Access]

Compute the accesses.

Parameters:

  • interval (Interval) -- The interval.

  • from_trajectory (State) -- The state at the start of the interval.

  • to_trajectory (State) -- The state at the end of the interval.

Returns:

The accesses.

Return type:

Accesses

get_access_filter(
self: ostk.astrodynamics.access.Generator,
) → Callable[[ostk.astrodynamics.Access], bool]

Get the access filter.

Returns:

The access filter.

Return type:

function

get_aer_filter(
self: ostk.astrodynamics.access.Generator,
) → Callable[[ostk.physics.coordinate.spherical.AER], bool]

Get the AER filter.

Returns:

The AER filter.

Return type:

function

get_condition_function(
self: ostk.astrodynamics.access.Generator,
from_trajectory: ostk.astrodynamics.Trajectory,
to_trajectory: ostk.astrodynamics.Trajectory,
) → Callable[[ostk.physics.time.Instant], bool]

Get the condition function.

Parameters:

  • from_trajectory (State) -- The state at the start of the interval.

  • to_trajectory (State) -- The state at the end of the interval.

Returns:

The condition function.

Return type:

function

get_state_filter(
self: ostk.astrodynamics.access.Generator,
) → Callable[[ostk.astrodynamics.trajectory.State, ostk.astrodynamics.trajectory.State], bool]

Get the state filter.

Returns:

The state filter.

Return type:

function

get_step(
self: ostk.astrodynamics.access.Generator,
) → ostk.physics.time.Duration

Get the step.

Returns:

The step.

Return type:

Duration

get_tolerance(
self: ostk.astrodynamics.access.Generator,
) → ostk.physics.time.Duration

Get the tolerance.

Returns:

The tolerance.

Return type:

Duration

is_defined(self: ostk.astrodynamics.access.Generator) → bool

Check if the generator is defined.

Returns:

True if the generator is defined, False otherwise.

Return type:

bool

set_access_filter(
self: ostk.astrodynamics.access.Generator,
access_filter: Callable[[ostk.astrodynamics.Access], bool],
) → None

Set the access filter.

Parameters:

access_filter (function) -- The access filter.

set_aer_filter(
self: ostk.astrodynamics.access.Generator,
aer_filter: Callable[[ostk.physics.coordinate.spherical.AER], bool],
) → None

Set the AER filter.

Parameters:

aer_filter (function) -- The AER filter.

set_state_filter(
self: ostk.astrodynamics.access.Generator,
state_filter: Callable[[ostk.astrodynamics.trajectory.State, ostk.astrodynamics.trajectory.State], bool],
) → None

Set the state filter.

Parameters:

state_filter (function) -- The state filter.

set_step(
self: ostk.astrodynamics.access.Generator,
step: ostk.physics.time.Duration,
) → None

Set the step.

Parameters:

step (Duration) -- The step.

set_tolerance(
self: ostk.astrodynamics.access.Generator,
tolerance: ostk.physics.time.Duration,
) → None

Set the tolerance.

Parameters:

tolerance (Duration) -- The tolerance.

static undefined() → ostk.astrodynamics.access.Generator

Get an undefined generator.

Returns:

An undefined generator.

Return type:

Generator

\ No newline at end of file + ostk.astrodynamics.access.Generator — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.access.Generator

class Generator(
self: ostk.astrodynamics.access.Generator,
environment: ostk.physics.Environment,
aer_filter: Callable[[ostk.physics.coordinate.spherical.AER], bool] = None,
access_filter: Callable[[ostk.astrodynamics.Access], bool] = None,
state_filter: Callable[[ostk.astrodynamics.trajectory.State, ostk.astrodynamics.trajectory.State], bool] = None,
step: ostk.physics.time.Duration = Duration.minutes(1.0),
tolerance: ostk.physics.time.Duration = Duration.microseconds(1.0),
)

Bases: pybind11_object

An access generator.

Constructor.

Parameters:

  • environment (Environment) -- The environment.

  • aer_filter (function) -- The AER filter.

  • access_filter (function) -- The access filter.

  • state_filter (function) -- The state filter.

  • step (Duration) -- The step.

  • tolerance (Duration) -- The tolerance.

Methods

aer_mask

Create an AER generator with a mask.

aer_ranges

Create an AER generator with ranges.

compute_accesses

Compute the accesses.

get_access_filter

Get the access filter.

get_aer_filter

Get the AER filter.

get_condition_function

Get the condition function.

get_state_filter

Get the state filter.

get_step

Get the step.

get_tolerance

Get the tolerance.

is_defined

Check if the generator is defined.

set_access_filter

Set the access filter.

set_aer_filter

Set the AER filter.

set_state_filter

Set the state filter.

set_step

Set the step.

set_tolerance

Set the tolerance.

undefined

Get an undefined generator.

static aer_mask(
azimuth_elevation_mask: Dict[ostk.core.type.Real, ostk.core.type.Real],
range_range: ostk.mathematics.object.RealInterval,
environment: ostk.physics.Environment,
) → ostk.astrodynamics.access.Generator

Create an AER generator with a mask.

Parameters:

  • azimuth_elevation_mask (Interval) -- The azimuth-elevation mask.

  • range_range (Interval) -- The range range.

  • environment (Environment) -- The environment.

Returns:

The AER generator.

Return type:

Generator

static aer_ranges(
azimuth_range: ostk.mathematics.object.RealInterval,
elevation_range: ostk.mathematics.object.RealInterval,
range_range: ostk.mathematics.object.RealInterval,
environment: ostk.physics.Environment,
) → ostk.astrodynamics.access.Generator

Create an AER generator with ranges.

Parameters:

  • azimuth_range (Interval) -- The azimuth range.

  • elevation_range (Interval) -- The elevation range.

  • range_range (Interval) -- The range range.

  • environment (Environment) -- The environment.

Returns:

The AER generator.

Return type:

Generator

compute_accesses(
self: ostk.astrodynamics.access.Generator,
interval: ostk.physics.time.Interval,
from_trajectory: ostk.astrodynamics.Trajectory,
to_trajectory: ostk.astrodynamics.Trajectory,
) → List[ostk.astrodynamics.Access]

Compute the accesses.

Parameters:

  • interval (Interval) -- The interval.

  • from_trajectory (State) -- The state at the start of the interval.

  • to_trajectory (State) -- The state at the end of the interval.

Returns:

The accesses.

Return type:

Accesses

get_access_filter(
self: ostk.astrodynamics.access.Generator,
) → Callable[[ostk.astrodynamics.Access], bool]

Get the access filter.

Returns:

The access filter.

Return type:

function

get_aer_filter(
self: ostk.astrodynamics.access.Generator,
) → Callable[[ostk.physics.coordinate.spherical.AER], bool]

Get the AER filter.

Returns:

The AER filter.

Return type:

function

get_condition_function(
self: ostk.astrodynamics.access.Generator,
from_trajectory: ostk.astrodynamics.Trajectory,
to_trajectory: ostk.astrodynamics.Trajectory,
) → Callable[[ostk.physics.time.Instant], bool]

Get the condition function.

Parameters:

  • from_trajectory (State) -- The state at the start of the interval.

  • to_trajectory (State) -- The state at the end of the interval.

Returns:

The condition function.

Return type:

function

get_state_filter(
self: ostk.astrodynamics.access.Generator,
) → Callable[[ostk.astrodynamics.trajectory.State, ostk.astrodynamics.trajectory.State], bool]

Get the state filter.

Returns:

The state filter.

Return type:

function

get_step(
self: ostk.astrodynamics.access.Generator,
) → ostk.physics.time.Duration

Get the step.

Returns:

The step.

Return type:

Duration

get_tolerance(
self: ostk.astrodynamics.access.Generator,
) → ostk.physics.time.Duration

Get the tolerance.

Returns:

The tolerance.

Return type:

Duration

is_defined(self: ostk.astrodynamics.access.Generator) → bool

Check if the generator is defined.

Returns:

True if the generator is defined, False otherwise.

Return type:

bool

set_access_filter(
self: ostk.astrodynamics.access.Generator,
access_filter: Callable[[ostk.astrodynamics.Access], bool],
) → None

Set the access filter.

Parameters:

access_filter (function) -- The access filter.

set_aer_filter(
self: ostk.astrodynamics.access.Generator,
aer_filter: Callable[[ostk.physics.coordinate.spherical.AER], bool],
) → None

Set the AER filter.

Parameters:

aer_filter (function) -- The AER filter.

set_state_filter(
self: ostk.astrodynamics.access.Generator,
state_filter: Callable[[ostk.astrodynamics.trajectory.State, ostk.astrodynamics.trajectory.State], bool],
) → None

Set the state filter.

Parameters:

state_filter (function) -- The state filter.

set_step(
self: ostk.astrodynamics.access.Generator,
step: ostk.physics.time.Duration,
) → None

Set the step.

Parameters:

step (Duration) -- The step.

set_tolerance(
self: ostk.astrodynamics.access.Generator,
tolerance: ostk.physics.time.Duration,
) → None

Set the tolerance.

Parameters:

tolerance (Duration) -- The tolerance.

static undefined() → ostk.astrodynamics.access.Generator

Get an undefined generator.

Returns:

An undefined generator.

Return type:

Generator

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.conjunction.message.ccsds.CDM.html b/_build/html/_autosummary/ostk.astrodynamics.conjunction.message.ccsds.CDM.html index e43b52f1f..486a6baa3 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.conjunction.message.ccsds.CDM.html +++ b/_build/html/_autosummary/ostk.astrodynamics.conjunction.message.ccsds.CDM.html @@ -1 +1 @@ - ostk.astrodynamics.conjunction.message.ccsds.CDM — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.conjunction.message.ccsds.CDM

class CDM(self: ostk.astrodynamics.conjunction.message.ccsds.CDM, header: ostk::astrodynamics::conjunction::message::ccsds::CDM::Header, relative_metadata: ostk::astrodynamics::conjunction::message::ccsds::CDM::RelativeMetadata, objects_metadata_array: List[ostk::astrodynamics::conjunction::message::ccsds::CDM::Metadata], objects_data_array: List[ostk::astrodynamics::conjunction::message::ccsds::CDM::Data])

Bases: pybind11_object

Conjunction Data Message.

Ref: https://public.ccsds.org/Pubs/508x0b1e2s.pdf

Constructor.

Parameters:

  • header (CDM::Header) -- The CDM header.

  • relative_metadata (CDM::RelativeMetadata) -- The relative metadata.

  • objects_metadata_array (Array<CDM::Metadata>) -- The objects metadata array.

  • objects_data_array (Array<CDM::Data>) -- The objects data array.

Methods

dictionary

Get the CDM dictionary.

get_ccsds_cdm_version

Get the CCSDS CDM version.

get_collision_probability

Get the collision probability.

get_collision_probability_method

Get the collision probability method.

get_creation_instant

Get the creation instant.

get_data_array

Get the objects data array.

get_header

Get the CDM header.

get_message_for

Get the message for.

get_message_id

Get the message ID.

get_metadata_array

Get the objects metadata array.

get_miss_distance

Get the miss distance.

get_object_data_at

Get the object data at the specified index.

get_object_metadata_at

Get the object metadata at the specified index.

get_originator

Get the originator.

get_relative_metadata

Get the relative metadata.

get_relative_position

Get the relative position.

get_relative_velocity

Get the relative velocity.

get_time_of_closest_approach

Get the time of closest approach.

is_defined

Check if the CDM is defined.

load

Load a CDM from a file.

object_type_from_string

Get the object type from a string.

parse

Parse a CDM from a string.

undefined

Get an undefined CDM.

class Data

Bases: pybind11_object

Conjunction Data Message data.

Ref: https://public.ccsds.org/Pubs/508x0b1e2s.pdf

__init__(self: ostk.astrodynamics.conjunction.message.ccsds.CDM.Data, time_last_observation_start: ostk.physics.time.Instant, time_last_observation_end: ostk.physics.time.Instant, recommended_od_span: ostk.physics.time.Duration, actual_od_span: ostk.physics.time.Duration, observations_available: ostk.core.type.Integer, observations_used: ostk.core.type.Integer, tracks_available: ostk.core.type.Integer, tracks_used: ostk.core.type.Integer, residuals_accepted: ostk.core.type.Real, weighted_rms: ostk.core.type.Real, area_pc: ostk.core.type.Real, area_drag: ostk.core.type.Real, area_srp: ostk.core.type.Real, mass: ostk.physics.unit.Mass, cd_area_over_mass: ostk.core.type.Real, cr_area_over_mass: ostk.core.type.Real, thrust_acceleration: ostk.core.type.Real, sedr: ostk.core.type.Real, state: ostk.astrodynamics.trajectory.State = undefined, covariance_matrix: numpy.ndarray[numpy.float64[m, n]] = array([[0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.]])) -> None

Constructor.

Args:

time_last_observation_start (Instant): The time of the last observation start. time_last_observation_end (Instant): The time of the last observation end. recommended_od_span (Duration): The recommended OD span. actual_od_span (Duration): The actual OD span. observations_available (int): The number of observations available. observations_used (int): The number of observations used. tracks_available (int): The number of tracks available. tracks_used (int): The number of tracks used. residuals_accepted (float): The residuals accepted. weighted_rms (float): The weighted RMS. area_pc (float): The area PC. area_drag (float): The area drag. area_srp (float): The area SRP. mass (Mass): The mass. cd_area_over_mass (float): The CD area over mass. cr_area_over_mass (float): The CR area over mass. thrust_acceleration (float): The thrust acceleration. sedr (float): The SEDR. state (State): The state. covariance_matrix (MatrixXd): The covariance matrix.

property actual_od_span

The actual OD span.

property area_drag

The area drag.

property area_pc

The area PC.

property area_srp

The area SRP.

property cd_area_over_mass

The CD area over mass.

property covariance_matrix

The covariance matrix.

property cr_area_over_mass

The CR area over mass.

property mass

The mass.

property observations_available

The number of observations available.

property observations_used

The number of observations used.

property recommended_od_span

The recommended OD span.

property residuals_accepted

The residuals accepted.

property sedr

The SEDR.

property state

The state.

property thrust_acceleration

The thrust acceleration.

property time_last_observation_end

The time of the last observation end.

property time_last_observation_start

The time of the last observation start.

property tracks_available

The number of tracks available.

property tracks_used

The number of tracks used.

property weighted_rms

The weighted RMS.

class Header(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM.Header,
ccsds_cdm_version: ostk.core.type.String,
comment: ostk.core.type.String =,
creation_date: ostk.physics.time.Instant,
originator: ostk.core.type.String,
message_for: ostk.core.type.String =,
message_id: ostk.core.type.String,
)

Bases: pybind11_object

Conjunction Data Message header.

Ref: https://public.ccsds.org/Pubs/508x0b1e2s.pdf

Constructor.

Parameters:

  • ccsds_cdm_version (str) -- The CCSDS CDM version.

  • comment (str) -- The comment.

  • creation_date (Instant) -- The creation date.

  • originator (str) -- The originator.

  • message_for (str) -- The message for.

  • message_id (str) -- The message ID.

property ccsds_cdm_version

The CCSDS CDM version.

property comment

The comment.

property creation_date

The creation date.

property message_for

The message for.

property message_id

The message ID.

property originator

The originator.

class Metadata(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM.Metadata,
comment: ostk.core.type.String =,
object: ostk.core.type.String,
object_designator: ostk.core.type.Integer,
catalog_name: ostk.core.type.String =,
object_name: ostk.core.type.String,
international_designator: ostk.core.type.String,
object_type: ostk.astrodynamics.conjunction.message.ccsds.CDM.ObjectType,
operator_contact_position: ostk.core.type.String =,
operator_organization: ostk.core.type.String =,
operator_phone: ostk.core.type.String =,
operator_email: ostk.core.type.String =,
ephemeris_name: ostk.core.type.String,
covariance_method: ostk.core.type.String,
maneuverable: ostk.core.type.String,
orbit_center: ostk.core.type.String =,
reference_frame: ostk.core.type.String,
gravity_model: ostk.core.type.String =,
atmospheric_model: ostk.core.type.String =,
n_body_perturbations: ostk.core.type.String =,
solar_radiation_pressure: bool = False,
earth_tides: bool = False,
in_track_thrust: bool = False,
)

Bases: pybind11_object

Conjunction Data Message metadata.

Ref: https://public.ccsds.org/Pubs/508x0b1e2s.pdf

Constructor.

Parameters:

  • comment (str) -- The comment.

  • object (str) -- The object.

  • object_designator (int) -- The object designator.

  • catalog_name (str) -- The catalog name.

  • object_name (str) -- The object name.

  • international_designator (str) -- The international designator.

  • object_type (ObjectType) -- The object type.

  • operator_contact_position (str) -- The operator contact position.

  • operator_organization (str) -- The operator organization.

  • operator_phone (str) -- The operator phone.

  • operator_email (str) -- The operator email.

  • ephemeris_name (str) -- The ephemeris name.

  • covariance_method (str) -- The covariance method.

  • maneuverable (str) -- The maneuverable.

  • orbit_center (str) -- The orbit center.

  • reference_frame (str) -- The reference frame.

  • gravity_model (str) -- The gravity model.

  • atmospheric_model (str) -- The atmospheric model.

  • n_body_perturbations (str) -- The n-body perturbations.

  • solar_radiation_pressure (bool) -- The solar radiation pressure.

  • earth_tides (bool) -- The earth tides.

  • in_track_thrust (bool) -- The in-track thrust.

property atmospheric_model

The atmospheric model.

property catalog_name

The catalog name.

property comment

The comment.

property covariance_method

The covariance method.

property earth_tides

The earth tides.

property ephemeris_name

The ephemeris name.

property gravity_model

The gravity model.

property in_track_thrust

The in-track thrust.

property international_designator

The international designator.

property maneuverable

The maneuverable.

property n_body_perturbations

The n-body perturbations.

property object

The object.

property object_designator

The object designator.

property object_name

The object name.

property object_type

The object type.

property operator_contact_position

The operator contact position.

property operator_email

The operator email.

property operator_organization

The operator organization.

property operator_phone

The operator phone.

property orbit_center

The orbit center.

property reference_frame

The reference frame.

property solar_radiation_pressure

The solar radiation pressure.

class ObjectType(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM.ObjectType,
value: int,
)

Bases: pybind11_object

Object type.

Members:

Payload : Payload

RocketBody : Rocket Body

Debris : Debris

Unknown : Unknown

Other : Other

property name
class RelativeMetadata(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM.RelativeMetadata,
comment: ostk.core.type.String =,
time_of_closest_approach: ostk.physics.time.Instant,
miss_distance: ostk.physics.unit.Length,
relative_position: ostk.physics.coordinate.Position = undefined,
relative_velocity: ostk.physics.coordinate.Velocity = undefined,
start_screen_period: ostk.physics.time.Instant,
end_screen_period: ostk.physics.time.Instant,
screen_volume_frame: ostk.core.type.String =,
screen_volume_shape: ostk.core.type.String =,
screen_volume_x: ostk.core.type.Real = Undefined,
screen_volume_y: ostk.core.type.Real = Undefined,
screen_volume_z: ostk.core.type.Real = Undefined,
screen_entry_time: ostk.physics.time.Instant,
screen_exit_time: ostk.physics.time.Instant,
collision_probability: ostk.core.type.Real,
collision_probability_method: ostk.core.type.String,
)

Bases: pybind11_object

Relative metadata.

Ref: https://public.ccsds.org/Pubs/508x0b1e2s.pdf

Constructor.

Parameters:

  • comment (str) -- The comment.

  • time_of_closest_approach (Instant) -- The time of closest approach.

  • miss_distance (Distance) -- The miss distance.

  • relative_position (Position) -- The relative position.

  • relative_velocity (Velocity) -- The relative velocity.

  • start_screen_period (Instant) -- The start screen period.

  • end_screen_period (Instant) -- The end screen period.

  • screen_volume_frame (str) -- The screen volume frame.

  • screen_volume_shape (str) -- The screen volume shape.

  • screen_volume_x (float) -- The screen volume x.

  • screen_volume_y (float) -- The screen volume y.

  • screen_volume_z (float) -- The screen volume z.

  • screen_entry_time (Instant) -- The screen entry time.

  • screen_exit_time (Instant) -- The screen exit time.

  • collision_probability (Probability) -- The collision probability.

  • collision_probability_method (str) -- The collision probability method.

property collision_probability

The collision probability.

property collision_probability_method

The collision probability method.

property comment

The comment.

property end_screen_period

The end screen period.

property miss_distance

The miss distance.

property relative_position

The relative position.

property relative_velocity

The relative velocity.

property screen_entry_time

The screen entry time.

property screen_exit_time

The screen exit time.

property screen_volume_frame

The screen volume frame.

property screen_volume_shape

The screen volume shape.

property screen_volume_x

The screen volume x.

property screen_volume_y

The screen volume y.

property screen_volume_z

The screen volume z.

property start_screen_period

The start screen period.

property time_of_closest_approach

The time of closest approach.

static dictionary(
dictionary: ostk.core.container.Dictionary,
) → ostk.astrodynamics.conjunction.message.ccsds.CDM

Get the CDM dictionary.

Returns:

The CDM dictionary.

Return type:

Dictionary

get_ccsds_cdm_version(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.core.type.String

Get the CCSDS CDM version.

Returns:

The CCSDS CDM version.

Return type:

str

get_collision_probability(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.core.type.Real

Get the collision probability.

Returns:

The collision probability.

Return type:

Probability

get_collision_probability_method(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.core.type.String

Get the collision probability method.

Returns:

The collision probability method.

Return type:

str

get_creation_instant(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.physics.time.Instant

Get the creation instant.

Returns:

The creation instant.

Return type:

Instant

get_data_array(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → List[ostk::astrodynamics::conjunction::message::ccsds::CDM::Data]

Get the objects data array.

Returns:

The objects data array.

Return type:

Array<CDM::Data>

get_header(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk::astrodynamics::conjunction::message::ccsds::CDM::Header

Get the CDM header.

Returns:

The CDM header.

Return type:

CDM::Header

get_message_for(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.core.type.String

Get the message for.

Returns:

The message for.

Return type:

str

get_message_id(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.core.type.String

Get the message ID.

Returns:

The message ID.

Return type:

str

get_metadata_array(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → List[ostk::astrodynamics::conjunction::message::ccsds::CDM::Metadata]

Get the objects metadata array.

Returns:

The objects metadata array.

Return type:

Array<CDM::Metadata>

get_miss_distance(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.physics.unit.Length

Get the miss distance.

Returns:

The miss distance.

Return type:

Distance

get_object_data_at(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
index: int,
) → ostk::astrodynamics::conjunction::message::ccsds::CDM::Data

Get the object data at the specified index.

Parameters:

index (int) -- The index of the object data.

Returns:

The object data.

Return type:

Data

get_object_metadata_at(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
index: int,
) → ostk::astrodynamics::conjunction::message::ccsds::CDM::Metadata

Get the object metadata at the specified index.

Parameters:

index (int) -- The index of the object metadata.

Returns:

The object metadata.

Return type:

CDM::Metadata

get_originator(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.core.type.String

Get the originator.

Returns:

The originator.

Return type:

str

get_relative_metadata(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk::astrodynamics::conjunction::message::ccsds::CDM::RelativeMetadata

Get the relative metadata.

Returns:

The relative metadata.

Return type:

CDM::RelativeMetadata

get_relative_position(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.physics.coordinate.Position

Get the relative position.

Returns:

The relative position.

Return type:

Position

get_relative_velocity(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.physics.coordinate.Velocity

Get the relative velocity.

Returns:

The relative velocity.

Return type:

Velocity

get_time_of_closest_approach(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.physics.time.Instant

Get the time of closest approach.

Returns:

The time of closest approach.

Return type:

Instant

is_defined(self: ostk.astrodynamics.conjunction.message.ccsds.CDM) → bool

Check if the CDM is defined.

Returns:

True if the CDM is defined, False otherwise.

Return type:

bool

static load(
file: ostk.core.filesystem.File,
) → ostk.astrodynamics.conjunction.message.ccsds.CDM

Load a CDM from a file.

Parameters:

file (str) -- The file to load.

Returns:

The loaded CDM.

Return type:

CDM

static object_type_from_string(
string: ostk.core.type.String,
) → ostk.astrodynamics.conjunction.message.ccsds.CDM.ObjectType

Get the object type from a string.

Parameters:

string (str) -- The string to get the object type from.

Returns:

The object type.

Return type:

CDM::ObjectType

static parse(
string: ostk.core.type.String,
) → ostk.astrodynamics.conjunction.message.ccsds.CDM

Parse a CDM from a string.

Parameters:

string (str) -- The string to parse.

Returns:

The parsed CDM.

Return type:

CDM

static undefined() → ostk.astrodynamics.conjunction.message.ccsds.CDM

Get an undefined CDM.

Returns:

An undefined CDM.

Return type:

CDM

\ No newline at end of file + ostk.astrodynamics.conjunction.message.ccsds.CDM — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.conjunction.message.ccsds.CDM

class CDM(self: ostk.astrodynamics.conjunction.message.ccsds.CDM, header: ostk::astrodynamics::conjunction::message::ccsds::CDM::Header, relative_metadata: ostk::astrodynamics::conjunction::message::ccsds::CDM::RelativeMetadata, objects_metadata_array: List[ostk::astrodynamics::conjunction::message::ccsds::CDM::Metadata], objects_data_array: List[ostk::astrodynamics::conjunction::message::ccsds::CDM::Data])

Bases: pybind11_object

Conjunction Data Message.

Ref: https://public.ccsds.org/Pubs/508x0b1e2s.pdf

Constructor.

Parameters:

  • header (CDM::Header) -- The CDM header.

  • relative_metadata (CDM::RelativeMetadata) -- The relative metadata.

  • objects_metadata_array (Array<CDM::Metadata>) -- The objects metadata array.

  • objects_data_array (Array<CDM::Data>) -- The objects data array.

Methods

dictionary

Get the CDM dictionary.

get_ccsds_cdm_version

Get the CCSDS CDM version.

get_collision_probability

Get the collision probability.

get_collision_probability_method

Get the collision probability method.

get_creation_instant

Get the creation instant.

get_data_array

Get the objects data array.

get_header

Get the CDM header.

get_message_for

Get the message for.

get_message_id

Get the message ID.

get_metadata_array

Get the objects metadata array.

get_miss_distance

Get the miss distance.

get_object_data_at

Get the object data at the specified index.

get_object_metadata_at

Get the object metadata at the specified index.

get_originator

Get the originator.

get_relative_metadata

Get the relative metadata.

get_relative_position

Get the relative position.

get_relative_velocity

Get the relative velocity.

get_time_of_closest_approach

Get the time of closest approach.

is_defined

Check if the CDM is defined.

load

Load a CDM from a file.

object_type_from_string

Get the object type from a string.

parse

Parse a CDM from a string.

undefined

Get an undefined CDM.

class Data

Bases: pybind11_object

Conjunction Data Message data.

Ref: https://public.ccsds.org/Pubs/508x0b1e2s.pdf

__init__(self: ostk.astrodynamics.conjunction.message.ccsds.CDM.Data, time_last_observation_start: ostk.physics.time.Instant, time_last_observation_end: ostk.physics.time.Instant, recommended_od_span: ostk.physics.time.Duration, actual_od_span: ostk.physics.time.Duration, observations_available: ostk.core.type.Integer, observations_used: ostk.core.type.Integer, tracks_available: ostk.core.type.Integer, tracks_used: ostk.core.type.Integer, residuals_accepted: ostk.core.type.Real, weighted_rms: ostk.core.type.Real, area_pc: ostk.core.type.Real, area_drag: ostk.core.type.Real, area_srp: ostk.core.type.Real, mass: ostk.physics.unit.Mass, cd_area_over_mass: ostk.core.type.Real, cr_area_over_mass: ostk.core.type.Real, thrust_acceleration: ostk.core.type.Real, sedr: ostk.core.type.Real, state: ostk.astrodynamics.trajectory.State = undefined, covariance_matrix: numpy.ndarray[numpy.float64[m, n]] = array([[0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.], [0., 0., 0., 0., 0., 0., 0., 0., 0.]])) -> None

Constructor.

Args:

time_last_observation_start (Instant): The time of the last observation start. time_last_observation_end (Instant): The time of the last observation end. recommended_od_span (Duration): The recommended OD span. actual_od_span (Duration): The actual OD span. observations_available (int): The number of observations available. observations_used (int): The number of observations used. tracks_available (int): The number of tracks available. tracks_used (int): The number of tracks used. residuals_accepted (float): The residuals accepted. weighted_rms (float): The weighted RMS. area_pc (float): The area PC. area_drag (float): The area drag. area_srp (float): The area SRP. mass (Mass): The mass. cd_area_over_mass (float): The CD area over mass. cr_area_over_mass (float): The CR area over mass. thrust_acceleration (float): The thrust acceleration. sedr (float): The SEDR. state (State): The state. covariance_matrix (MatrixXd): The covariance matrix.

property actual_od_span

The actual OD span.

property area_drag

The area drag.

property area_pc

The area PC.

property area_srp

The area SRP.

property cd_area_over_mass

The CD area over mass.

property covariance_matrix

The covariance matrix.

property cr_area_over_mass

The CR area over mass.

property mass

The mass.

property observations_available

The number of observations available.

property observations_used

The number of observations used.

property recommended_od_span

The recommended OD span.

property residuals_accepted

The residuals accepted.

property sedr

The SEDR.

property state

The state.

property thrust_acceleration

The thrust acceleration.

property time_last_observation_end

The time of the last observation end.

property time_last_observation_start

The time of the last observation start.

property tracks_available

The number of tracks available.

property tracks_used

The number of tracks used.

property weighted_rms

The weighted RMS.

class Header(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM.Header,
ccsds_cdm_version: ostk.core.type.String,
comment: ostk.core.type.String =,
creation_date: ostk.physics.time.Instant,
originator: ostk.core.type.String,
message_for: ostk.core.type.String =,
message_id: ostk.core.type.String,
)

Bases: pybind11_object

Conjunction Data Message header.

Ref: https://public.ccsds.org/Pubs/508x0b1e2s.pdf

Constructor.

Parameters:

  • ccsds_cdm_version (str) -- The CCSDS CDM version.

  • comment (str) -- The comment.

  • creation_date (Instant) -- The creation date.

  • originator (str) -- The originator.

  • message_for (str) -- The message for.

  • message_id (str) -- The message ID.

property ccsds_cdm_version

The CCSDS CDM version.

property comment

The comment.

property creation_date

The creation date.

property message_for

The message for.

property message_id

The message ID.

property originator

The originator.

class Metadata(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM.Metadata,
comment: ostk.core.type.String =,
object: ostk.core.type.String,
object_designator: ostk.core.type.Integer,
catalog_name: ostk.core.type.String =,
object_name: ostk.core.type.String,
international_designator: ostk.core.type.String,
object_type: ostk.astrodynamics.conjunction.message.ccsds.CDM.ObjectType,
operator_contact_position: ostk.core.type.String =,
operator_organization: ostk.core.type.String =,
operator_phone: ostk.core.type.String =,
operator_email: ostk.core.type.String =,
ephemeris_name: ostk.core.type.String,
covariance_method: ostk.core.type.String,
maneuverable: ostk.core.type.String,
orbit_center: ostk.core.type.String =,
reference_frame: ostk.core.type.String,
gravity_model: ostk.core.type.String =,
atmospheric_model: ostk.core.type.String =,
n_body_perturbations: ostk.core.type.String =,
solar_radiation_pressure: bool = False,
earth_tides: bool = False,
in_track_thrust: bool = False,
)

Bases: pybind11_object

Conjunction Data Message metadata.

Ref: https://public.ccsds.org/Pubs/508x0b1e2s.pdf

Constructor.

Parameters:

  • comment (str) -- The comment.

  • object (str) -- The object.

  • object_designator (int) -- The object designator.

  • catalog_name (str) -- The catalog name.

  • object_name (str) -- The object name.

  • international_designator (str) -- The international designator.

  • object_type (ObjectType) -- The object type.

  • operator_contact_position (str) -- The operator contact position.

  • operator_organization (str) -- The operator organization.

  • operator_phone (str) -- The operator phone.

  • operator_email (str) -- The operator email.

  • ephemeris_name (str) -- The ephemeris name.

  • covariance_method (str) -- The covariance method.

  • maneuverable (str) -- The maneuverable.

  • orbit_center (str) -- The orbit center.

  • reference_frame (str) -- The reference frame.

  • gravity_model (str) -- The gravity model.

  • atmospheric_model (str) -- The atmospheric model.

  • n_body_perturbations (str) -- The n-body perturbations.

  • solar_radiation_pressure (bool) -- The solar radiation pressure.

  • earth_tides (bool) -- The earth tides.

  • in_track_thrust (bool) -- The in-track thrust.

property atmospheric_model

The atmospheric model.

property catalog_name

The catalog name.

property comment

The comment.

property covariance_method

The covariance method.

property earth_tides

The earth tides.

property ephemeris_name

The ephemeris name.

property gravity_model

The gravity model.

property in_track_thrust

The in-track thrust.

property international_designator

The international designator.

property maneuverable

The maneuverable.

property n_body_perturbations

The n-body perturbations.

property object

The object.

property object_designator

The object designator.

property object_name

The object name.

property object_type

The object type.

property operator_contact_position

The operator contact position.

property operator_email

The operator email.

property operator_organization

The operator organization.

property operator_phone

The operator phone.

property orbit_center

The orbit center.

property reference_frame

The reference frame.

property solar_radiation_pressure

The solar radiation pressure.

class ObjectType(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM.ObjectType,
value: int,
)

Bases: pybind11_object

Object type.

Members:

Payload : Payload

RocketBody : Rocket Body

Debris : Debris

Unknown : Unknown

Other : Other

property name
class RelativeMetadata(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM.RelativeMetadata,
comment: ostk.core.type.String =,
time_of_closest_approach: ostk.physics.time.Instant,
miss_distance: ostk.physics.unit.Length,
relative_position: ostk.physics.coordinate.Position = undefined,
relative_velocity: ostk.physics.coordinate.Velocity = undefined,
start_screen_period: ostk.physics.time.Instant,
end_screen_period: ostk.physics.time.Instant,
screen_volume_frame: ostk.core.type.String =,
screen_volume_shape: ostk.core.type.String =,
screen_volume_x: ostk.core.type.Real = Undefined,
screen_volume_y: ostk.core.type.Real = Undefined,
screen_volume_z: ostk.core.type.Real = Undefined,
screen_entry_time: ostk.physics.time.Instant,
screen_exit_time: ostk.physics.time.Instant,
collision_probability: ostk.core.type.Real,
collision_probability_method: ostk.core.type.String,
)

Bases: pybind11_object

Relative metadata.

Ref: https://public.ccsds.org/Pubs/508x0b1e2s.pdf

Constructor.

Parameters:

  • comment (str) -- The comment.

  • time_of_closest_approach (Instant) -- The time of closest approach.

  • miss_distance (Distance) -- The miss distance.

  • relative_position (Position) -- The relative position.

  • relative_velocity (Velocity) -- The relative velocity.

  • start_screen_period (Instant) -- The start screen period.

  • end_screen_period (Instant) -- The end screen period.

  • screen_volume_frame (str) -- The screen volume frame.

  • screen_volume_shape (str) -- The screen volume shape.

  • screen_volume_x (float) -- The screen volume x.

  • screen_volume_y (float) -- The screen volume y.

  • screen_volume_z (float) -- The screen volume z.

  • screen_entry_time (Instant) -- The screen entry time.

  • screen_exit_time (Instant) -- The screen exit time.

  • collision_probability (Probability) -- The collision probability.

  • collision_probability_method (str) -- The collision probability method.

property collision_probability

The collision probability.

property collision_probability_method

The collision probability method.

property comment

The comment.

property end_screen_period

The end screen period.

property miss_distance

The miss distance.

property relative_position

The relative position.

property relative_velocity

The relative velocity.

property screen_entry_time

The screen entry time.

property screen_exit_time

The screen exit time.

property screen_volume_frame

The screen volume frame.

property screen_volume_shape

The screen volume shape.

property screen_volume_x

The screen volume x.

property screen_volume_y

The screen volume y.

property screen_volume_z

The screen volume z.

property start_screen_period

The start screen period.

property time_of_closest_approach

The time of closest approach.

static dictionary(
dictionary: ostk.core.container.Dictionary,
) → ostk.astrodynamics.conjunction.message.ccsds.CDM

Get the CDM dictionary.

Returns:

The CDM dictionary.

Return type:

Dictionary

get_ccsds_cdm_version(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.core.type.String

Get the CCSDS CDM version.

Returns:

The CCSDS CDM version.

Return type:

str

get_collision_probability(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.core.type.Real

Get the collision probability.

Returns:

The collision probability.

Return type:

Probability

get_collision_probability_method(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.core.type.String

Get the collision probability method.

Returns:

The collision probability method.

Return type:

str

get_creation_instant(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.physics.time.Instant

Get the creation instant.

Returns:

The creation instant.

Return type:

Instant

get_data_array(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → List[ostk::astrodynamics::conjunction::message::ccsds::CDM::Data]

Get the objects data array.

Returns:

The objects data array.

Return type:

Array<CDM::Data>

get_header(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk::astrodynamics::conjunction::message::ccsds::CDM::Header

Get the CDM header.

Returns:

The CDM header.

Return type:

CDM::Header

get_message_for(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.core.type.String

Get the message for.

Returns:

The message for.

Return type:

str

get_message_id(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.core.type.String

Get the message ID.

Returns:

The message ID.

Return type:

str

get_metadata_array(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → List[ostk::astrodynamics::conjunction::message::ccsds::CDM::Metadata]

Get the objects metadata array.

Returns:

The objects metadata array.

Return type:

Array<CDM::Metadata>

get_miss_distance(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.physics.unit.Length

Get the miss distance.

Returns:

The miss distance.

Return type:

Distance

get_object_data_at(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
index: int,
) → ostk::astrodynamics::conjunction::message::ccsds::CDM::Data

Get the object data at the specified index.

Parameters:

index (int) -- The index of the object data.

Returns:

The object data.

Return type:

Data

get_object_metadata_at(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
index: int,
) → ostk::astrodynamics::conjunction::message::ccsds::CDM::Metadata

Get the object metadata at the specified index.

Parameters:

index (int) -- The index of the object metadata.

Returns:

The object metadata.

Return type:

CDM::Metadata

get_originator(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.core.type.String

Get the originator.

Returns:

The originator.

Return type:

str

get_relative_metadata(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk::astrodynamics::conjunction::message::ccsds::CDM::RelativeMetadata

Get the relative metadata.

Returns:

The relative metadata.

Return type:

CDM::RelativeMetadata

get_relative_position(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.physics.coordinate.Position

Get the relative position.

Returns:

The relative position.

Return type:

Position

get_relative_velocity(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.physics.coordinate.Velocity

Get the relative velocity.

Returns:

The relative velocity.

Return type:

Velocity

get_time_of_closest_approach(
self: ostk.astrodynamics.conjunction.message.ccsds.CDM,
) → ostk.physics.time.Instant

Get the time of closest approach.

Returns:

The time of closest approach.

Return type:

Instant

is_defined(self: ostk.astrodynamics.conjunction.message.ccsds.CDM) → bool

Check if the CDM is defined.

Returns:

True if the CDM is defined, False otherwise.

Return type:

bool

static load(
file: ostk.core.filesystem.File,
) → ostk.astrodynamics.conjunction.message.ccsds.CDM

Load a CDM from a file.

Parameters:

file (str) -- The file to load.

Returns:

The loaded CDM.

Return type:

CDM

static object_type_from_string(
string: ostk.core.type.String,
) → ostk.astrodynamics.conjunction.message.ccsds.CDM.ObjectType

Get the object type from a string.

Parameters:

string (str) -- The string to get the object type from.

Returns:

The object type.

Return type:

CDM::ObjectType

static parse(
string: ostk.core.type.String,
) → ostk.astrodynamics.conjunction.message.ccsds.CDM

Parse a CDM from a string.

Parameters:

string (str) -- The string to parse.

Returns:

The parsed CDM.

Return type:

CDM

static undefined() → ostk.astrodynamics.conjunction.message.ccsds.CDM

Get an undefined CDM.

Returns:

An undefined CDM.

Return type:

CDM

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_datetime.html b/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_datetime.html index 0b4897fa1..3cd5d4f5b 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_datetime.html +++ b/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_datetime.html @@ -1 +1 @@ - ostk.astrodynamics.converters.coerce_to_datetime — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.converters.coerce_to_datetime

coerce_to_datetime(
value: Instant | datetime | str,
) → datetime

Return datetime from value.

Parameters:

value (Instant | datetime | str) -- A value to coerce.

Returns:

The coerced datetime.

Return type:

datetime

\ No newline at end of file + ostk.astrodynamics.converters.coerce_to_datetime — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.converters.coerce_to_datetime

coerce_to_datetime(
value: Instant | datetime | str,
) → datetime

Return datetime from value.

Parameters:

value (Instant | datetime | str) -- A value to coerce.

Returns:

The coerced datetime.

Return type:

datetime

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_duration.html b/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_duration.html index 62599e919..d005ba4fc 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_duration.html +++ b/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_duration.html @@ -1 +1 @@ - ostk.astrodynamics.converters.coerce_to_duration — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.converters.coerce_to_duration

coerce_to_duration(
value: Duration | timedelta,
) → Duration

Return Duration from value.

Parameters:

value (Duration | datetime) -- A value to coerce.

Returns:

The coerced Duration.

Return type:

Duration

\ No newline at end of file + ostk.astrodynamics.converters.coerce_to_duration — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.converters.coerce_to_duration

coerce_to_duration(
value: Duration | timedelta,
) → Duration

Return Duration from value.

Parameters:

value (Duration | datetime) -- A value to coerce.

Returns:

The coerced Duration.

Return type:

Duration

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_instant.html b/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_instant.html index 6ee63f893..184b99b5d 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_instant.html +++ b/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_instant.html @@ -1 +1 @@ - ostk.astrodynamics.converters.coerce_to_instant — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.converters.coerce_to_instant

coerce_to_instant(
value: Instant | datetime | str,
) → Instant

Return Instant from value.

Parameters:

value (Instant | datetime | str) -- A value to coerce.

Returns:

The coerced Instant.

Return type:

Instant

\ No newline at end of file + ostk.astrodynamics.converters.coerce_to_instant — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.converters.coerce_to_instant

coerce_to_instant(
value: Instant | datetime | str,
) → Instant

Return Instant from value.

Parameters:

value (Instant | datetime | str) -- A value to coerce.

Returns:

The coerced Instant.

Return type:

Instant

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_interval.html b/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_interval.html index 5791cf64d..85412f9a9 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_interval.html +++ b/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_interval.html @@ -1 +1 @@ - ostk.astrodynamics.converters.coerce_to_interval — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.converters.coerce_to_interval

coerce_to_interval(
value: Interval | tuple[Instant, Instant] | tuple[datetime, datetime],
) → Interval

Return Interval from value.

Parameters:

value (Interval | tuple[Instant, Instant] | tuple[datetime, datetime]) -- A value to coerce.

Returns:

The coerced Interval.

Return type:

Interval

\ No newline at end of file + ostk.astrodynamics.converters.coerce_to_interval — Open Space Toolkit Astrodynamics Skip to content
\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_iso.html b/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_iso.html index 5a2b7d53c..dfdb799ac 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_iso.html +++ b/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_iso.html @@ -1 +1 @@ - ostk.astrodynamics.converters.coerce_to_iso — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.converters.coerce_to_iso

coerce_to_iso(
value: Instant | datetime | str,
timespec: str = 'microseconds',
) → str

Return an ISO string from value.

Parameters:

  • value (Instant | datetime | str) -- A value to coerce.

  • timespec (str) -- A time resolution. Defaults to "microseconds".

Returns:

The coerced ISO string.

Return type:

str

\ No newline at end of file + ostk.astrodynamics.converters.coerce_to_iso — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.converters.coerce_to_iso

coerce_to_iso(
value: Instant | datetime | str,
timespec: str = 'microseconds',
) → str

Return an ISO string from value.

Parameters:

  • value (Instant | datetime | str) -- A value to coerce.

  • timespec (str) -- A time resolution. Defaults to "microseconds".

Returns:

The coerced ISO string.

Return type:

str

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_position.html b/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_position.html index ce510348d..3790518ee 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_position.html +++ b/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_position.html @@ -1 +1 @@ - ostk.astrodynamics.converters.coerce_to_position — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.converters.coerce_to_position

coerce_to_position(
value: Position | tuple[float, float, float] | list[float] | ndarray,
frame: Frame,
) → Position

Return Position from value.

Parameters:
Returns:

The coerced Position.

Return type:

Position

\ No newline at end of file + ostk.astrodynamics.converters.coerce_to_position — Open Space Toolkit Astrodynamics Skip to content
\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_velocity.html b/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_velocity.html index 2752e1e4c..92ab602de 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_velocity.html +++ b/_build/html/_autosummary/ostk.astrodynamics.converters.coerce_to_velocity.html @@ -1 +1 @@ - ostk.astrodynamics.converters.coerce_to_velocity — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.converters.coerce_to_velocity

coerce_to_velocity(
value: Velocity | tuple[float, float, float] | list[float] | ndarray,
frame: Frame,
) → Velocity

Return Velocity from value.

Parameters:
Returns:

The coerced Velocity.

Return type:

Velocity

\ No newline at end of file + ostk.astrodynamics.converters.coerce_to_velocity — Open Space Toolkit Astrodynamics Skip to content
\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.display.AccessesPlot.html b/_build/html/_autosummary/ostk.astrodynamics.display.AccessesPlot.html index 5b64b2070..1cd4ad2c1 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.display.AccessesPlot.html +++ b/_build/html/_autosummary/ostk.astrodynamics.display.AccessesPlot.html @@ -1 +1 @@ - ostk.astrodynamics.display.AccessesPlot — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.display.AccessesPlot

class AccessesPlot(
earth: Celestial,
interval: RealInterval,
trajectory_step: Duration,
access_step: Duration,
ground_station_lla: LLA,
color: str,
)

Bases: object

Accesses plot. Display a 2D world map, with 1 ground station and multiple satellites, highlighting the accesses.

Methods

add_satellite

Add a satellite trajectory to the plot, including a highligh ot the interference accesses.

show

Display the figure.

add_satellite(
trajectory: Trajectory,
accesses: list[Access],
rgb: list[int],
) → None

Add a satellite trajectory to the plot, including a highligh ot the interference accesses.

show()

Display the figure.

\ No newline at end of file + ostk.astrodynamics.display.AccessesPlot — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.display.AccessesPlot

class AccessesPlot(
earth: Celestial,
interval: RealInterval,
trajectory_step: Duration,
access_step: Duration,
ground_station_lla: LLA,
color: str,
)

Bases: object

Accesses plot. Display a 2D world map, with 1 ground station and multiple satellites, highlighting the accesses.

Methods

add_satellite

Add a satellite trajectory to the plot, including a highligh ot the interference accesses.

show

Display the figure.

add_satellite(
trajectory: Trajectory,
accesses: list[Access],
rgb: list[int],
) → None

Add a satellite trajectory to the plot, including a highligh ot the interference accesses.

show()

Display the figure.

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.dynamics.AtmosphericDrag.html b/_build/html/_autosummary/ostk.astrodynamics.dynamics.AtmosphericDrag.html index ba36a8a84..01c7c28c8 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.dynamics.AtmosphericDrag.html +++ b/_build/html/_autosummary/ostk.astrodynamics.dynamics.AtmosphericDrag.html @@ -1 +1 @@ - ostk.astrodynamics.dynamics.AtmosphericDrag — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.dynamics.AtmosphericDrag

class AtmosphericDrag(
self: ostk.astrodynamics.dynamics.AtmosphericDrag,
celestial: ostk.physics.environment.object.Celestial,
)

Bases: Dynamics

The atmospheric drag dynamics.

Constructor.

Parameters:

celestial (Celestial) -- The celestial body.

Methods

compute_contribution

Compute the contribution of the atmospheric drag to the state vector.

from_environment

Create a list of Dynamics objects from an environment.

get_celestial

Get the celestial body.

get_name

Get the name of the dynamics.

get_read_coordinate_subsets

Get the coordinate subsets that the dynamics reads.

get_write_coordinate_subsets

Get the coordinate subsets that the dynamics writes.

is_defined

Check if the atmospheric drag is defined.

compute_contribution(
self: ostk.astrodynamics.dynamics.AtmosphericDrag,
instant: ostk.physics.time.Instant,
x: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, 1]]

Compute the contribution of the atmospheric drag to the state vector.

Parameters:

  • instant (Instant) -- The instant of the state vector.

  • x (numpy.ndarray) -- The state vector.

  • frame (Frame) -- The reference frame.

Returns:

The contribution of the atmospheric drag to the state vector.

Return type:

numpy.ndarray

static from_environment(
environment: ostk.physics.Environment,
) → List[ostk.astrodynamics.Dynamics]

Create a list of Dynamics objects from an environment.

Parameters:

environment (Environment) -- The environment to create the dynamics from.

Returns:

The list of Dynamics objects created from the environment.

Return type:

dynamics (list[Dynamics])

get_celestial(
self: ostk.astrodynamics.dynamics.AtmosphericDrag,
) → ostk.physics.environment.object.Celestial

Get the celestial body.

Returns:

The celestial body.

Return type:

Celestial

get_name(self: ostk.astrodynamics.Dynamics) → ostk.core.type.String

Get the name of the dynamics.

Returns:

The name of the dynamics.

Return type:

name (str)

get_read_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics reads.

Returns:

The coordinate subsets that the dynamics reads.

Return type:

read_coordinate_subsets (Array<CoordinateSubset>)

get_write_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics writes.

Returns:

The coordinate subsets that the dynamics writes.

Return type:

write_coordinate_subsets (Array<CoordinateSubset>)

is_defined(self: ostk.astrodynamics.dynamics.AtmosphericDrag) → bool

Check if the atmospheric drag is defined.

Returns:

True if the atmospheric drag is defined, False otherwise.

Return type:

bool

\ No newline at end of file + ostk.astrodynamics.dynamics.AtmosphericDrag — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.dynamics.AtmosphericDrag

class AtmosphericDrag(
self: ostk.astrodynamics.dynamics.AtmosphericDrag,
celestial: ostk.physics.environment.object.Celestial,
)

Bases: Dynamics

The atmospheric drag dynamics.

Constructor.

Parameters:

celestial (Celestial) -- The celestial body.

Methods

compute_contribution

Compute the contribution of the atmospheric drag to the state vector.

from_environment

Create a list of Dynamics objects from an environment.

get_celestial

Get the celestial body.

get_name

Get the name of the dynamics.

get_read_coordinate_subsets

Get the coordinate subsets that the dynamics reads.

get_write_coordinate_subsets

Get the coordinate subsets that the dynamics writes.

is_defined

Check if the atmospheric drag is defined.

compute_contribution(
self: ostk.astrodynamics.dynamics.AtmosphericDrag,
instant: ostk.physics.time.Instant,
x: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, 1]]

Compute the contribution of the atmospheric drag to the state vector.

Parameters:

  • instant (Instant) -- The instant of the state vector.

  • x (numpy.ndarray) -- The state vector.

  • frame (Frame) -- The reference frame.

Returns:

The contribution of the atmospheric drag to the state vector.

Return type:

numpy.ndarray

static from_environment(
environment: ostk.physics.Environment,
) → List[ostk.astrodynamics.Dynamics]

Create a list of Dynamics objects from an environment.

Parameters:

environment (Environment) -- The environment to create the dynamics from.

Returns:

The list of Dynamics objects created from the environment.

Return type:

dynamics (list[Dynamics])

get_celestial(
self: ostk.astrodynamics.dynamics.AtmosphericDrag,
) → ostk.physics.environment.object.Celestial

Get the celestial body.

Returns:

The celestial body.

Return type:

Celestial

get_name(self: ostk.astrodynamics.Dynamics) → ostk.core.type.String

Get the name of the dynamics.

Returns:

The name of the dynamics.

Return type:

name (str)

get_read_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics reads.

Returns:

The coordinate subsets that the dynamics reads.

Return type:

read_coordinate_subsets (Array<CoordinateSubset>)

get_write_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics writes.

Returns:

The coordinate subsets that the dynamics writes.

Return type:

write_coordinate_subsets (Array<CoordinateSubset>)

is_defined(self: ostk.astrodynamics.dynamics.AtmosphericDrag) → bool

Check if the atmospheric drag is defined.

Returns:

True if the atmospheric drag is defined, False otherwise.

Return type:

bool

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.dynamics.CentralBodyGravity.html b/_build/html/_autosummary/ostk.astrodynamics.dynamics.CentralBodyGravity.html index 080cf7546..238fd4f25 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.dynamics.CentralBodyGravity.html +++ b/_build/html/_autosummary/ostk.astrodynamics.dynamics.CentralBodyGravity.html @@ -1 +1 @@ - ostk.astrodynamics.dynamics.CentralBodyGravity — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.dynamics.CentralBodyGravity

class CentralBodyGravity(
self: ostk.astrodynamics.dynamics.CentralBodyGravity,
celestial: ostk.physics.environment.object.Celestial,
)

Bases: Dynamics

The central-body gravity model.

Constructor.

Parameters:

celestial (Celestial) -- The central body.

Methods

compute_contribution

Compute the contribution of the central-body gravity to the state vector.

from_environment

Create a list of Dynamics objects from an environment.

get_celestial

Get the central body.

get_name

Get the name of the dynamics.

get_read_coordinate_subsets

Get the coordinate subsets that the dynamics reads.

get_write_coordinate_subsets

Get the coordinate subsets that the dynamics writes.

is_defined

Check if the central-body gravity is defined.

compute_contribution(
self: ostk.astrodynamics.dynamics.CentralBodyGravity,
instant: ostk.physics.time.Instant,
x: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, 1]]

Compute the contribution of the central-body gravity to the state vector.

Parameters:

  • instant (Instant) -- The instant of the state vector.

  • x (numpy.ndarray) -- The state vector.

  • frame (Frame) -- The reference frame.

Returns:

The contribution of the central-body gravity to the state vector.

Return type:

numpy.ndarray

static from_environment(
environment: ostk.physics.Environment,
) → List[ostk.astrodynamics.Dynamics]

Create a list of Dynamics objects from an environment.

Parameters:

environment (Environment) -- The environment to create the dynamics from.

Returns:

The list of Dynamics objects created from the environment.

Return type:

dynamics (list[Dynamics])

get_celestial(
self: ostk.astrodynamics.dynamics.CentralBodyGravity,
) → ostk.physics.environment.object.Celestial

Get the central body.

Returns:

The central body.

Return type:

Celestial

get_name(self: ostk.astrodynamics.Dynamics) → ostk.core.type.String

Get the name of the dynamics.

Returns:

The name of the dynamics.

Return type:

name (str)

get_read_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics reads.

Returns:

The coordinate subsets that the dynamics reads.

Return type:

read_coordinate_subsets (Array<CoordinateSubset>)

get_write_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics writes.

Returns:

The coordinate subsets that the dynamics writes.

Return type:

write_coordinate_subsets (Array<CoordinateSubset>)

is_defined(
self: ostk.astrodynamics.dynamics.CentralBodyGravity,
) → bool

Check if the central-body gravity is defined.

Returns:

True if the central-body gravity is defined, False otherwise.

Return type:

bool

\ No newline at end of file + ostk.astrodynamics.dynamics.CentralBodyGravity — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.dynamics.CentralBodyGravity

class CentralBodyGravity(
self: ostk.astrodynamics.dynamics.CentralBodyGravity,
celestial: ostk.physics.environment.object.Celestial,
)

Bases: Dynamics

The central-body gravity model.

Constructor.

Parameters:

celestial (Celestial) -- The central body.

Methods

compute_contribution

Compute the contribution of the central-body gravity to the state vector.

from_environment

Create a list of Dynamics objects from an environment.

get_celestial

Get the central body.

get_name

Get the name of the dynamics.

get_read_coordinate_subsets

Get the coordinate subsets that the dynamics reads.

get_write_coordinate_subsets

Get the coordinate subsets that the dynamics writes.

is_defined

Check if the central-body gravity is defined.

compute_contribution(
self: ostk.astrodynamics.dynamics.CentralBodyGravity,
instant: ostk.physics.time.Instant,
x: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, 1]]

Compute the contribution of the central-body gravity to the state vector.

Parameters:

  • instant (Instant) -- The instant of the state vector.

  • x (numpy.ndarray) -- The state vector.

  • frame (Frame) -- The reference frame.

Returns:

The contribution of the central-body gravity to the state vector.

Return type:

numpy.ndarray

static from_environment(
environment: ostk.physics.Environment,
) → List[ostk.astrodynamics.Dynamics]

Create a list of Dynamics objects from an environment.

Parameters:

environment (Environment) -- The environment to create the dynamics from.

Returns:

The list of Dynamics objects created from the environment.

Return type:

dynamics (list[Dynamics])

get_celestial(
self: ostk.astrodynamics.dynamics.CentralBodyGravity,
) → ostk.physics.environment.object.Celestial

Get the central body.

Returns:

The central body.

Return type:

Celestial

get_name(self: ostk.astrodynamics.Dynamics) → ostk.core.type.String

Get the name of the dynamics.

Returns:

The name of the dynamics.

Return type:

name (str)

get_read_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics reads.

Returns:

The coordinate subsets that the dynamics reads.

Return type:

read_coordinate_subsets (Array<CoordinateSubset>)

get_write_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics writes.

Returns:

The coordinate subsets that the dynamics writes.

Return type:

write_coordinate_subsets (Array<CoordinateSubset>)

is_defined(
self: ostk.astrodynamics.dynamics.CentralBodyGravity,
) → bool

Check if the central-body gravity is defined.

Returns:

True if the central-body gravity is defined, False otherwise.

Return type:

bool

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.dynamics.PositionDerivative.html b/_build/html/_autosummary/ostk.astrodynamics.dynamics.PositionDerivative.html index 26320b36a..5cab02c31 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.dynamics.PositionDerivative.html +++ b/_build/html/_autosummary/ostk.astrodynamics.dynamics.PositionDerivative.html @@ -1 +1 @@ - ostk.astrodynamics.dynamics.PositionDerivative — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.dynamics.PositionDerivative

class PositionDerivative(self: ostk.astrodynamics.dynamics.PositionDerivative)

Bases: Dynamics

The position derivative model.

Constructor.

Methods

compute_contribution

Compute the contribution of the position derivative to the state vector.

from_environment

Create a list of Dynamics objects from an environment.

get_name

Get the name of the dynamics.

get_read_coordinate_subsets

Get the coordinate subsets that the dynamics reads.

get_write_coordinate_subsets

Get the coordinate subsets that the dynamics writes.

is_defined

Check if the position derivative is defined.

compute_contribution(
self: ostk.astrodynamics.dynamics.PositionDerivative,
instant: ostk.physics.time.Instant,
x: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, 1]]

Compute the contribution of the position derivative to the state vector.

Parameters:

  • instant (Instant) -- The instant of the state vector.

  • x (numpy.ndarray) -- The state vector.

  • frame (Frame) -- The reference frame.

Returns:

The contribution of the position derivative to the state vector.

Return type:

numpy.ndarray

static from_environment(
environment: ostk.physics.Environment,
) → List[ostk.astrodynamics.Dynamics]

Create a list of Dynamics objects from an environment.

Parameters:

environment (Environment) -- The environment to create the dynamics from.

Returns:

The list of Dynamics objects created from the environment.

Return type:

dynamics (list[Dynamics])

get_name(self: ostk.astrodynamics.Dynamics) → ostk.core.type.String

Get the name of the dynamics.

Returns:

The name of the dynamics.

Return type:

name (str)

get_read_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics reads.

Returns:

The coordinate subsets that the dynamics reads.

Return type:

read_coordinate_subsets (Array<CoordinateSubset>)

get_write_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics writes.

Returns:

The coordinate subsets that the dynamics writes.

Return type:

write_coordinate_subsets (Array<CoordinateSubset>)

is_defined(
self: ostk.astrodynamics.dynamics.PositionDerivative,
) → bool

Check if the position derivative is defined.

Returns:

True if the position derivative is defined, False otherwise.

Return type:

bool

\ No newline at end of file + ostk.astrodynamics.dynamics.PositionDerivative — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.dynamics.PositionDerivative

class PositionDerivative(self: ostk.astrodynamics.dynamics.PositionDerivative)

Bases: Dynamics

The position derivative model.

Constructor.

Methods

compute_contribution

Compute the contribution of the position derivative to the state vector.

from_environment

Create a list of Dynamics objects from an environment.

get_name

Get the name of the dynamics.

get_read_coordinate_subsets

Get the coordinate subsets that the dynamics reads.

get_write_coordinate_subsets

Get the coordinate subsets that the dynamics writes.

is_defined

Check if the position derivative is defined.

compute_contribution(
self: ostk.astrodynamics.dynamics.PositionDerivative,
instant: ostk.physics.time.Instant,
x: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, 1]]

Compute the contribution of the position derivative to the state vector.

Parameters:

  • instant (Instant) -- The instant of the state vector.

  • x (numpy.ndarray) -- The state vector.

  • frame (Frame) -- The reference frame.

Returns:

The contribution of the position derivative to the state vector.

Return type:

numpy.ndarray

static from_environment(
environment: ostk.physics.Environment,
) → List[ostk.astrodynamics.Dynamics]

Create a list of Dynamics objects from an environment.

Parameters:

environment (Environment) -- The environment to create the dynamics from.

Returns:

The list of Dynamics objects created from the environment.

Return type:

dynamics (list[Dynamics])

get_name(self: ostk.astrodynamics.Dynamics) → ostk.core.type.String

Get the name of the dynamics.

Returns:

The name of the dynamics.

Return type:

name (str)

get_read_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics reads.

Returns:

The coordinate subsets that the dynamics reads.

Return type:

read_coordinate_subsets (Array<CoordinateSubset>)

get_write_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics writes.

Returns:

The coordinate subsets that the dynamics writes.

Return type:

write_coordinate_subsets (Array<CoordinateSubset>)

is_defined(
self: ostk.astrodynamics.dynamics.PositionDerivative,
) → bool

Check if the position derivative is defined.

Returns:

True if the position derivative is defined, False otherwise.

Return type:

bool

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.dynamics.Tabulated.html b/_build/html/_autosummary/ostk.astrodynamics.dynamics.Tabulated.html index 71ff2f2c7..6203a8ab8 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.dynamics.Tabulated.html +++ b/_build/html/_autosummary/ostk.astrodynamics.dynamics.Tabulated.html @@ -1 +1 @@ - ostk.astrodynamics.dynamics.Tabulated — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.dynamics.Tabulated

class Tabulated(self: ostk.astrodynamics.dynamics.Tabulated, instants: List[ostk.physics.time.Instant], contribution_profile: numpy.ndarray[numpy.float64[m, n]], coordinate_subsets: List[ostk::astrodynamics::trajectory::state::CoordinateSubset], frame: ostk.physics.coordinate.Frame, interpolation_type: ostk.mathematics.curve_fitting.Interpolator.Type = <Type.BarycentricRational: 0>)

Bases: Dynamics

The tabulated dynamics.

Constructor.

Parameters:

  • instants (list[Instant]) -- An array of instants.

  • contribution_profile (numpy.ndarray) -- A contribution profile.

  • coordinate_subsets (list[CoordinateSubset]) -- An array of coordinate subsets related to the contribution profile.

  • frame (Frame) -- A frame.

  • interpolation_type (Interpolator.Type, optional) -- The interpolation type. Defaults to Barycentric Rational.

Methods

access_contribution_profile

Access the contribution profile.

access_frame

Access the reference frame.

access_instants

Access the contribution instants.

compute_contribution

Compute the contribution from the contribution profile to the state vector.

from_environment

Create a list of Dynamics objects from an environment.

get_contribution_profile_from_coordinate_subsets

Get the contribution profile corresponding to a subset of coordinates.

get_interpolation_type

Get the interpolation type used for each row of the contribution profile (they are all the same).

get_name

Get the name of the dynamics.

get_read_coordinate_subsets

Get the coordinate subsets that the dynamics reads.

get_write_coordinate_subsets

Get the coordinate subsets that the dynamics writes.

is_defined

Check if the tabulated dynamics is defined.

access_contribution_profile(
self: ostk.astrodynamics.dynamics.Tabulated,
) → numpy.ndarray[numpy.float64[m, n]]

Access the contribution profile.

Returns:

The contribution profile.

Return type:

np.ndarray

access_frame(
self: ostk.astrodynamics.dynamics.Tabulated,
) → ostk.physics.coordinate.Frame

Access the reference frame.

Returns:

The reference frame.

Return type:

Frame

access_instants(
self: ostk.astrodynamics.dynamics.Tabulated,
) → List[ostk.physics.time.Instant]

Access the contribution instants.

Returns:

The contribution instants.

Return type:

list[Instant]

compute_contribution(
self: ostk.astrodynamics.dynamics.Tabulated,
instant: ostk.physics.time.Instant,
x: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, 1]]

Compute the contribution from the contribution profile to the state vector.

Parameters:

  • instant (Instant) -- The instant of the state vector.

  • x (numpy.ndarray) -- The state vector.

  • frame (Frame) -- The reference frame.

Returns:

The contribution from the contribution profile to the state vector.

Return type:

numpy.ndarray

static from_environment(
environment: ostk.physics.Environment,
) → List[ostk.astrodynamics.Dynamics]

Create a list of Dynamics objects from an environment.

Parameters:

environment (Environment) -- The environment to create the dynamics from.

Returns:

The list of Dynamics objects created from the environment.

Return type:

dynamics (list[Dynamics])

get_contribution_profile_from_coordinate_subsets(self: ostk.astrodynamics.dynamics.Tabulated, coordinate_subsets: List[ostk::astrodynamics::trajectory::state::CoordinateSubset]) → numpy.ndarray[numpy.float64[m, n]]

Get the contribution profile corresponding to a subset of coordinates.

Parameters:

coordinate_subsets (list[CoordinateSubset]) -- The coordinate subsets.

Returns:

The contribution profile.

Return type:

numpy.ndarray

get_interpolation_type(
self: ostk.astrodynamics.dynamics.Tabulated,
) → ostk.mathematics.curve_fitting.Interpolator.Type

Get the interpolation type used for each row of the contribution profile (they are all the same).

Returns:

The interpolation type.

Return type:

Interpolator.Type

get_name(self: ostk.astrodynamics.Dynamics) → ostk.core.type.String

Get the name of the dynamics.

Returns:

The name of the dynamics.

Return type:

name (str)

get_read_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics reads.

Returns:

The coordinate subsets that the dynamics reads.

Return type:

read_coordinate_subsets (Array<CoordinateSubset>)

get_write_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics writes.

Returns:

The coordinate subsets that the dynamics writes.

Return type:

write_coordinate_subsets (Array<CoordinateSubset>)

is_defined(self: ostk.astrodynamics.dynamics.Tabulated) → bool

Check if the tabulated dynamics is defined.

Returns:

True if the tabulated dynamics is defined, False otherwise.

Return type:

bool

\ No newline at end of file + ostk.astrodynamics.dynamics.Tabulated — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.dynamics.Tabulated

class Tabulated(self: ostk.astrodynamics.dynamics.Tabulated, instants: List[ostk.physics.time.Instant], contribution_profile: numpy.ndarray[numpy.float64[m, n]], coordinate_subsets: List[ostk::astrodynamics::trajectory::state::CoordinateSubset], frame: ostk.physics.coordinate.Frame, interpolation_type: ostk.mathematics.curve_fitting.Interpolator.Type = <Type.BarycentricRational: 0>)

Bases: Dynamics

The tabulated dynamics.

Constructor.

Parameters:

  • instants (list[Instant]) -- An array of instants.

  • contribution_profile (numpy.ndarray) -- A contribution profile.

  • coordinate_subsets (list[CoordinateSubset]) -- An array of coordinate subsets related to the contribution profile.

  • frame (Frame) -- A frame.

  • interpolation_type (Interpolator.Type, optional) -- The interpolation type. Defaults to Barycentric Rational.

Methods

access_contribution_profile

Access the contribution profile.

access_frame

Access the reference frame.

access_instants

Access the contribution instants.

compute_contribution

Compute the contribution from the contribution profile to the state vector.

from_environment

Create a list of Dynamics objects from an environment.

get_contribution_profile_from_coordinate_subsets

Get the contribution profile corresponding to a subset of coordinates.

get_interpolation_type

Get the interpolation type used for each row of the contribution profile (they are all the same).

get_name

Get the name of the dynamics.

get_read_coordinate_subsets

Get the coordinate subsets that the dynamics reads.

get_write_coordinate_subsets

Get the coordinate subsets that the dynamics writes.

is_defined

Check if the tabulated dynamics is defined.

access_contribution_profile(
self: ostk.astrodynamics.dynamics.Tabulated,
) → numpy.ndarray[numpy.float64[m, n]]

Access the contribution profile.

Returns:

The contribution profile.

Return type:

np.ndarray

access_frame(
self: ostk.astrodynamics.dynamics.Tabulated,
) → ostk.physics.coordinate.Frame

Access the reference frame.

Returns:

The reference frame.

Return type:

Frame

access_instants(
self: ostk.astrodynamics.dynamics.Tabulated,
) → List[ostk.physics.time.Instant]

Access the contribution instants.

Returns:

The contribution instants.

Return type:

list[Instant]

compute_contribution(
self: ostk.astrodynamics.dynamics.Tabulated,
instant: ostk.physics.time.Instant,
x: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, 1]]

Compute the contribution from the contribution profile to the state vector.

Parameters:

  • instant (Instant) -- The instant of the state vector.

  • x (numpy.ndarray) -- The state vector.

  • frame (Frame) -- The reference frame.

Returns:

The contribution from the contribution profile to the state vector.

Return type:

numpy.ndarray

static from_environment(
environment: ostk.physics.Environment,
) → List[ostk.astrodynamics.Dynamics]

Create a list of Dynamics objects from an environment.

Parameters:

environment (Environment) -- The environment to create the dynamics from.

Returns:

The list of Dynamics objects created from the environment.

Return type:

dynamics (list[Dynamics])

get_contribution_profile_from_coordinate_subsets(self: ostk.astrodynamics.dynamics.Tabulated, coordinate_subsets: List[ostk::astrodynamics::trajectory::state::CoordinateSubset]) → numpy.ndarray[numpy.float64[m, n]]

Get the contribution profile corresponding to a subset of coordinates.

Parameters:

coordinate_subsets (list[CoordinateSubset]) -- The coordinate subsets.

Returns:

The contribution profile.

Return type:

numpy.ndarray

get_interpolation_type(
self: ostk.astrodynamics.dynamics.Tabulated,
) → ostk.mathematics.curve_fitting.Interpolator.Type

Get the interpolation type used for each row of the contribution profile (they are all the same).

Returns:

The interpolation type.

Return type:

Interpolator.Type

get_name(self: ostk.astrodynamics.Dynamics) → ostk.core.type.String

Get the name of the dynamics.

Returns:

The name of the dynamics.

Return type:

name (str)

get_read_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics reads.

Returns:

The coordinate subsets that the dynamics reads.

Return type:

read_coordinate_subsets (Array<CoordinateSubset>)

get_write_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics writes.

Returns:

The coordinate subsets that the dynamics writes.

Return type:

write_coordinate_subsets (Array<CoordinateSubset>)

is_defined(self: ostk.astrodynamics.dynamics.Tabulated) → bool

Check if the tabulated dynamics is defined.

Returns:

True if the tabulated dynamics is defined, False otherwise.

Return type:

bool

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.dynamics.ThirdBodyGravity.html b/_build/html/_autosummary/ostk.astrodynamics.dynamics.ThirdBodyGravity.html index f2483ed66..c77cbd890 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.dynamics.ThirdBodyGravity.html +++ b/_build/html/_autosummary/ostk.astrodynamics.dynamics.ThirdBodyGravity.html @@ -1 +1 @@ - ostk.astrodynamics.dynamics.ThirdBodyGravity — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.dynamics.ThirdBodyGravity

class ThirdBodyGravity(
self: ostk.astrodynamics.dynamics.ThirdBodyGravity,
celestial: ostk.physics.environment.object.Celestial,
)

Bases: Dynamics

The third body gravity model.

Constructor.

Parameters:

celestial (Celestial) -- The celestial body.

Methods

compute_contribution

Compute the contribution of the third-body gravity to the state vector.

from_environment

Create a list of Dynamics objects from an environment.

get_celestial

Get the celestial body.

get_name

Get the name of the dynamics.

get_read_coordinate_subsets

Get the coordinate subsets that the dynamics reads.

get_write_coordinate_subsets

Get the coordinate subsets that the dynamics writes.

is_defined

Check if the third-body gravity is defined.

compute_contribution(
self: ostk.astrodynamics.dynamics.ThirdBodyGravity,
instant: ostk.physics.time.Instant,
x: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, 1]]

Compute the contribution of the third-body gravity to the state vector.

Parameters:

  • instant (Instant) -- The instant of the state vector.

  • x (numpy.ndarray) -- The state vector.

  • frame (Frame) -- The reference frame.

Returns:

The contribution of the third-body gravity to the state vector.

Return type:

numpy.ndarray

static from_environment(
environment: ostk.physics.Environment,
) → List[ostk.astrodynamics.Dynamics]

Create a list of Dynamics objects from an environment.

Parameters:

environment (Environment) -- The environment to create the dynamics from.

Returns:

The list of Dynamics objects created from the environment.

Return type:

dynamics (list[Dynamics])

get_celestial(
self: ostk.astrodynamics.dynamics.ThirdBodyGravity,
) → ostk.physics.environment.object.Celestial

Get the celestial body.

Returns:

The celestial body.

Return type:

Celestial

get_name(self: ostk.astrodynamics.Dynamics) → ostk.core.type.String

Get the name of the dynamics.

Returns:

The name of the dynamics.

Return type:

name (str)

get_read_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics reads.

Returns:

The coordinate subsets that the dynamics reads.

Return type:

read_coordinate_subsets (Array<CoordinateSubset>)

get_write_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics writes.

Returns:

The coordinate subsets that the dynamics writes.

Return type:

write_coordinate_subsets (Array<CoordinateSubset>)

is_defined(self: ostk.astrodynamics.dynamics.ThirdBodyGravity) → bool

Check if the third-body gravity is defined.

Returns:

True if the third-body gravity is defined, False otherwise.

Return type:

bool

\ No newline at end of file + ostk.astrodynamics.dynamics.ThirdBodyGravity — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.dynamics.ThirdBodyGravity

class ThirdBodyGravity(
self: ostk.astrodynamics.dynamics.ThirdBodyGravity,
celestial: ostk.physics.environment.object.Celestial,
)

Bases: Dynamics

The third body gravity model.

Constructor.

Parameters:

celestial (Celestial) -- The celestial body.

Methods

compute_contribution

Compute the contribution of the third-body gravity to the state vector.

from_environment

Create a list of Dynamics objects from an environment.

get_celestial

Get the celestial body.

get_name

Get the name of the dynamics.

get_read_coordinate_subsets

Get the coordinate subsets that the dynamics reads.

get_write_coordinate_subsets

Get the coordinate subsets that the dynamics writes.

is_defined

Check if the third-body gravity is defined.

compute_contribution(
self: ostk.astrodynamics.dynamics.ThirdBodyGravity,
instant: ostk.physics.time.Instant,
x: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, 1]]

Compute the contribution of the third-body gravity to the state vector.

Parameters:

  • instant (Instant) -- The instant of the state vector.

  • x (numpy.ndarray) -- The state vector.

  • frame (Frame) -- The reference frame.

Returns:

The contribution of the third-body gravity to the state vector.

Return type:

numpy.ndarray

static from_environment(
environment: ostk.physics.Environment,
) → List[ostk.astrodynamics.Dynamics]

Create a list of Dynamics objects from an environment.

Parameters:

environment (Environment) -- The environment to create the dynamics from.

Returns:

The list of Dynamics objects created from the environment.

Return type:

dynamics (list[Dynamics])

get_celestial(
self: ostk.astrodynamics.dynamics.ThirdBodyGravity,
) → ostk.physics.environment.object.Celestial

Get the celestial body.

Returns:

The celestial body.

Return type:

Celestial

get_name(self: ostk.astrodynamics.Dynamics) → ostk.core.type.String

Get the name of the dynamics.

Returns:

The name of the dynamics.

Return type:

name (str)

get_read_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics reads.

Returns:

The coordinate subsets that the dynamics reads.

Return type:

read_coordinate_subsets (Array<CoordinateSubset>)

get_write_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics writes.

Returns:

The coordinate subsets that the dynamics writes.

Return type:

write_coordinate_subsets (Array<CoordinateSubset>)

is_defined(self: ostk.astrodynamics.dynamics.ThirdBodyGravity) → bool

Check if the third-body gravity is defined.

Returns:

True if the third-body gravity is defined, False otherwise.

Return type:

bool

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.dynamics.Thruster.html b/_build/html/_autosummary/ostk.astrodynamics.dynamics.Thruster.html index 7028d4f2d..b2aaa47fb 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.dynamics.Thruster.html +++ b/_build/html/_autosummary/ostk.astrodynamics.dynamics.Thruster.html @@ -1 +1 @@ - ostk.astrodynamics.dynamics.Thruster — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.dynamics.Thruster

class Thruster(
self: ostk.astrodynamics.dynamics.Thruster,
satellite_system: ostk.astrodynamics.flight.system.SatelliteSystem,
guidance_law: ostk::astrodynamics::GuidanceLaw,
name: ostk.core.type.String =,
)

Bases: Dynamics

Abstract Thruster Class.

Base class to derive other thruster classes from. Cannot be instantiated.

Constructor.

Parameters:

  • satellite_system (SatelliteSystem) -- The satellite system.

  • guidance_law (GuidanceLaw) -- The guidance law used to compute the acceleration vector.

  • name (str) -- The name of the thruster.

Methods

compute_contribution

Compute the contribution of the thruster to the state vector.

from_environment

Create a list of Dynamics objects from an environment.

get_guidance_law

Get the guidance law of the thruster.

get_name

Get the name of the dynamics.

get_read_coordinate_subsets

Get the coordinate subsets that the dynamics reads.

get_satellite_system

Get the satellite system of the thruster.

get_write_coordinate_subsets

Get the coordinate subsets that the dynamics writes.

is_defined

Check if the thruster is defined.

compute_contribution(
self: ostk.astrodynamics.dynamics.Thruster,
instant: ostk.physics.time.Instant,
state_vector: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, 1]]

Compute the contribution of the thruster to the state vector.

Parameters:

  • instant (Instant) -- The instant of the state vector.

  • state_vector (numpy.ndarray) -- The state vector.

  • frame (Frame) -- The reference frame.

Returns:

The contribution of the thruster to the state vector.

Return type:

numpy.ndarray

static from_environment(
environment: ostk.physics.Environment,
) → List[ostk.astrodynamics.Dynamics]

Create a list of Dynamics objects from an environment.

Parameters:

environment (Environment) -- The environment to create the dynamics from.

Returns:

The list of Dynamics objects created from the environment.

Return type:

dynamics (list[Dynamics])

get_guidance_law(
self: ostk.astrodynamics.dynamics.Thruster,
) → ostk::astrodynamics::GuidanceLaw

Get the guidance law of the thruster.

Returns:

The guidance law.

Return type:

GuidanceLaw

get_name(self: ostk.astrodynamics.Dynamics) → ostk.core.type.String

Get the name of the dynamics.

Returns:

The name of the dynamics.

Return type:

name (str)

get_read_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics reads.

Returns:

The coordinate subsets that the dynamics reads.

Return type:

read_coordinate_subsets (Array<CoordinateSubset>)

get_satellite_system(
self: ostk.astrodynamics.dynamics.Thruster,
) → ostk.astrodynamics.flight.system.SatelliteSystem

Get the satellite system of the thruster.

Returns:

The satellite system.

Return type:

SatelliteSystem

get_write_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics writes.

Returns:

The coordinate subsets that the dynamics writes.

Return type:

write_coordinate_subsets (Array<CoordinateSubset>)

is_defined(self: ostk.astrodynamics.dynamics.Thruster) → bool

Check if the thruster is defined.

Returns:

True if the thruster is defined, False otherwise.

Return type:

bool

\ No newline at end of file + ostk.astrodynamics.dynamics.Thruster — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.dynamics.Thruster

class Thruster(
self: ostk.astrodynamics.dynamics.Thruster,
satellite_system: ostk.astrodynamics.flight.system.SatelliteSystem,
guidance_law: ostk::astrodynamics::GuidanceLaw,
name: ostk.core.type.String =,
)

Bases: Dynamics

Abstract Thruster Class.

Base class to derive other thruster classes from. Cannot be instantiated.

Constructor.

Parameters:

  • satellite_system (SatelliteSystem) -- The satellite system.

  • guidance_law (GuidanceLaw) -- The guidance law used to compute the acceleration vector.

  • name (str) -- The name of the thruster.

Methods

compute_contribution

Compute the contribution of the thruster to the state vector.

from_environment

Create a list of Dynamics objects from an environment.

get_guidance_law

Get the guidance law of the thruster.

get_name

Get the name of the dynamics.

get_read_coordinate_subsets

Get the coordinate subsets that the dynamics reads.

get_satellite_system

Get the satellite system of the thruster.

get_write_coordinate_subsets

Get the coordinate subsets that the dynamics writes.

is_defined

Check if the thruster is defined.

compute_contribution(
self: ostk.astrodynamics.dynamics.Thruster,
instant: ostk.physics.time.Instant,
state_vector: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, 1]]

Compute the contribution of the thruster to the state vector.

Parameters:

  • instant (Instant) -- The instant of the state vector.

  • state_vector (numpy.ndarray) -- The state vector.

  • frame (Frame) -- The reference frame.

Returns:

The contribution of the thruster to the state vector.

Return type:

numpy.ndarray

static from_environment(
environment: ostk.physics.Environment,
) → List[ostk.astrodynamics.Dynamics]

Create a list of Dynamics objects from an environment.

Parameters:

environment (Environment) -- The environment to create the dynamics from.

Returns:

The list of Dynamics objects created from the environment.

Return type:

dynamics (list[Dynamics])

get_guidance_law(
self: ostk.astrodynamics.dynamics.Thruster,
) → ostk::astrodynamics::GuidanceLaw

Get the guidance law of the thruster.

Returns:

The guidance law.

Return type:

GuidanceLaw

get_name(self: ostk.astrodynamics.Dynamics) → ostk.core.type.String

Get the name of the dynamics.

Returns:

The name of the dynamics.

Return type:

name (str)

get_read_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics reads.

Returns:

The coordinate subsets that the dynamics reads.

Return type:

read_coordinate_subsets (Array<CoordinateSubset>)

get_satellite_system(
self: ostk.astrodynamics.dynamics.Thruster,
) → ostk.astrodynamics.flight.system.SatelliteSystem

Get the satellite system of the thruster.

Returns:

The satellite system.

Return type:

SatelliteSystem

get_write_coordinate_subsets(
self: ostk.astrodynamics.Dynamics,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets that the dynamics writes.

Returns:

The coordinate subsets that the dynamics writes.

Return type:

write_coordinate_subsets (Array<CoordinateSubset>)

is_defined(self: ostk.astrodynamics.dynamics.Thruster) → bool

Check if the thruster is defined.

Returns:

True if the thruster is defined, False otherwise.

Return type:

bool

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.event_condition.AngularCondition.html b/_build/html/_autosummary/ostk.astrodynamics.event_condition.AngularCondition.html index f907d881b..99ed8be99 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.event_condition.AngularCondition.html +++ b/_build/html/_autosummary/ostk.astrodynamics.event_condition.AngularCondition.html @@ -1 +1 @@ - ostk.astrodynamics.event_condition.AngularCondition — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.event_condition.AngularCondition

class AngularCondition(*args, **kwargs)

Bases: EventCondition

An Angular Event Condition.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.event_condition.AngularCondition, name: ostk.core.type.String, criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion, evaluator: Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real], target_angle: ostk.physics.unit.Angle) -> None

    Constructor.

    Args:

    name (str): The name of the condition. criterion (ostk.astrodynamics.event_condition.AngularCondition.Criterion): The criterion of the condition. evaluator (function): The evaluator of the condition. target_angle (Angle): The target angle of the condition.

  2. __init__(self: ostk.astrodynamics.event_condition.AngularCondition, name: ostk.core.type.String, criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion, evaluator: Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real], target: ostk.astrodynamics.EventCondition.Target) -> None

    Constructor.

    Args:

    name (str): The name of the condition. criterion (ostk.astrodynamics.event_condition.AngularCondition.Criterion): The criterion of the condition. evaluator (function): The evaluator of the condition. target (EventConditionTarget): The target of the condition.

Methods

get_criterion

Get the criterion of the condition.

get_evaluator

Get the evaluator of the event condition.

get_name

Get the name of the event condition.

get_target

Get the target of the event condition.

get_target_angle

Get the target angle of the condition.

get_target_range

Get the target range of the condition.

is_satisfied

Check if the condition is satisfied.

string_from_criterion

Get the string representation of a criterion.

within_range

Create an angular condition that is satisfied when the angle is within a range.

class Criterion(
self: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
value: int,
)

Bases: pybind11_object

Angular condition criterion.

Members:

PositiveCrossing

NegativeCrossing

AnyCrossing

WithinRange

property name
class Target(*args, **kwargs)

Bases: pybind11_object

The Event Condition Target.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.core.type.Real, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    value (float): The value of the target. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  2. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Length, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    length (Length): The value of the target as a Length. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  3. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Angle, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    angle (Angle): The value of the target as an Angle. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

static StringFromType(
arg0: ostk.astrodynamics.EventCondition.Target.Type,
) → ostk.core.type.String

Enum as a string

Parameters:

type (EventConditionTarget.Type) -- The type of the target.

Returns:

Name of the enum as a string.

Return type:

string (str)

class Type(
self: ostk.astrodynamics.EventCondition.Target.Type,
value: int,
)

Bases: pybind11_object

Event Condition Target type.

Members:

Absolute : Absolute

Relative : Relative to the provided State.

property name
property type

The type of the target.

Type:

Type

property value

The value of the target.

Type:

Real

get_criterion(
self: ostk.astrodynamics.event_condition.AngularCondition,
) → ostk.astrodynamics.event_condition.AngularCondition.Criterion

Get the criterion of the condition.

Returns:

The criterion of the condition.

Return type:

ostk.astrodynamics.event_condition.AngularCondition.Criterion

get_evaluator(
self: ostk.astrodynamics.EventCondition,
) → Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real]

Get the evaluator of the event condition.

Returns:

The evaluator of the event condition.

Return type:

evaluator (str)

get_name(
self: ostk.astrodynamics.EventCondition,
) → ostk.core.type.String

Get the name of the event condition.

Returns:

The name of the event condition.

Return type:

name (str)

get_target(
self: ostk.astrodynamics.EventCondition,
) → ostk.astrodynamics.EventCondition.Target

Get the target of the event condition.

Returns:

The target of the event condition.

Return type:

target (EventConditionTarget)

get_target_angle(
self: ostk.astrodynamics.event_condition.AngularCondition,
) → ostk.physics.unit.Angle

Get the target angle of the condition.

Returns:

The target angle of the condition.

Return type:

Angle

get_target_range(
self: ostk.astrodynamics.event_condition.AngularCondition,
) → Tuple[ostk.physics.unit.Angle, ostk.physics.unit.Angle]

Get the target range of the condition.

Returns:

The target range of the condition.

Return type:

tuple

is_satisfied(
self: ostk.astrodynamics.event_condition.AngularCondition,
current_state: ostk.astrodynamics.trajectory.State,
previous_state: ostk.astrodynamics.trajectory.State,
) → bool

Check if the condition is satisfied.

Parameters:

  • current_state (State) -- The current state.

  • previous_state (State) -- The previous state.

Returns:

True if the condition is satisfied, False otherwise.

Return type:

bool

static string_from_criterion(
criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
) → ostk.core.type.String

Get the string representation of a criterion.

Parameters:

criterion (ostk.astrodynamics.event_condition.AngularCondition.Criterion) -- The criterion.

Returns:

The string representation of the criterion.

Return type:

str

static within_range(
name: ostk.core.type.String,
evaluator: Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real],
target_range: Tuple[ostk.physics.unit.Angle, ostk.physics.unit.Angle],
) → ostk.astrodynamics.event_condition.AngularCondition

Create an angular condition that is satisfied when the angle is within a range.

Parameters:

  • name (str) -- The name of the condition.

  • evaluator (function) -- The evaluator of the condition.

  • target_range (tuple) -- The target range of the condition.

Returns:

The angular condition.

Return type:

AngularCondition

\ No newline at end of file + ostk.astrodynamics.event_condition.AngularCondition — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.event_condition.AngularCondition

class AngularCondition(*args, **kwargs)

Bases: EventCondition

An Angular Event Condition.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.event_condition.AngularCondition, name: ostk.core.type.String, criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion, evaluator: Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real], target_angle: ostk.physics.unit.Angle) -> None

    Constructor.

    Args:

    name (str): The name of the condition. criterion (ostk.astrodynamics.event_condition.AngularCondition.Criterion): The criterion of the condition. evaluator (function): The evaluator of the condition. target_angle (Angle): The target angle of the condition.

  2. __init__(self: ostk.astrodynamics.event_condition.AngularCondition, name: ostk.core.type.String, criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion, evaluator: Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real], target: ostk.astrodynamics.EventCondition.Target) -> None

    Constructor.

    Args:

    name (str): The name of the condition. criterion (ostk.astrodynamics.event_condition.AngularCondition.Criterion): The criterion of the condition. evaluator (function): The evaluator of the condition. target (EventConditionTarget): The target of the condition.

Methods

get_criterion

Get the criterion of the condition.

get_evaluator

Get the evaluator of the event condition.

get_name

Get the name of the event condition.

get_target

Get the target of the event condition.

get_target_angle

Get the target angle of the condition.

get_target_range

Get the target range of the condition.

is_satisfied

Check if the condition is satisfied.

string_from_criterion

Get the string representation of a criterion.

within_range

Create an angular condition that is satisfied when the angle is within a range.

class Criterion(
self: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
value: int,
)

Bases: pybind11_object

Angular condition criterion.

Members:

PositiveCrossing

NegativeCrossing

AnyCrossing

WithinRange

property name
class Target(*args, **kwargs)

Bases: pybind11_object

The Event Condition Target.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.core.type.Real, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    value (float): The value of the target. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  2. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Length, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    length (Length): The value of the target as a Length. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  3. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Angle, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    angle (Angle): The value of the target as an Angle. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

static StringFromType(
arg0: ostk.astrodynamics.EventCondition.Target.Type,
) → ostk.core.type.String

Enum as a string

Parameters:

type (EventConditionTarget.Type) -- The type of the target.

Returns:

Name of the enum as a string.

Return type:

string (str)

class Type(
self: ostk.astrodynamics.EventCondition.Target.Type,
value: int,
)

Bases: pybind11_object

Event Condition Target type.

Members:

Absolute : Absolute

Relative : Relative to the provided State.

property name
property type

The type of the target.

Type:

Type

property value

The value of the target.

Type:

Real

get_criterion(
self: ostk.astrodynamics.event_condition.AngularCondition,
) → ostk.astrodynamics.event_condition.AngularCondition.Criterion

Get the criterion of the condition.

Returns:

The criterion of the condition.

Return type:

ostk.astrodynamics.event_condition.AngularCondition.Criterion

get_evaluator(
self: ostk.astrodynamics.EventCondition,
) → Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real]

Get the evaluator of the event condition.

Returns:

The evaluator of the event condition.

Return type:

evaluator (str)

get_name(
self: ostk.astrodynamics.EventCondition,
) → ostk.core.type.String

Get the name of the event condition.

Returns:

The name of the event condition.

Return type:

name (str)

get_target(
self: ostk.astrodynamics.EventCondition,
) → ostk.astrodynamics.EventCondition.Target

Get the target of the event condition.

Returns:

The target of the event condition.

Return type:

target (EventConditionTarget)

get_target_angle(
self: ostk.astrodynamics.event_condition.AngularCondition,
) → ostk.physics.unit.Angle

Get the target angle of the condition.

Returns:

The target angle of the condition.

Return type:

Angle

get_target_range(
self: ostk.astrodynamics.event_condition.AngularCondition,
) → Tuple[ostk.physics.unit.Angle, ostk.physics.unit.Angle]

Get the target range of the condition.

Returns:

The target range of the condition.

Return type:

tuple

is_satisfied(
self: ostk.astrodynamics.event_condition.AngularCondition,
current_state: ostk.astrodynamics.trajectory.State,
previous_state: ostk.astrodynamics.trajectory.State,
) → bool

Check if the condition is satisfied.

Parameters:

  • current_state (State) -- The current state.

  • previous_state (State) -- The previous state.

Returns:

True if the condition is satisfied, False otherwise.

Return type:

bool

static string_from_criterion(
criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
) → ostk.core.type.String

Get the string representation of a criterion.

Parameters:

criterion (ostk.astrodynamics.event_condition.AngularCondition.Criterion) -- The criterion.

Returns:

The string representation of the criterion.

Return type:

str

static within_range(
name: ostk.core.type.String,
evaluator: Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real],
target_range: Tuple[ostk.physics.unit.Angle, ostk.physics.unit.Angle],
) → ostk.astrodynamics.event_condition.AngularCondition

Create an angular condition that is satisfied when the angle is within a range.

Parameters:

  • name (str) -- The name of the condition.

  • evaluator (function) -- The evaluator of the condition.

  • target_range (tuple) -- The target range of the condition.

Returns:

The angular condition.

Return type:

AngularCondition

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.event_condition.BooleanCondition.html b/_build/html/_autosummary/ostk.astrodynamics.event_condition.BooleanCondition.html index 0e619c021..73cca9307 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.event_condition.BooleanCondition.html +++ b/_build/html/_autosummary/ostk.astrodynamics.event_condition.BooleanCondition.html @@ -1 +1 @@ - ostk.astrodynamics.event_condition.BooleanCondition — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.event_condition.BooleanCondition

class BooleanCondition(
self: ostk.astrodynamics.event_condition.BooleanCondition,
name: ostk.core.type.String,
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
evaluator: Callable[[ostk.astrodynamics.trajectory.State], bool],
is_inverse: bool,
)

Bases: RealCondition

A Boolean Event Condition.

Constructor.

Parameters:

  • name (str) -- The name of the condition.

  • criterion (Criterion) -- The criterion of the condition.

  • evaluator (function) -- The evaluator of the condition.

  • is_inverse (bool) -- Whether the condition is inverse.

Methods

duration_condition

Generate a duration condition.

evaluate

Evaluate the condition.

get_criterion

Get the criterion of the condition.

get_evaluator

Get the evaluator of the event condition.

get_name

Get the name of the event condition.

get_target

Get the target of the event condition.

is_inversed

Check if the condition is inverse.

is_satisfied

Check if the condition is satisfied.

string_from_criterion

Get the string representation of a criterion.

class Criterion(
self: ostk.astrodynamics.event_condition.RealCondition.Criterion,
value: int,
)

Bases: pybind11_object

The Criterion that defines how the condition is satisfied.

Members:

PositiveCrossing : The positive crossing criterion

NegativeCrossing : The negative crossing criterion

AnyCrossing : The any crossing criterion

StrictlyPositive : The strictly positive criterion

StrictlyNegative : The strictly negative criterion

property name
class Target(*args, **kwargs)

Bases: pybind11_object

The Event Condition Target.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.core.type.Real, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    value (float): The value of the target. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  2. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Length, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    length (Length): The value of the target as a Length. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  3. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Angle, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    angle (Angle): The value of the target as an Angle. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

static StringFromType(
arg0: ostk.astrodynamics.EventCondition.Target.Type,
) → ostk.core.type.String

Enum as a string

Parameters:

type (EventConditionTarget.Type) -- The type of the target.

Returns:

Name of the enum as a string.

Return type:

string (str)

class Type(
self: ostk.astrodynamics.EventCondition.Target.Type,
value: int,
)

Bases: pybind11_object

Event Condition Target type.

Members:

Absolute : Absolute

Relative : Relative to the provided State.

property name
property type

The type of the target.

Type:

Type

property value

The value of the target.

Type:

Real

static duration_condition(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
duration: ostk.physics.time.Duration,
) → ostk.astrodynamics.event_condition.RealCondition

Generate a duration condition.

Parameters:

  • criterion (Criterion) -- The criterion of the condition.

  • duration (Duration) -- Duration target.

Returns:

The duration condition.

Return type:

RealCondition

evaluate(
self: ostk.astrodynamics.event_condition.BooleanCondition,
state: ostk.astrodynamics.trajectory.State,
) → ostk.core.type.Real

Evaluate the condition.

Parameters:

state (State) -- The state.

Returns:

True if the condition is satisfied, False otherwise.

Return type:

bool

get_criterion(
self: ostk.astrodynamics.event_condition.RealCondition,
) → ostk.astrodynamics.event_condition.RealCondition.Criterion

Get the criterion of the condition.

Returns:

The criterion.

Return type:

Criterion

get_evaluator(
self: ostk.astrodynamics.EventCondition,
) → Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real]

Get the evaluator of the event condition.

Returns:

The evaluator of the event condition.

Return type:

evaluator (str)

get_name(
self: ostk.astrodynamics.EventCondition,
) → ostk.core.type.String

Get the name of the event condition.

Returns:

The name of the event condition.

Return type:

name (str)

get_target(
self: ostk.astrodynamics.EventCondition,
) → ostk.astrodynamics.EventCondition.Target

Get the target of the event condition.

Returns:

The target of the event condition.

Return type:

target (EventConditionTarget)

is_inversed(
self: ostk.astrodynamics.event_condition.BooleanCondition,
) → bool

Check if the condition is inverse.

Returns:

True if the condition is inverse, False otherwise.

Return type:

bool

is_satisfied(
self: ostk.astrodynamics.event_condition.BooleanCondition,
current_state: ostk.astrodynamics.trajectory.State,
previous_state: ostk.astrodynamics.trajectory.State,
) → bool

Check if the condition is satisfied.

Parameters:

  • current_state (State) -- The current state.

  • previous_state (State) -- The previous state.

Returns:

True if the condition is satisfied, False otherwise.

Return type:

bool

static string_from_criterion(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
) → ostk.core.type.String

Get the string representation of a criterion.

Parameters:

criterion (Criterion) -- The criterion.

Returns:

The string representation.

Return type:

str

\ No newline at end of file + ostk.astrodynamics.event_condition.BooleanCondition — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.event_condition.BooleanCondition

class BooleanCondition(
self: ostk.astrodynamics.event_condition.BooleanCondition,
name: ostk.core.type.String,
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
evaluator: Callable[[ostk.astrodynamics.trajectory.State], bool],
is_inverse: bool,
)

Bases: RealCondition

A Boolean Event Condition.

Constructor.

Parameters:

  • name (str) -- The name of the condition.

  • criterion (Criterion) -- The criterion of the condition.

  • evaluator (function) -- The evaluator of the condition.

  • is_inverse (bool) -- Whether the condition is inverse.

Methods

duration_condition

Generate a duration condition.

evaluate

Evaluate the condition.

get_criterion

Get the criterion of the condition.

get_evaluator

Get the evaluator of the event condition.

get_name

Get the name of the event condition.

get_target

Get the target of the event condition.

is_inversed

Check if the condition is inverse.

is_satisfied

Check if the condition is satisfied.

string_from_criterion

Get the string representation of a criterion.

class Criterion(
self: ostk.astrodynamics.event_condition.RealCondition.Criterion,
value: int,
)

Bases: pybind11_object

The Criterion that defines how the condition is satisfied.

Members:

PositiveCrossing : The positive crossing criterion

NegativeCrossing : The negative crossing criterion

AnyCrossing : The any crossing criterion

StrictlyPositive : The strictly positive criterion

StrictlyNegative : The strictly negative criterion

property name
class Target(*args, **kwargs)

Bases: pybind11_object

The Event Condition Target.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.core.type.Real, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    value (float): The value of the target. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  2. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Length, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    length (Length): The value of the target as a Length. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  3. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Angle, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    angle (Angle): The value of the target as an Angle. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

static StringFromType(
arg0: ostk.astrodynamics.EventCondition.Target.Type,
) → ostk.core.type.String

Enum as a string

Parameters:

type (EventConditionTarget.Type) -- The type of the target.

Returns:

Name of the enum as a string.

Return type:

string (str)

class Type(
self: ostk.astrodynamics.EventCondition.Target.Type,
value: int,
)

Bases: pybind11_object

Event Condition Target type.

Members:

Absolute : Absolute

Relative : Relative to the provided State.

property name
property type

The type of the target.

Type:

Type

property value

The value of the target.

Type:

Real

static duration_condition(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
duration: ostk.physics.time.Duration,
) → ostk.astrodynamics.event_condition.RealCondition

Generate a duration condition.

Parameters:

  • criterion (Criterion) -- The criterion of the condition.

  • duration (Duration) -- Duration target.

Returns:

The duration condition.

Return type:

RealCondition

evaluate(
self: ostk.astrodynamics.event_condition.BooleanCondition,
state: ostk.astrodynamics.trajectory.State,
) → ostk.core.type.Real

Evaluate the condition.

Parameters:

state (State) -- The state.

Returns:

True if the condition is satisfied, False otherwise.

Return type:

bool

get_criterion(
self: ostk.astrodynamics.event_condition.RealCondition,
) → ostk.astrodynamics.event_condition.RealCondition.Criterion

Get the criterion of the condition.

Returns:

The criterion.

Return type:

Criterion

get_evaluator(
self: ostk.astrodynamics.EventCondition,
) → Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real]

Get the evaluator of the event condition.

Returns:

The evaluator of the event condition.

Return type:

evaluator (str)

get_name(
self: ostk.astrodynamics.EventCondition,
) → ostk.core.type.String

Get the name of the event condition.

Returns:

The name of the event condition.

Return type:

name (str)

get_target(
self: ostk.astrodynamics.EventCondition,
) → ostk.astrodynamics.EventCondition.Target

Get the target of the event condition.

Returns:

The target of the event condition.

Return type:

target (EventConditionTarget)

is_inversed(
self: ostk.astrodynamics.event_condition.BooleanCondition,
) → bool

Check if the condition is inverse.

Returns:

True if the condition is inverse, False otherwise.

Return type:

bool

is_satisfied(
self: ostk.astrodynamics.event_condition.BooleanCondition,
current_state: ostk.astrodynamics.trajectory.State,
previous_state: ostk.astrodynamics.trajectory.State,
) → bool

Check if the condition is satisfied.

Parameters:

  • current_state (State) -- The current state.

  • previous_state (State) -- The previous state.

Returns:

True if the condition is satisfied, False otherwise.

Return type:

bool

static string_from_criterion(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
) → ostk.core.type.String

Get the string representation of a criterion.

Parameters:

criterion (Criterion) -- The criterion.

Returns:

The string representation.

Return type:

str

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.event_condition.COECondition.html b/_build/html/_autosummary/ostk.astrodynamics.event_condition.COECondition.html index 1eabba7f8..f22fad647 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.event_condition.COECondition.html +++ b/_build/html/_autosummary/ostk.astrodynamics.event_condition.COECondition.html @@ -1 +1 @@ - ostk.astrodynamics.event_condition.COECondition — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.event_condition.COECondition

class COECondition

Bases: pybind11_object

A COE Event Condition.

Methods

aop

Create a COE condition based on the argument of perigee.

eccentric_anomaly

Create a COE condition based on the eccentric anomaly.

eccentricity

Create a COE condition based on the eccentricity.

inclination

Create a COE condition based on the inclination.

mean_anomaly

Create a COE condition based on the mean anomaly.

raan

Create a COE condition based on the right ascension of the ascending node.

semi_major_axis

Create a COE condition based on the semi-major axis.

true_anomaly

Create a COE condition based on the true anomaly.

static aop(
criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
aop: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.AngularCondition

Create a COE condition based on the argument of perigee.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • aop (EventConditionTarget) -- The argument of perigee.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

static eccentric_anomaly(
criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
eccentric_anomaly: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.AngularCondition

Create a COE condition based on the eccentric anomaly.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • eccentric_anomaly (EventConditionTarget) -- The eccentric anomaly.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

static eccentricity(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
eccentricity: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.RealCondition

Create a COE condition based on the eccentricity.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • eccentricity (EventConditionTarget) -- The eccentricity.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

static inclination(
criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
inclination: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.AngularCondition

Create a COE condition based on the inclination.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • inclination (EventConditionTarget) -- The inclination.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

static mean_anomaly(
criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
mean_anomaly: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.AngularCondition

Create a COE condition based on the mean anomaly.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • mean_anomaly (EventConditionTarget) -- The mean anomaly.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

static raan(
criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
raan: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.AngularCondition

Create a COE condition based on the right ascension of the ascending node.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • raan (EventConditionTarget) -- The right ascension of the ascending node.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

static semi_major_axis(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
semi_major_axis: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.RealCondition

Create a COE condition based on the semi-major axis.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • semi_major_axis (EventConditionTarget) -- The semi-major axis.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

static true_anomaly(
criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
true_anomaly: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.AngularCondition

Create a COE condition based on the true anomaly.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • true_anomaly (EventConditionTarget) -- The true anomaly.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

\ No newline at end of file + ostk.astrodynamics.event_condition.COECondition — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.event_condition.COECondition

class COECondition

Bases: pybind11_object

A COE Event Condition.

Methods

aop

Create a COE condition based on the argument of perigee.

eccentric_anomaly

Create a COE condition based on the eccentric anomaly.

eccentricity

Create a COE condition based on the eccentricity.

inclination

Create a COE condition based on the inclination.

mean_anomaly

Create a COE condition based on the mean anomaly.

raan

Create a COE condition based on the right ascension of the ascending node.

semi_major_axis

Create a COE condition based on the semi-major axis.

true_anomaly

Create a COE condition based on the true anomaly.

static aop(
criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
aop: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.AngularCondition

Create a COE condition based on the argument of perigee.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • aop (EventConditionTarget) -- The argument of perigee.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

static eccentric_anomaly(
criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
eccentric_anomaly: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.AngularCondition

Create a COE condition based on the eccentric anomaly.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • eccentric_anomaly (EventConditionTarget) -- The eccentric anomaly.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

static eccentricity(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
eccentricity: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.RealCondition

Create a COE condition based on the eccentricity.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • eccentricity (EventConditionTarget) -- The eccentricity.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

static inclination(
criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
inclination: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.AngularCondition

Create a COE condition based on the inclination.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • inclination (EventConditionTarget) -- The inclination.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

static mean_anomaly(
criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
mean_anomaly: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.AngularCondition

Create a COE condition based on the mean anomaly.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • mean_anomaly (EventConditionTarget) -- The mean anomaly.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

static raan(
criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
raan: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.AngularCondition

Create a COE condition based on the right ascension of the ascending node.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • raan (EventConditionTarget) -- The right ascension of the ascending node.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

static semi_major_axis(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
semi_major_axis: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.RealCondition

Create a COE condition based on the semi-major axis.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • semi_major_axis (EventConditionTarget) -- The semi-major axis.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

static true_anomaly(
criterion: ostk.astrodynamics.event_condition.AngularCondition.Criterion,
frame: ostk.physics.coordinate.Frame,
true_anomaly: ostk.astrodynamics.EventCondition.Target,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.event_condition.AngularCondition

Create a COE condition based on the true anomaly.

Parameters:

  • criterion (Criterion) -- The criterion.

  • frame (Frame) -- The reference frame.

  • true_anomaly (EventConditionTarget) -- The true anomaly.

  • gravitational_parameter (float) -- The gravitational parameter.

Returns:

The COE condition.

Return type:

COECondition

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.event_condition.InstantCondition.html b/_build/html/_autosummary/ostk.astrodynamics.event_condition.InstantCondition.html index 19252b484..68af9bb9c 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.event_condition.InstantCondition.html +++ b/_build/html/_autosummary/ostk.astrodynamics.event_condition.InstantCondition.html @@ -1 +1 @@ - ostk.astrodynamics.event_condition.InstantCondition — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.event_condition.InstantCondition

class InstantCondition(
self: ostk.astrodynamics.event_condition.InstantCondition,
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
instant: ostk.physics.time.Instant,
)

Bases: RealCondition

An Instant Event Condition.

Constructor.

Parameters:

  • criterion (Criterion) -- The criterion.

  • instant (Instant) -- The instant.

Methods

duration_condition

Generate a duration condition.

evaluate

Evaluate the condition.

get_criterion

Get the criterion of the condition.

get_evaluator

Get the evaluator of the event condition.

get_instant

Get the instant.

get_name

Get the name of the event condition.

get_target

Get the target of the event condition.

is_satisfied

Check if the condition is satisfied.

string_from_criterion

Get the string representation of a criterion.

class Criterion(
self: ostk.astrodynamics.event_condition.RealCondition.Criterion,
value: int,
)

Bases: pybind11_object

The Criterion that defines how the condition is satisfied.

Members:

PositiveCrossing : The positive crossing criterion

NegativeCrossing : The negative crossing criterion

AnyCrossing : The any crossing criterion

StrictlyPositive : The strictly positive criterion

StrictlyNegative : The strictly negative criterion

property name
class Target(*args, **kwargs)

Bases: pybind11_object

The Event Condition Target.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.core.type.Real, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    value (float): The value of the target. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  2. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Length, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    length (Length): The value of the target as a Length. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  3. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Angle, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    angle (Angle): The value of the target as an Angle. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

static StringFromType(
arg0: ostk.astrodynamics.EventCondition.Target.Type,
) → ostk.core.type.String

Enum as a string

Parameters:

type (EventConditionTarget.Type) -- The type of the target.

Returns:

Name of the enum as a string.

Return type:

string (str)

class Type(
self: ostk.astrodynamics.EventCondition.Target.Type,
value: int,
)

Bases: pybind11_object

Event Condition Target type.

Members:

Absolute : Absolute

Relative : Relative to the provided State.

property name
property type

The type of the target.

Type:

Type

property value

The value of the target.

Type:

Real

static duration_condition(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
duration: ostk.physics.time.Duration,
) → ostk.astrodynamics.event_condition.RealCondition

Generate a duration condition.

Parameters:

  • criterion (Criterion) -- The criterion of the condition.

  • duration (Duration) -- Duration target.

Returns:

The duration condition.

Return type:

RealCondition

evaluate(
self: ostk.astrodynamics.event_condition.RealCondition,
state: ostk.astrodynamics.trajectory.State,
) → ostk.core.type.Real

Evaluate the condition.

Parameters:

state (State) -- The state.

Returns:

True if the condition is satisfied, False otherwise.

Return type:

bool

get_criterion(
self: ostk.astrodynamics.event_condition.RealCondition,
) → ostk.astrodynamics.event_condition.RealCondition.Criterion

Get the criterion of the condition.

Returns:

The criterion.

Return type:

Criterion

get_evaluator(
self: ostk.astrodynamics.EventCondition,
) → Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real]

Get the evaluator of the event condition.

Returns:

The evaluator of the event condition.

Return type:

evaluator (str)

get_instant(
self: ostk.astrodynamics.event_condition.InstantCondition,
) → ostk.physics.time.Instant

Get the instant.

Returns:

The instant.

Return type:

Instant

get_name(
self: ostk.astrodynamics.EventCondition,
) → ostk.core.type.String

Get the name of the event condition.

Returns:

The name of the event condition.

Return type:

name (str)

get_target(
self: ostk.astrodynamics.EventCondition,
) → ostk.astrodynamics.EventCondition.Target

Get the target of the event condition.

Returns:

The target of the event condition.

Return type:

target (EventConditionTarget)

is_satisfied(
self: ostk.astrodynamics.event_condition.RealCondition,
current_state: ostk.astrodynamics.trajectory.State,
previous_state: ostk.astrodynamics.trajectory.State,
) → bool

Check if the condition is satisfied.

Parameters:

  • current_state (State) -- The current state.

  • previous_state (State) -- The previous state.

Returns:

True if the condition is satisfied, False otherwise.

Return type:

bool

static string_from_criterion(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
) → ostk.core.type.String

Get the string representation of a criterion.

Parameters:

criterion (Criterion) -- The criterion.

Returns:

The string representation.

Return type:

str

\ No newline at end of file + ostk.astrodynamics.event_condition.InstantCondition — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.event_condition.InstantCondition

class InstantCondition(
self: ostk.astrodynamics.event_condition.InstantCondition,
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
instant: ostk.physics.time.Instant,
)

Bases: RealCondition

An Instant Event Condition.

Constructor.

Parameters:

  • criterion (Criterion) -- The criterion.

  • instant (Instant) -- The instant.

Methods

duration_condition

Generate a duration condition.

evaluate

Evaluate the condition.

get_criterion

Get the criterion of the condition.

get_evaluator

Get the evaluator of the event condition.

get_instant

Get the instant.

get_name

Get the name of the event condition.

get_target

Get the target of the event condition.

is_satisfied

Check if the condition is satisfied.

string_from_criterion

Get the string representation of a criterion.

class Criterion(
self: ostk.astrodynamics.event_condition.RealCondition.Criterion,
value: int,
)

Bases: pybind11_object

The Criterion that defines how the condition is satisfied.

Members:

PositiveCrossing : The positive crossing criterion

NegativeCrossing : The negative crossing criterion

AnyCrossing : The any crossing criterion

StrictlyPositive : The strictly positive criterion

StrictlyNegative : The strictly negative criterion

property name
class Target(*args, **kwargs)

Bases: pybind11_object

The Event Condition Target.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.core.type.Real, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    value (float): The value of the target. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  2. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Length, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    length (Length): The value of the target as a Length. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  3. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Angle, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    angle (Angle): The value of the target as an Angle. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

static StringFromType(
arg0: ostk.astrodynamics.EventCondition.Target.Type,
) → ostk.core.type.String

Enum as a string

Parameters:

type (EventConditionTarget.Type) -- The type of the target.

Returns:

Name of the enum as a string.

Return type:

string (str)

class Type(
self: ostk.astrodynamics.EventCondition.Target.Type,
value: int,
)

Bases: pybind11_object

Event Condition Target type.

Members:

Absolute : Absolute

Relative : Relative to the provided State.

property name
property type

The type of the target.

Type:

Type

property value

The value of the target.

Type:

Real

static duration_condition(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
duration: ostk.physics.time.Duration,
) → ostk.astrodynamics.event_condition.RealCondition

Generate a duration condition.

Parameters:

  • criterion (Criterion) -- The criterion of the condition.

  • duration (Duration) -- Duration target.

Returns:

The duration condition.

Return type:

RealCondition

evaluate(
self: ostk.astrodynamics.event_condition.RealCondition,
state: ostk.astrodynamics.trajectory.State,
) → ostk.core.type.Real

Evaluate the condition.

Parameters:

state (State) -- The state.

Returns:

True if the condition is satisfied, False otherwise.

Return type:

bool

get_criterion(
self: ostk.astrodynamics.event_condition.RealCondition,
) → ostk.astrodynamics.event_condition.RealCondition.Criterion

Get the criterion of the condition.

Returns:

The criterion.

Return type:

Criterion

get_evaluator(
self: ostk.astrodynamics.EventCondition,
) → Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real]

Get the evaluator of the event condition.

Returns:

The evaluator of the event condition.

Return type:

evaluator (str)

get_instant(
self: ostk.astrodynamics.event_condition.InstantCondition,
) → ostk.physics.time.Instant

Get the instant.

Returns:

The instant.

Return type:

Instant

get_name(
self: ostk.astrodynamics.EventCondition,
) → ostk.core.type.String

Get the name of the event condition.

Returns:

The name of the event condition.

Return type:

name (str)

get_target(
self: ostk.astrodynamics.EventCondition,
) → ostk.astrodynamics.EventCondition.Target

Get the target of the event condition.

Returns:

The target of the event condition.

Return type:

target (EventConditionTarget)

is_satisfied(
self: ostk.astrodynamics.event_condition.RealCondition,
current_state: ostk.astrodynamics.trajectory.State,
previous_state: ostk.astrodynamics.trajectory.State,
) → bool

Check if the condition is satisfied.

Parameters:

  • current_state (State) -- The current state.

  • previous_state (State) -- The previous state.

Returns:

True if the condition is satisfied, False otherwise.

Return type:

bool

static string_from_criterion(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
) → ostk.core.type.String

Get the string representation of a criterion.

Parameters:

criterion (Criterion) -- The criterion.

Returns:

The string representation.

Return type:

str

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.event_condition.RealCondition.html b/_build/html/_autosummary/ostk.astrodynamics.event_condition.RealCondition.html index e0a1144b8..582c1634a 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.event_condition.RealCondition.html +++ b/_build/html/_autosummary/ostk.astrodynamics.event_condition.RealCondition.html @@ -1 +1 @@ - ostk.astrodynamics.event_condition.RealCondition — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.event_condition.RealCondition

class RealCondition(*args, **kwargs)

Bases: EventCondition

A Real Event Condition.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.event_condition.RealCondition, name: ostk.core.type.String, criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion, evaluator: Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real], target_value: ostk.core.type.Real = 0.0) -> None

    Constructor.

    Args:

    name (str): The name of the condition. criterion (Criterion): The criterion of the condition. evaluator (function): The evaluator of the condition. target_value (float): The target value of the condition.

  2. __init__(self: ostk.astrodynamics.event_condition.RealCondition, name: ostk.core.type.String, criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion, evaluator: Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real], target: ostk.astrodynamics.EventCondition.Target) -> None

    Constructor.

    Args:

    name (str): The name of the condition. criterion (Criterion): The criterion of the condition. evaluator (function): The evaluator of the condition. target (EventConditionTarget): The target of the condition.

Methods

duration_condition

Generate a duration condition.

evaluate

Evaluate the condition.

get_criterion

Get the criterion of the condition.

get_evaluator

Get the evaluator of the event condition.

get_name

Get the name of the event condition.

get_target

Get the target of the event condition.

is_satisfied

Check if the condition is satisfied.

string_from_criterion

Get the string representation of a criterion.

class Criterion(
self: ostk.astrodynamics.event_condition.RealCondition.Criterion,
value: int,
)

Bases: pybind11_object

The Criterion that defines how the condition is satisfied.

Members:

PositiveCrossing : The positive crossing criterion

NegativeCrossing : The negative crossing criterion

AnyCrossing : The any crossing criterion

StrictlyPositive : The strictly positive criterion

StrictlyNegative : The strictly negative criterion

property name
class Target(*args, **kwargs)

Bases: pybind11_object

The Event Condition Target.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.core.type.Real, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    value (float): The value of the target. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  2. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Length, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    length (Length): The value of the target as a Length. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  3. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Angle, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    angle (Angle): The value of the target as an Angle. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

static StringFromType(
arg0: ostk.astrodynamics.EventCondition.Target.Type,
) → ostk.core.type.String

Enum as a string

Parameters:

type (EventConditionTarget.Type) -- The type of the target.

Returns:

Name of the enum as a string.

Return type:

string (str)

class Type(
self: ostk.astrodynamics.EventCondition.Target.Type,
value: int,
)

Bases: pybind11_object

Event Condition Target type.

Members:

Absolute : Absolute

Relative : Relative to the provided State.

property name
property type

The type of the target.

Type:

Type

property value

The value of the target.

Type:

Real

static duration_condition(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
duration: ostk.physics.time.Duration,
) → ostk.astrodynamics.event_condition.RealCondition

Generate a duration condition.

Parameters:

  • criterion (Criterion) -- The criterion of the condition.

  • duration (Duration) -- Duration target.

Returns:

The duration condition.

Return type:

RealCondition

evaluate(
self: ostk.astrodynamics.event_condition.RealCondition,
state: ostk.astrodynamics.trajectory.State,
) → ostk.core.type.Real

Evaluate the condition.

Parameters:

state (State) -- The state.

Returns:

True if the condition is satisfied, False otherwise.

Return type:

bool

get_criterion(
self: ostk.astrodynamics.event_condition.RealCondition,
) → ostk.astrodynamics.event_condition.RealCondition.Criterion

Get the criterion of the condition.

Returns:

The criterion.

Return type:

Criterion

get_evaluator(
self: ostk.astrodynamics.EventCondition,
) → Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real]

Get the evaluator of the event condition.

Returns:

The evaluator of the event condition.

Return type:

evaluator (str)

get_name(self: ostk.astrodynamics.EventCondition) → ostk.core.type.String

Get the name of the event condition.

Returns:

The name of the event condition.

Return type:

name (str)

get_target(
self: ostk.astrodynamics.EventCondition,
) → ostk.astrodynamics.EventCondition.Target

Get the target of the event condition.

Returns:

The target of the event condition.

Return type:

target (EventConditionTarget)

is_satisfied(
self: ostk.astrodynamics.event_condition.RealCondition,
current_state: ostk.astrodynamics.trajectory.State,
previous_state: ostk.astrodynamics.trajectory.State,
) → bool

Check if the condition is satisfied.

Parameters:

  • current_state (State) -- The current state.

  • previous_state (State) -- The previous state.

Returns:

True if the condition is satisfied, False otherwise.

Return type:

bool

static string_from_criterion(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
) → ostk.core.type.String

Get the string representation of a criterion.

Parameters:

criterion (Criterion) -- The criterion.

Returns:

The string representation.

Return type:

str

\ No newline at end of file + ostk.astrodynamics.event_condition.RealCondition — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.event_condition.RealCondition

class RealCondition(*args, **kwargs)

Bases: EventCondition

A Real Event Condition.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.event_condition.RealCondition, name: ostk.core.type.String, criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion, evaluator: Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real], target_value: ostk.core.type.Real = 0.0) -> None

    Constructor.

    Args:

    name (str): The name of the condition. criterion (Criterion): The criterion of the condition. evaluator (function): The evaluator of the condition. target_value (float): The target value of the condition.

  2. __init__(self: ostk.astrodynamics.event_condition.RealCondition, name: ostk.core.type.String, criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion, evaluator: Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real], target: ostk.astrodynamics.EventCondition.Target) -> None

    Constructor.

    Args:

    name (str): The name of the condition. criterion (Criterion): The criterion of the condition. evaluator (function): The evaluator of the condition. target (EventConditionTarget): The target of the condition.

Methods

duration_condition

Generate a duration condition.

evaluate

Evaluate the condition.

get_criterion

Get the criterion of the condition.

get_evaluator

Get the evaluator of the event condition.

get_name

Get the name of the event condition.

get_target

Get the target of the event condition.

is_satisfied

Check if the condition is satisfied.

string_from_criterion

Get the string representation of a criterion.

class Criterion(
self: ostk.astrodynamics.event_condition.RealCondition.Criterion,
value: int,
)

Bases: pybind11_object

The Criterion that defines how the condition is satisfied.

Members:

PositiveCrossing : The positive crossing criterion

NegativeCrossing : The negative crossing criterion

AnyCrossing : The any crossing criterion

StrictlyPositive : The strictly positive criterion

StrictlyNegative : The strictly negative criterion

property name
class Target(*args, **kwargs)

Bases: pybind11_object

The Event Condition Target.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.core.type.Real, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    value (float): The value of the target. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  2. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Length, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    length (Length): The value of the target as a Length. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

  3. __init__(self: ostk.astrodynamics.EventCondition.Target, value: ostk.physics.unit.Angle, type: ostk.astrodynamics.EventCondition.Target.Type = <Type.Absolute: 0>) -> None

    Construct a new EventConditionTarget object.

    Args:

    angle (Angle): The value of the target as an Angle. type (EventConditionTarget.Type): The type of the target. Defaults to EventConditionTarget.Type.Absolute.

    Returns:

    event_condition_target (EventConditionTarget): The new EventConditionTarget object.

static StringFromType(
arg0: ostk.astrodynamics.EventCondition.Target.Type,
) → ostk.core.type.String

Enum as a string

Parameters:

type (EventConditionTarget.Type) -- The type of the target.

Returns:

Name of the enum as a string.

Return type:

string (str)

class Type(
self: ostk.astrodynamics.EventCondition.Target.Type,
value: int,
)

Bases: pybind11_object

Event Condition Target type.

Members:

Absolute : Absolute

Relative : Relative to the provided State.

property name
property type

The type of the target.

Type:

Type

property value

The value of the target.

Type:

Real

static duration_condition(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
duration: ostk.physics.time.Duration,
) → ostk.astrodynamics.event_condition.RealCondition

Generate a duration condition.

Parameters:

  • criterion (Criterion) -- The criterion of the condition.

  • duration (Duration) -- Duration target.

Returns:

The duration condition.

Return type:

RealCondition

evaluate(
self: ostk.astrodynamics.event_condition.RealCondition,
state: ostk.astrodynamics.trajectory.State,
) → ostk.core.type.Real

Evaluate the condition.

Parameters:

state (State) -- The state.

Returns:

True if the condition is satisfied, False otherwise.

Return type:

bool

get_criterion(
self: ostk.astrodynamics.event_condition.RealCondition,
) → ostk.astrodynamics.event_condition.RealCondition.Criterion

Get the criterion of the condition.

Returns:

The criterion.

Return type:

Criterion

get_evaluator(
self: ostk.astrodynamics.EventCondition,
) → Callable[[ostk.astrodynamics.trajectory.State], ostk.core.type.Real]

Get the evaluator of the event condition.

Returns:

The evaluator of the event condition.

Return type:

evaluator (str)

get_name(self: ostk.astrodynamics.EventCondition) → ostk.core.type.String

Get the name of the event condition.

Returns:

The name of the event condition.

Return type:

name (str)

get_target(
self: ostk.astrodynamics.EventCondition,
) → ostk.astrodynamics.EventCondition.Target

Get the target of the event condition.

Returns:

The target of the event condition.

Return type:

target (EventConditionTarget)

is_satisfied(
self: ostk.astrodynamics.event_condition.RealCondition,
current_state: ostk.astrodynamics.trajectory.State,
previous_state: ostk.astrodynamics.trajectory.State,
) → bool

Check if the condition is satisfied.

Parameters:

  • current_state (State) -- The current state.

  • previous_state (State) -- The previous state.

Returns:

True if the condition is satisfied, False otherwise.

Return type:

bool

static string_from_criterion(
criterion: ostk.astrodynamics.event_condition.RealCondition.Criterion,
) → ostk.core.type.String

Get the string representation of a criterion.

Parameters:

criterion (Criterion) -- The criterion.

Returns:

The string representation.

Return type:

str

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.flight.Maneuver.html b/_build/html/_autosummary/ostk.astrodynamics.flight.Maneuver.html index 8fbbcab07..844cd08c7 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.flight.Maneuver.html +++ b/_build/html/_autosummary/ostk.astrodynamics.flight.Maneuver.html @@ -1 +1 @@ - ostk.astrodynamics.flight.Maneuver — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.Maneuver

class Maneuver(
self: ostk.astrodynamics.flight.Maneuver,
instants: List[ostk.physics.time.Instant],
acceleration_profile: List[numpy.ndarray[numpy.float64[3, 1]]],
frame: ostk.physics.coordinate.Frame,
mass_flow_rate_profile: List[ostk.core.type.Real],
)

Bases: pybind11_object

Spacecraft Maneuver class. Store an acceleration and mass flow rate profile of a spacecraft maneuver.

Constructor.

Parameters:

  • instants (list[Instant]) -- An array of instants, must be sorted.

  • acceleration_profile (list[numpy.ndarray]) -- An acceleration profile of the maneuver, one numpy.ndarray per instant in m/s^2.

  • frame (Frame) -- A frame in which the acceleration profile is defined.

  • mass_flow_rate_profile (list[float]) -- A mass flow rate profile of the maneuver (negative numbers expected), one float per instant in kg/s.

Methods

calculate_average_specific_impulse

Calculate the average specific impulse of the maneuver.

calculate_average_thrust

Calculate the average thrust of the maneuver.

calculate_delta_mass

Calculate the delta mass of the maneuver.

calculate_delta_v

Calculate the delta-v of the maneuver.

constant_mass_flow_rate_profile

Create a maneuver from a constant mass flow rate profile.

get_acceleration_profile

Get the acceleration profile.

get_instants

Get the instants.

get_interval

Get the interval of the maneuver.

get_mass_flow_rate_profile

Get the mass flow rate profile.

is_defined

Check if the maneuver is defined.

tabulated_dynamics

Create a maneuver from tabulated dynamics with cols 1-3 being acceleration and col 4 being mass flow rate.

to_tabulated_dynamics

Convert the maneuver to tabulated dynamics.

calculate_average_specific_impulse(
self: ostk.astrodynamics.flight.Maneuver,
initial_spacecraft_mass: ostk.physics.unit.Mass,
) → ostk.core.type.Real

Calculate the average specific impulse of the maneuver.

Parameters:

initial_spacecraft_mass (Mass) -- The initial mass of the spacecraft.

Returns:

The average specific impulse (s).

Return type:

float

calculate_average_thrust(
self: ostk.astrodynamics.flight.Maneuver,
initial_spacecraft_mass: ostk.physics.unit.Mass,
) → ostk.core.type.Real

Calculate the average thrust of the maneuver.

Parameters:

initial_spacecraft_mass (Mass) -- The initial mass of the spacecraft.

Returns:

The average thrust (N).

Return type:

float

calculate_delta_mass(
self: ostk.astrodynamics.flight.Maneuver,
) → ostk.physics.unit.Mass

Calculate the delta mass of the maneuver.

Returns:

The delta mass (always positive) (kg).

Return type:

Mass

calculate_delta_v(
self: ostk.astrodynamics.flight.Maneuver,
) → ostk.core.type.Real

Calculate the delta-v of the maneuver.

Returns:

The delta-v value (m/s).

Return type:

float

static constant_mass_flow_rate_profile(
instants: List[ostk.physics.time.Instant],
acceleration_profile: List[numpy.ndarray[numpy.float64[3, 1]]],
frame: ostk.physics.coordinate.Frame,
mass_flow_rate: ostk.core.type.Real,
) → ostk.astrodynamics.flight.Maneuver

Create a maneuver from a constant mass flow rate profile.

Parameters:

  • instants (list[Instant]) -- An array of instants, must be sorted.

  • acceleration_profile (list[numpy.ndarray]) -- An acceleration profile of the maneuver, one numpy.ndarray per instant.

  • frame (Frame) -- A frame in which the acceleration profile is defined.

  • mass_flow_rate (float) -- The constant mass flow rate (negative number expected).

Returns:

The created maneuver.

Return type:

Maneuver

get_acceleration_profile(
self: ostk.astrodynamics.flight.Maneuver,
frame: ostk.physics.coordinate.Frame = GCRF,
) → List[numpy.ndarray[numpy.float64[3, 1]]]

Get the acceleration profile.

Parameters:

frame (Frame, optional) -- The frame in which the acceleration profile is defined. Defaults to the default acceleration frame.

Returns:

The acceleration profile (m/s^2).

Return type:

list[numpy.ndarray]

get_instants(
self: ostk.astrodynamics.flight.Maneuver,
) → List[ostk.physics.time.Instant]

Get the instants.

Returns:

The instants.

Return type:

list[Instant]

get_interval(
self: ostk.astrodynamics.flight.Maneuver,
) → ostk.physics.time.Interval

Get the interval of the maneuver.

Returns:

The interval.

Return type:

Interval

get_mass_flow_rate_profile(
self: ostk.astrodynamics.flight.Maneuver,
) → List[ostk.core.type.Real]

Get the mass flow rate profile.

Returns:

The mass flow rate profile (kg/s).

Return type:

list[float]

is_defined(self: ostk.astrodynamics.flight.Maneuver) → bool

Check if the maneuver is defined.

Returns:

True if the maneuver is defined, False otherwise. (Always returns true).

Return type:

bool

static tabulated_dynamics(
tabulated_dynamics: ostk::astrodynamics::dynamics::Tabulated,
) → ostk.astrodynamics.flight.Maneuver

Create a maneuver from tabulated dynamics with cols 1-3 being acceleration and col 4 being mass flow rate.

Parameters:

tabulated_dynamics (Tabulated) -- The tabulated dynamics.

Returns:

The created maneuver.

Return type:

Maneuver

to_tabulated_dynamics(
self: ostk.astrodynamics.flight.Maneuver,
frame: ostk.physics.coordinate.Frame = GCRF,
interpolation_type: ostk.mathematics.curve_fitting.Interpolator.Type = <Type.BarycentricRational: 0>,
) → ostk::astrodynamics::dynamics::Tabulated

Convert the maneuver to tabulated dynamics.

Parameters:

  • frame (Frame, optional) -- The frame in which the acceleration profile is defined. Defaults to the default acceleration frame.

  • interpolation_type (Interpolator.Type, optional) -- The interpolation type to use. Defaults to the default interpolation type.

Returns:

The tabulated dynamics.

Return type:

Tabulated

\ No newline at end of file + ostk.astrodynamics.flight.Maneuver — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.Maneuver

class Maneuver(
self: ostk.astrodynamics.flight.Maneuver,
instants: List[ostk.physics.time.Instant],
acceleration_profile: List[numpy.ndarray[numpy.float64[3, 1]]],
frame: ostk.physics.coordinate.Frame,
mass_flow_rate_profile: List[ostk.core.type.Real],
)

Bases: pybind11_object

Spacecraft Maneuver class. Store an acceleration and mass flow rate profile of a spacecraft maneuver.

Constructor.

Parameters:

  • instants (list[Instant]) -- An array of instants, must be sorted.

  • acceleration_profile (list[numpy.ndarray]) -- An acceleration profile of the maneuver, one numpy.ndarray per instant in m/s^2.

  • frame (Frame) -- A frame in which the acceleration profile is defined.

  • mass_flow_rate_profile (list[float]) -- A mass flow rate profile of the maneuver (negative numbers expected), one float per instant in kg/s.

Methods

calculate_average_specific_impulse

Calculate the average specific impulse of the maneuver.

calculate_average_thrust

Calculate the average thrust of the maneuver.

calculate_delta_mass

Calculate the delta mass of the maneuver.

calculate_delta_v

Calculate the delta-v of the maneuver.

constant_mass_flow_rate_profile

Create a maneuver from a constant mass flow rate profile.

get_acceleration_profile

Get the acceleration profile.

get_instants

Get the instants.

get_interval

Get the interval of the maneuver.

get_mass_flow_rate_profile

Get the mass flow rate profile.

is_defined

Check if the maneuver is defined.

tabulated_dynamics

Create a maneuver from tabulated dynamics with cols 1-3 being acceleration and col 4 being mass flow rate.

to_tabulated_dynamics

Convert the maneuver to tabulated dynamics.

calculate_average_specific_impulse(
self: ostk.astrodynamics.flight.Maneuver,
initial_spacecraft_mass: ostk.physics.unit.Mass,
) → ostk.core.type.Real

Calculate the average specific impulse of the maneuver.

Parameters:

initial_spacecraft_mass (Mass) -- The initial mass of the spacecraft.

Returns:

The average specific impulse (s).

Return type:

float

calculate_average_thrust(
self: ostk.astrodynamics.flight.Maneuver,
initial_spacecraft_mass: ostk.physics.unit.Mass,
) → ostk.core.type.Real

Calculate the average thrust of the maneuver.

Parameters:

initial_spacecraft_mass (Mass) -- The initial mass of the spacecraft.

Returns:

The average thrust (N).

Return type:

float

calculate_delta_mass(
self: ostk.astrodynamics.flight.Maneuver,
) → ostk.physics.unit.Mass

Calculate the delta mass of the maneuver.

Returns:

The delta mass (always positive) (kg).

Return type:

Mass

calculate_delta_v(
self: ostk.astrodynamics.flight.Maneuver,
) → ostk.core.type.Real

Calculate the delta-v of the maneuver.

Returns:

The delta-v value (m/s).

Return type:

float

static constant_mass_flow_rate_profile(
instants: List[ostk.physics.time.Instant],
acceleration_profile: List[numpy.ndarray[numpy.float64[3, 1]]],
frame: ostk.physics.coordinate.Frame,
mass_flow_rate: ostk.core.type.Real,
) → ostk.astrodynamics.flight.Maneuver

Create a maneuver from a constant mass flow rate profile.

Parameters:

  • instants (list[Instant]) -- An array of instants, must be sorted.

  • acceleration_profile (list[numpy.ndarray]) -- An acceleration profile of the maneuver, one numpy.ndarray per instant.

  • frame (Frame) -- A frame in which the acceleration profile is defined.

  • mass_flow_rate (float) -- The constant mass flow rate (negative number expected).

Returns:

The created maneuver.

Return type:

Maneuver

get_acceleration_profile(
self: ostk.astrodynamics.flight.Maneuver,
frame: ostk.physics.coordinate.Frame = GCRF,
) → List[numpy.ndarray[numpy.float64[3, 1]]]

Get the acceleration profile.

Parameters:

frame (Frame, optional) -- The frame in which the acceleration profile is defined. Defaults to the default acceleration frame.

Returns:

The acceleration profile (m/s^2).

Return type:

list[numpy.ndarray]

get_instants(
self: ostk.astrodynamics.flight.Maneuver,
) → List[ostk.physics.time.Instant]

Get the instants.

Returns:

The instants.

Return type:

list[Instant]

get_interval(
self: ostk.astrodynamics.flight.Maneuver,
) → ostk.physics.time.Interval

Get the interval of the maneuver.

Returns:

The interval.

Return type:

Interval

get_mass_flow_rate_profile(
self: ostk.astrodynamics.flight.Maneuver,
) → List[ostk.core.type.Real]

Get the mass flow rate profile.

Returns:

The mass flow rate profile (kg/s).

Return type:

list[float]

is_defined(self: ostk.astrodynamics.flight.Maneuver) → bool

Check if the maneuver is defined.

Returns:

True if the maneuver is defined, False otherwise. (Always returns true).

Return type:

bool

static tabulated_dynamics(
tabulated_dynamics: ostk::astrodynamics::dynamics::Tabulated,
) → ostk.astrodynamics.flight.Maneuver

Create a maneuver from tabulated dynamics with cols 1-3 being acceleration and col 4 being mass flow rate.

Parameters:

tabulated_dynamics (Tabulated) -- The tabulated dynamics.

Returns:

The created maneuver.

Return type:

Maneuver

to_tabulated_dynamics(
self: ostk.astrodynamics.flight.Maneuver,
frame: ostk.physics.coordinate.Frame = GCRF,
interpolation_type: ostk.mathematics.curve_fitting.Interpolator.Type = <Type.BarycentricRational: 0>,
) → ostk::astrodynamics::dynamics::Tabulated

Convert the maneuver to tabulated dynamics.

Parameters:

  • frame (Frame, optional) -- The frame in which the acceleration profile is defined. Defaults to the default acceleration frame.

  • interpolation_type (Interpolator.Type, optional) -- The interpolation type to use. Defaults to the default interpolation type.

Returns:

The tabulated dynamics.

Return type:

Tabulated

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.flight.Profile.html b/_build/html/_autosummary/ostk.astrodynamics.flight.Profile.html index ba312f6fe..e8fe2f87f 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.flight.Profile.html +++ b/_build/html/_autosummary/ostk.astrodynamics.flight.Profile.html @@ -1 +1 @@ - ostk.astrodynamics.flight.Profile — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.Profile

class Profile(
self: ostk.astrodynamics.flight.Profile,
model: ostk::astrodynamics::flight::profile::Model,
)

Bases: pybind11_object

Spacecraft Flight Profile.

Constructor.

Parameters:

model (Model) -- The profile model.

Methods

get_axes_at

Get the axes of the profile at a given instant.

get_body_frame

Get the body frame of the profile.

get_state_at

Get the state of the profile at a given instant.

get_states_at

Get the states of the profile at given instants.

inertial_pointing

Create an inertial pointing profile.

is_defined

Check if the profile is defined.

nadir_pointing

Create a nadir pointing profile.

undefined

Create an undefined profile.

get_axes_at(
self: ostk.astrodynamics.flight.Profile,
instant: ostk.physics.time.Instant,
) → ostk.physics.coordinate.Axes

Get the axes of the profile at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The axes of the profile at the given instant.

Return type:

Frame

get_body_frame(
self: ostk.astrodynamics.flight.Profile,
frame_name: ostk.core.type.String,
) → ostk.physics.coordinate.Frame

Get the body frame of the profile.

Parameters:

frame_name (str) -- The name of the frame.

Returns:

The body frame of the profile.

Return type:

Frame

get_state_at(
self: ostk.astrodynamics.flight.Profile,
instant: ostk.physics.time.Instant,
) → ostk::astrodynamics::trajectory::State

Get the state of the profile at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state of the profile at the given instant.

Return type:

State

get_states_at(
self: ostk.astrodynamics.flight.Profile,
instants: List[ostk.physics.time.Instant],
) → List[ostk::astrodynamics::trajectory::State]

Get the states of the profile at given instants.

Parameters:

instants (list) -- The instants.

Returns:

The states of the profile at the given instants.

Return type:

list

static inertial_pointing(
trajectory: ostk::astrodynamics::Trajectory,
quaternion: ostk.mathematics.geometry.d3.transformation.rotation.Quaternion,
) → ostk.astrodynamics.flight.Profile

Create an inertial pointing profile.

Parameters:

  • trajectory (Trajectory) -- The trajectory.

  • quaternion (Quaternion) -- The quaternion.

Returns:

The inertial pointing profile.

Return type:

Profile

is_defined(self: ostk.astrodynamics.flight.Profile) → bool

Check if the profile is defined.

Returns:

True if the profile is defined, False otherwise.

Return type:

bool

static nadir_pointing(
orbit: ostk::astrodynamics::trajectory::Orbit,
orbital_frame_type: ostk::astrodynamics::trajectory::Orbit::FrameType,
) → ostk.astrodynamics.flight.Profile

Create a nadir pointing profile.

Parameters:

  • orbit (Orbit) -- The orbit.

  • orbital_frame_type (OrbitalFrameType) -- The type of the orbital frame.

Returns:

The nadir pointing profile.

Return type:

Profile

static undefined() → ostk.astrodynamics.flight.Profile

Create an undefined profile.

Returns:

The undefined profile.

Return type:

Profile

\ No newline at end of file + ostk.astrodynamics.flight.Profile — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.Profile

class Profile(
self: ostk.astrodynamics.flight.Profile,
model: ostk::astrodynamics::flight::profile::Model,
)

Bases: pybind11_object

Spacecraft Flight Profile.

Constructor.

Parameters:

model (Model) -- The profile model.

Methods

get_axes_at

Get the axes of the profile at a given instant.

get_body_frame

Get the body frame of the profile.

get_state_at

Get the state of the profile at a given instant.

get_states_at

Get the states of the profile at given instants.

inertial_pointing

Create an inertial pointing profile.

is_defined

Check if the profile is defined.

nadir_pointing

Create a nadir pointing profile.

undefined

Create an undefined profile.

get_axes_at(
self: ostk.astrodynamics.flight.Profile,
instant: ostk.physics.time.Instant,
) → ostk.physics.coordinate.Axes

Get the axes of the profile at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The axes of the profile at the given instant.

Return type:

Frame

get_body_frame(
self: ostk.astrodynamics.flight.Profile,
frame_name: ostk.core.type.String,
) → ostk.physics.coordinate.Frame

Get the body frame of the profile.

Parameters:

frame_name (str) -- The name of the frame.

Returns:

The body frame of the profile.

Return type:

Frame

get_state_at(
self: ostk.astrodynamics.flight.Profile,
instant: ostk.physics.time.Instant,
) → ostk::astrodynamics::trajectory::State

Get the state of the profile at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state of the profile at the given instant.

Return type:

State

get_states_at(
self: ostk.astrodynamics.flight.Profile,
instants: List[ostk.physics.time.Instant],
) → List[ostk::astrodynamics::trajectory::State]

Get the states of the profile at given instants.

Parameters:

instants (list) -- The instants.

Returns:

The states of the profile at the given instants.

Return type:

list

static inertial_pointing(
trajectory: ostk::astrodynamics::Trajectory,
quaternion: ostk.mathematics.geometry.d3.transformation.rotation.Quaternion,
) → ostk.astrodynamics.flight.Profile

Create an inertial pointing profile.

Parameters:

  • trajectory (Trajectory) -- The trajectory.

  • quaternion (Quaternion) -- The quaternion.

Returns:

The inertial pointing profile.

Return type:

Profile

is_defined(self: ostk.astrodynamics.flight.Profile) → bool

Check if the profile is defined.

Returns:

True if the profile is defined, False otherwise.

Return type:

bool

static nadir_pointing(
orbit: ostk::astrodynamics::trajectory::Orbit,
orbital_frame_type: ostk::astrodynamics::trajectory::Orbit::FrameType,
) → ostk.astrodynamics.flight.Profile

Create a nadir pointing profile.

Parameters:

  • orbit (Orbit) -- The orbit.

  • orbital_frame_type (OrbitalFrameType) -- The type of the orbital frame.

Returns:

The nadir pointing profile.

Return type:

Profile

static undefined() → ostk.astrodynamics.flight.Profile

Create an undefined profile.

Returns:

The undefined profile.

Return type:

Profile

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.flight.System.html b/_build/html/_autosummary/ostk.astrodynamics.flight.System.html index 378854909..7b79cb273 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.flight.System.html +++ b/_build/html/_autosummary/ostk.astrodynamics.flight.System.html @@ -1 +1 @@ - ostk.astrodynamics.flight.System — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.System

class System(
self: ostk.astrodynamics.flight.System,
mass: ostk.physics.unit.Mass,
geometry: ostk.mathematics.geometry.d3.object.Composite,
)

Bases: pybind11_object

A flight system.

Provides the interface for flight systems.

Warning

This class is an abstract class and cannot be instantiated.

Constructor.

Parameters:

  • mass (Mass) -- The mass of the system.

  • geometry (Composite) -- The geometry of the system.

Methods

get_geometry

Get the geometry of the system.

get_mass

Get the mass of the system.

is_defined

Check if the system is defined.

undefined

Create an undefined system.

get_geometry(
self: ostk.astrodynamics.flight.System,
) → ostk.mathematics.geometry.d3.object.Composite

Get the geometry of the system.

Returns:

The geometry of the system.

Return type:

Composite

get_mass(self: ostk.astrodynamics.flight.System) → ostk.physics.unit.Mass

Get the mass of the system.

Returns:

The mass of the system.

Return type:

Mass

is_defined(self: ostk.astrodynamics.flight.System) → bool

Check if the system is defined.

Returns:

True if the system is defined, False otherwise.

Return type:

bool

static undefined() → ostk.astrodynamics.flight.System

Create an undefined system.

Returns:

The undefined system.

Return type:

System

\ No newline at end of file + ostk.astrodynamics.flight.System — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.System

class System(
self: ostk.astrodynamics.flight.System,
mass: ostk.physics.unit.Mass,
geometry: ostk.mathematics.geometry.d3.object.Composite,
)

Bases: pybind11_object

A flight system.

Provides the interface for flight systems.

Warning

This class is an abstract class and cannot be instantiated.

Constructor.

Parameters:

  • mass (Mass) -- The mass of the system.

  • geometry (Composite) -- The geometry of the system.

Methods

get_geometry

Get the geometry of the system.

get_mass

Get the mass of the system.

is_defined

Check if the system is defined.

undefined

Create an undefined system.

get_geometry(
self: ostk.astrodynamics.flight.System,
) → ostk.mathematics.geometry.d3.object.Composite

Get the geometry of the system.

Returns:

The geometry of the system.

Return type:

Composite

get_mass(self: ostk.astrodynamics.flight.System) → ostk.physics.unit.Mass

Get the mass of the system.

Returns:

The mass of the system.

Return type:

Mass

is_defined(self: ostk.astrodynamics.flight.System) → bool

Check if the system is defined.

Returns:

True if the system is defined, False otherwise.

Return type:

bool

static undefined() → ostk.astrodynamics.flight.System

Create an undefined system.

Returns:

The undefined system.

Return type:

System

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.flight.profile.Model.html b/_build/html/_autosummary/ostk.astrodynamics.flight.profile.Model.html index d60f53427..d3049d7eb 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.flight.profile.Model.html +++ b/_build/html/_autosummary/ostk.astrodynamics.flight.profile.Model.html @@ -1 +1 @@ - ostk.astrodynamics.flight.profile.Model — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.profile.Model

class Model

Bases: pybind11_object

A flight profile model.

Methods

calculate_state_at

Calculate the state of the model at a specific instant.

calculate_states_at

Calculate the states of the model at specific instants.

get_axes_at

Get the axes of the model at a specific instant.

get_body_frame

Get the body frame of the model with the specified name.

is_defined

Check if the model is defined.

calculate_state_at(
self: ostk.astrodynamics.flight.profile.Model,
instant: ostk.physics.time.Instant,
) → ostk::astrodynamics::trajectory::State

Calculate the state of the model at a specific instant.

Parameters:

instant (Instant) -- The instant at which to calculate the state.

Returns:

The state of the model at the specified instant.

Return type:

State

calculate_states_at(
self: ostk.astrodynamics.flight.profile.Model,
instants: List[ostk.physics.time.Instant],
) → List[ostk::astrodynamics::trajectory::State]

Calculate the states of the model at specific instants. It can be more performant than looping calculate_state_at for multiple instants.

Parameters:

instants (list[Instant]) -- The instants at which to calculate the states.

Returns:

The states of the model at the specified instants.

Return type:

list[State]

get_axes_at(
self: ostk.astrodynamics.flight.profile.Model,
instant: ostk.physics.time.Instant,
) → ostk.physics.coordinate.Axes

Get the axes of the model at a specific instant.

Parameters:

instant (Instant) -- The instant at which to get the axes.

Returns:

The axes of the model at the specified instant.

Return type:

numpy.ndarray

get_body_frame(
self: ostk.astrodynamics.flight.profile.Model,
frame_name: ostk.core.type.String,
) → ostk.physics.coordinate.Frame

Get the body frame of the model with the specified name.

Parameters:

frame_name (str) -- The name of the body frame.

Returns:

The body frame of the model with the specified name.

Return type:

Frame

is_defined(self: ostk.astrodynamics.flight.profile.Model) → bool

Check if the model is defined.

Returns:

True if the model is defined, False otherwise.

Return type:

bool

\ No newline at end of file + ostk.astrodynamics.flight.profile.Model — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.profile.Model

class Model

Bases: pybind11_object

A flight profile model.

Methods

calculate_state_at

Calculate the state of the model at a specific instant.

calculate_states_at

Calculate the states of the model at specific instants.

get_axes_at

Get the axes of the model at a specific instant.

get_body_frame

Get the body frame of the model with the specified name.

is_defined

Check if the model is defined.

calculate_state_at(
self: ostk.astrodynamics.flight.profile.Model,
instant: ostk.physics.time.Instant,
) → ostk::astrodynamics::trajectory::State

Calculate the state of the model at a specific instant.

Parameters:

instant (Instant) -- The instant at which to calculate the state.

Returns:

The state of the model at the specified instant.

Return type:

State

calculate_states_at(
self: ostk.astrodynamics.flight.profile.Model,
instants: List[ostk.physics.time.Instant],
) → List[ostk::astrodynamics::trajectory::State]

Calculate the states of the model at specific instants. It can be more performant than looping calculate_state_at for multiple instants.

Parameters:

instants (list[Instant]) -- The instants at which to calculate the states.

Returns:

The states of the model at the specified instants.

Return type:

list[State]

get_axes_at(
self: ostk.astrodynamics.flight.profile.Model,
instant: ostk.physics.time.Instant,
) → ostk.physics.coordinate.Axes

Get the axes of the model at a specific instant.

Parameters:

instant (Instant) -- The instant at which to get the axes.

Returns:

The axes of the model at the specified instant.

Return type:

numpy.ndarray

get_body_frame(
self: ostk.astrodynamics.flight.profile.Model,
frame_name: ostk.core.type.String,
) → ostk.physics.coordinate.Frame

Get the body frame of the model with the specified name.

Parameters:

frame_name (str) -- The name of the body frame.

Returns:

The body frame of the model with the specified name.

Return type:

Frame

is_defined(self: ostk.astrodynamics.flight.profile.Model) → bool

Check if the model is defined.

Returns:

True if the model is defined, False otherwise.

Return type:

bool

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.flight.profile.model.Tabulated.html b/_build/html/_autosummary/ostk.astrodynamics.flight.profile.model.Tabulated.html index 0f1c939aa..fc01f055a 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.flight.profile.model.Tabulated.html +++ b/_build/html/_autosummary/ostk.astrodynamics.flight.profile.model.Tabulated.html @@ -1 +1 @@ - ostk.astrodynamics.flight.profile.model.Tabulated — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.profile.model.Tabulated

class Tabulated(self: ostk.astrodynamics.flight.profile.model.Tabulated, states: List[ostk::astrodynamics::trajectory::State])

Bases: Model

A flight profile model defined by a set of states.

Constructor.

Parameters:

states (Array[State]) -- The states of the model.

Methods

calculate_state_at

Calculate the state of the model at a specific instant.

calculate_states_at

Calculate the states of the model at specific instants.

get_axes_at

Get the axes of the model at a specific instant.

get_body_frame

Get the body frame of the model with the specified name.

get_interval

Get the interval of the model.

is_defined

Check if the model is defined.

calculate_state_at(
self: ostk.astrodynamics.flight.profile.model.Tabulated,
instant: ostk.physics.time.Instant,
) → ostk::astrodynamics::trajectory::State

Calculate the state of the model at a specific instant.

Parameters:

instant (Instant) -- The instant at which to calculate the state.

Returns:

The state of the model at the specified instant.

Return type:

State

calculate_states_at(
self: ostk.astrodynamics.flight.profile.Model,
instants: List[ostk.physics.time.Instant],
) → List[ostk::astrodynamics::trajectory::State]

Calculate the states of the model at specific instants. It can be more performant than looping calculate_state_at for multiple instants.

Parameters:

instants (list[Instant]) -- The instants at which to calculate the states.

Returns:

The states of the model at the specified instants.

Return type:

list[State]

get_axes_at(
self: ostk.astrodynamics.flight.profile.model.Tabulated,
instant: ostk.physics.time.Instant,
) → ostk.physics.coordinate.Axes

Get the axes of the model at a specific instant.

Parameters:

instant (Instant) -- The instant at which to get the axes.

Returns:

The axes of the model at the specified instant.

Return type:

numpy.ndarray

get_body_frame(
self: ostk.astrodynamics.flight.profile.model.Tabulated,
frame_name: ostk.core.type.String,
) → ostk.physics.coordinate.Frame

Get the body frame of the model with the specified name.

Parameters:

frame_name (str) -- The name of the body frame.

Returns:

The body frame of the model with the specified name.

Return type:

Frame

get_interval(
self: ostk.astrodynamics.flight.profile.model.Tabulated,
) → ostk.physics.time.Interval

Get the interval of the model.

Returns:

The interval of the model.

Return type:

Interval

is_defined(self: ostk.astrodynamics.flight.profile.model.Tabulated) → bool

Check if the model is defined.

Returns:

True if the model is defined, False otherwise.

Return type:

bool

\ No newline at end of file + ostk.astrodynamics.flight.profile.model.Tabulated — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.profile.model.Tabulated

class Tabulated(self: ostk.astrodynamics.flight.profile.model.Tabulated, states: List[ostk::astrodynamics::trajectory::State])

Bases: Model

A flight profile model defined by a set of states.

Constructor.

Parameters:

states (Array[State]) -- The states of the model.

Methods

calculate_state_at

Calculate the state of the model at a specific instant.

calculate_states_at

Calculate the states of the model at specific instants.

get_axes_at

Get the axes of the model at a specific instant.

get_body_frame

Get the body frame of the model with the specified name.

get_interval

Get the interval of the model.

is_defined

Check if the model is defined.

calculate_state_at(
self: ostk.astrodynamics.flight.profile.model.Tabulated,
instant: ostk.physics.time.Instant,
) → ostk::astrodynamics::trajectory::State

Calculate the state of the model at a specific instant.

Parameters:

instant (Instant) -- The instant at which to calculate the state.

Returns:

The state of the model at the specified instant.

Return type:

State

calculate_states_at(
self: ostk.astrodynamics.flight.profile.Model,
instants: List[ostk.physics.time.Instant],
) → List[ostk::astrodynamics::trajectory::State]

Calculate the states of the model at specific instants. It can be more performant than looping calculate_state_at for multiple instants.

Parameters:

instants (list[Instant]) -- The instants at which to calculate the states.

Returns:

The states of the model at the specified instants.

Return type:

list[State]

get_axes_at(
self: ostk.astrodynamics.flight.profile.model.Tabulated,
instant: ostk.physics.time.Instant,
) → ostk.physics.coordinate.Axes

Get the axes of the model at a specific instant.

Parameters:

instant (Instant) -- The instant at which to get the axes.

Returns:

The axes of the model at the specified instant.

Return type:

numpy.ndarray

get_body_frame(
self: ostk.astrodynamics.flight.profile.model.Tabulated,
frame_name: ostk.core.type.String,
) → ostk.physics.coordinate.Frame

Get the body frame of the model with the specified name.

Parameters:

frame_name (str) -- The name of the body frame.

Returns:

The body frame of the model with the specified name.

Return type:

Frame

get_interval(
self: ostk.astrodynamics.flight.profile.model.Tabulated,
) → ostk.physics.time.Interval

Get the interval of the model.

Returns:

The interval of the model.

Return type:

Interval

is_defined(self: ostk.astrodynamics.flight.profile.model.Tabulated) → bool

Check if the model is defined.

Returns:

True if the model is defined, False otherwise.

Return type:

bool

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.flight.profile.model.Transform.html b/_build/html/_autosummary/ostk.astrodynamics.flight.profile.model.Transform.html index ea6955f6e..4e19b915c 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.flight.profile.model.Transform.html +++ b/_build/html/_autosummary/ostk.astrodynamics.flight.profile.model.Transform.html @@ -1 +1 @@ - ostk.astrodynamics.flight.profile.model.Transform — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.profile.model.Transform

class Transform(
self: ostk.astrodynamics.flight.profile.model.Transform,
dynamic_provider: ostk.physics.coordinate.frame.provider.Dynamic,
frame: ostk.physics.coordinate.Frame,
)

Bases: Model

A flight profile model defined by a transform.

Constructor.

Parameters:

  • dynamic_provider (DynamicProvider) -- The dynamic provider of the transform.

  • frame (Frame) -- The frame of the transform.

Methods

calculate_state_at

Calculate the state of the model at a specific instant.

calculate_states_at

Calculate the states of the model at specific instants.

get_axes_at

Get the axes of the model at a specific instant.

get_body_frame

Get the body frame of the model with the specified name.

inertial_pointing

Create a transform for inertial pointing.

is_defined

Check if the model is defined.

nadir_pointing

Create a transform for nadir pointing.

undefined

Get an undefined transform.

calculate_state_at(
self: ostk.astrodynamics.flight.profile.model.Transform,
instant: ostk.physics.time.Instant,
) → ostk::astrodynamics::trajectory::State

Calculate the state of the model at a specific instant.

Parameters:

instant (Instant) -- The instant at which to calculate the state.

Returns:

The state of the model at the specified instant.

Return type:

State

calculate_states_at(
self: ostk.astrodynamics.flight.profile.Model,
instants: List[ostk.physics.time.Instant],
) → List[ostk::astrodynamics::trajectory::State]

Calculate the states of the model at specific instants. It can be more performant than looping calculate_state_at for multiple instants.

Parameters:

instants (list[Instant]) -- The instants at which to calculate the states.

Returns:

The states of the model at the specified instants.

Return type:

list[State]

get_axes_at(
self: ostk.astrodynamics.flight.profile.model.Transform,
instant: ostk.physics.time.Instant,
) → ostk.physics.coordinate.Axes

Get the axes of the model at a specific instant.

Parameters:

instant (Instant) -- The instant at which to get the axes.

Returns:

The axes of the model at the specified instant.

Return type:

numpy.ndarray

get_body_frame(
self: ostk.astrodynamics.flight.profile.model.Transform,
frame_name: ostk.core.type.String,
) → ostk.physics.coordinate.Frame

Get the body frame of the model with the specified name.

Parameters:

frame_name (str) -- The name of the body frame.

Returns:

The body frame of the model with the specified name.

Return type:

Frame

static inertial_pointing(
trajectory: ostk::astrodynamics::Trajectory,
quaternion: ostk.mathematics.geometry.d3.transformation.rotation.Quaternion,
) → ostk.astrodynamics.flight.profile.model.Transform

Create a transform for inertial pointing.

Parameters:

  • trajectory (Trajectory) -- The trajectory to point at.

  • quaternion (Quaternion) -- The quaternion to rotate the axes by.

Returns:

The transform for inertial pointing.

Return type:

Transform

is_defined(self: ostk.astrodynamics.flight.profile.model.Transform) → bool

Check if the model is defined.

Returns:

True if the model is defined, False otherwise.

Return type:

bool

static nadir_pointing(
orbit: ostk::astrodynamics::trajectory::Orbit,
orbital_frame_type: ostk::astrodynamics::trajectory::Orbit::FrameType,
) → ostk.astrodynamics.flight.profile.model.Transform

Create a transform for nadir pointing.

Parameters:

  • orbit (Orbit) -- The orbit to point at.

  • orbital_frame_type (OrbitalFrameType) -- The type of the orbital frame.

Returns:

The transform for nadir pointing.

Return type:

Transform

static undefined() → ostk.astrodynamics.flight.profile.model.Transform

Get an undefined transform.

Returns:

The undefined transform.

Return type:

Transform

\ No newline at end of file + ostk.astrodynamics.flight.profile.model.Transform — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.profile.model.Transform

class Transform(
self: ostk.astrodynamics.flight.profile.model.Transform,
dynamic_provider: ostk.physics.coordinate.frame.provider.Dynamic,
frame: ostk.physics.coordinate.Frame,
)

Bases: Model

A flight profile model defined by a transform.

Constructor.

Parameters:

  • dynamic_provider (DynamicProvider) -- The dynamic provider of the transform.

  • frame (Frame) -- The frame of the transform.

Methods

calculate_state_at

Calculate the state of the model at a specific instant.

calculate_states_at

Calculate the states of the model at specific instants.

get_axes_at

Get the axes of the model at a specific instant.

get_body_frame

Get the body frame of the model with the specified name.

inertial_pointing

Create a transform for inertial pointing.

is_defined

Check if the model is defined.

nadir_pointing

Create a transform for nadir pointing.

undefined

Get an undefined transform.

calculate_state_at(
self: ostk.astrodynamics.flight.profile.model.Transform,
instant: ostk.physics.time.Instant,
) → ostk::astrodynamics::trajectory::State

Calculate the state of the model at a specific instant.

Parameters:

instant (Instant) -- The instant at which to calculate the state.

Returns:

The state of the model at the specified instant.

Return type:

State

calculate_states_at(
self: ostk.astrodynamics.flight.profile.Model,
instants: List[ostk.physics.time.Instant],
) → List[ostk::astrodynamics::trajectory::State]

Calculate the states of the model at specific instants. It can be more performant than looping calculate_state_at for multiple instants.

Parameters:

instants (list[Instant]) -- The instants at which to calculate the states.

Returns:

The states of the model at the specified instants.

Return type:

list[State]

get_axes_at(
self: ostk.astrodynamics.flight.profile.model.Transform,
instant: ostk.physics.time.Instant,
) → ostk.physics.coordinate.Axes

Get the axes of the model at a specific instant.

Parameters:

instant (Instant) -- The instant at which to get the axes.

Returns:

The axes of the model at the specified instant.

Return type:

numpy.ndarray

get_body_frame(
self: ostk.astrodynamics.flight.profile.model.Transform,
frame_name: ostk.core.type.String,
) → ostk.physics.coordinate.Frame

Get the body frame of the model with the specified name.

Parameters:

frame_name (str) -- The name of the body frame.

Returns:

The body frame of the model with the specified name.

Return type:

Frame

static inertial_pointing(
trajectory: ostk::astrodynamics::Trajectory,
quaternion: ostk.mathematics.geometry.d3.transformation.rotation.Quaternion,
) → ostk.astrodynamics.flight.profile.model.Transform

Create a transform for inertial pointing.

Parameters:

  • trajectory (Trajectory) -- The trajectory to point at.

  • quaternion (Quaternion) -- The quaternion to rotate the axes by.

Returns:

The transform for inertial pointing.

Return type:

Transform

is_defined(self: ostk.astrodynamics.flight.profile.model.Transform) → bool

Check if the model is defined.

Returns:

True if the model is defined, False otherwise.

Return type:

bool

static nadir_pointing(
orbit: ostk::astrodynamics::trajectory::Orbit,
orbital_frame_type: ostk::astrodynamics::trajectory::Orbit::FrameType,
) → ostk.astrodynamics.flight.profile.model.Transform

Create a transform for nadir pointing.

Parameters:

  • orbit (Orbit) -- The orbit to point at.

  • orbital_frame_type (OrbitalFrameType) -- The type of the orbital frame.

Returns:

The transform for nadir pointing.

Return type:

Transform

static undefined() → ostk.astrodynamics.flight.profile.model.Transform

Get an undefined transform.

Returns:

The undefined transform.

Return type:

Transform

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.flight.system.PropulsionSystem.html b/_build/html/_autosummary/ostk.astrodynamics.flight.system.PropulsionSystem.html index 4f67bd6ea..4cb0c25a9 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.flight.system.PropulsionSystem.html +++ b/_build/html/_autosummary/ostk.astrodynamics.flight.system.PropulsionSystem.html @@ -1 +1 @@ - ostk.astrodynamics.flight.system.PropulsionSystem — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.system.PropulsionSystem

class PropulsionSystem(
self: ostk.astrodynamics.flight.system.PropulsionSystem,
thrust_si_unit: ostk.core.type.Real,
specific_impulse_si_unit: ostk.core.type.Real,
)

Bases: pybind11_object

A propulsion system.

Construct a propulsion system.

Parameters:

  • thrust (float) -- Thrust in Newton.

  • specific_impulse (float) -- Specific impulse in Seconds.

Methods

default

Return a default propulsion system.

get_acceleration

Return the acceleration.

get_mass_flow_rate

Return the mass flow rate.

get_specific_impulse

Return the specific impulse.

get_thrust

Return the thrust.

is_defined

Check if the propulsion system is defined.

undefined

Return an undefined propulsion system.

static default() → ostk.astrodynamics.flight.system.PropulsionSystem

Return a default propulsion system.

Returns:

A default propulsion system.

Return type:

PropulsionSystem

get_acceleration(
self: ostk.astrodynamics.flight.system.PropulsionSystem,
mass: ostk.physics.unit.Mass,
) → ostk.core.type.Real

Return the acceleration.

Parameters:

mass (float) -- Mass in Kilograms.

Returns:

The acceleration in Meters per Second squared.

Return type:

float

get_mass_flow_rate(
self: ostk.astrodynamics.flight.system.PropulsionSystem,
) → ostk.core.type.Real

Return the mass flow rate.

Returns:

The mass flow rate in Kilograms per Second.

Return type:

float

get_specific_impulse(
self: ostk.astrodynamics.flight.system.PropulsionSystem,
) → ostk.core.type.Real

Return the specific impulse.

Returns:

The specific impulse in Seconds.

Return type:

float

get_thrust(
self: ostk.astrodynamics.flight.system.PropulsionSystem,
) → ostk.core.type.Real

Return the thrust.

Returns:

The thrust in Newton.

Return type:

float

is_defined(
self: ostk.astrodynamics.flight.system.PropulsionSystem,
) → bool

Check if the propulsion system is defined.

Returns:

True if the propulsion system is defined, False otherwise.

Return type:

bool

static undefined() → ostk.astrodynamics.flight.system.PropulsionSystem

Return an undefined propulsion system.

Returns:

An undefined propulsion system.

Return type:

PropulsionSystem

\ No newline at end of file + ostk.astrodynamics.flight.system.PropulsionSystem — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.system.PropulsionSystem

class PropulsionSystem(
self: ostk.astrodynamics.flight.system.PropulsionSystem,
thrust_si_unit: ostk.core.type.Real,
specific_impulse_si_unit: ostk.core.type.Real,
)

Bases: pybind11_object

A propulsion system.

Construct a propulsion system.

Parameters:

  • thrust (float) -- Thrust in Newton.

  • specific_impulse (float) -- Specific impulse in Seconds.

Methods

default

Return a default propulsion system.

get_acceleration

Return the acceleration.

get_mass_flow_rate

Return the mass flow rate.

get_specific_impulse

Return the specific impulse.

get_thrust

Return the thrust.

is_defined

Check if the propulsion system is defined.

undefined

Return an undefined propulsion system.

static default() → ostk.astrodynamics.flight.system.PropulsionSystem

Return a default propulsion system.

Returns:

A default propulsion system.

Return type:

PropulsionSystem

get_acceleration(
self: ostk.astrodynamics.flight.system.PropulsionSystem,
mass: ostk.physics.unit.Mass,
) → ostk.core.type.Real

Return the acceleration.

Parameters:

mass (float) -- Mass in Kilograms.

Returns:

The acceleration in Meters per Second squared.

Return type:

float

get_mass_flow_rate(
self: ostk.astrodynamics.flight.system.PropulsionSystem,
) → ostk.core.type.Real

Return the mass flow rate.

Returns:

The mass flow rate in Kilograms per Second.

Return type:

float

get_specific_impulse(
self: ostk.astrodynamics.flight.system.PropulsionSystem,
) → ostk.core.type.Real

Return the specific impulse.

Returns:

The specific impulse in Seconds.

Return type:

float

get_thrust(
self: ostk.astrodynamics.flight.system.PropulsionSystem,
) → ostk.core.type.Real

Return the thrust.

Returns:

The thrust in Newton.

Return type:

float

is_defined(
self: ostk.astrodynamics.flight.system.PropulsionSystem,
) → bool

Check if the propulsion system is defined.

Returns:

True if the propulsion system is defined, False otherwise.

Return type:

bool

static undefined() → ostk.astrodynamics.flight.system.PropulsionSystem

Return an undefined propulsion system.

Returns:

An undefined propulsion system.

Return type:

PropulsionSystem

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.flight.system.SatelliteSystem.html b/_build/html/_autosummary/ostk.astrodynamics.flight.system.SatelliteSystem.html index 7fe0750ca..42157fdec 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.flight.system.SatelliteSystem.html +++ b/_build/html/_autosummary/ostk.astrodynamics.flight.system.SatelliteSystem.html @@ -1 +1 @@ - ostk.astrodynamics.flight.system.SatelliteSystem — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.system.SatelliteSystem

class SatelliteSystem(
self: ostk.astrodynamics.flight.system.SatelliteSystem,
mass: ostk.physics.unit.Mass,
satellite_geometry: ostk.mathematics.geometry.d3.object.Composite,
inertia_tensor: numpy.ndarray[numpy.float64[3, 3]],
cross_sectional_surface_area: ostk.core.type.Real,
drag_coefficient: ostk.core.type.Real,
propulsion_system: ostk.astrodynamics.flight.system.PropulsionSystem = undefined,
)

Bases: System

A Satellite System.

Constructor.

Parameters:

  • mass (Mass) -- The mass of the satellite system.

  • satellite_geometry (Composite) -- The geometry of the satellite system.

  • inertia_tensor (np.ndarray) -- The inertia tensor of the satellite system.

  • cross_sectional_surface_area (float) -- The cross-sectional surface area of the satellite system.

  • drag_coefficient (float) -- The drag coefficient of the satellite system.

  • propulsion_system (PropulsionSystem) -- The propulsion system of the satellite system.

Methods

default

Create a default satellite system.

get_cross_sectional_surface_area

Get the cross-sectional surface area of the satellite system.

get_drag_coefficient

Get the drag coefficient of the satellite system.

get_geometry

Get the geometry of the system.

get_inertia_tensor

Get the inertia tensor of the satellite system.

get_mass

Get the mass of the system.

get_propulsion_system

Get the propulsion system of the satellite system.

is_defined

Check if the satellite system is defined.

undefined

Create an undefined satellite system.

static default() → ostk.astrodynamics.flight.system.SatelliteSystem

Create a default satellite system.

Returns:

The default satellite system.

Return type:

SatelliteSystem

get_cross_sectional_surface_area(
self: ostk.astrodynamics.flight.system.SatelliteSystem,
) → ostk.core.type.Real

Get the cross-sectional surface area of the satellite system.

Returns:

The cross-sectional surface area of the satellite system.

Return type:

float

get_drag_coefficient(
self: ostk.astrodynamics.flight.system.SatelliteSystem,
) → ostk.core.type.Real

Get the drag coefficient of the satellite system.

Returns:

The drag coefficient of the satellite system.

Return type:

float

get_geometry(
self: ostk.astrodynamics.flight.System,
) → ostk.mathematics.geometry.d3.object.Composite

Get the geometry of the system.

Returns:

The geometry of the system.

Return type:

Composite

get_inertia_tensor(
self: ostk.astrodynamics.flight.system.SatelliteSystem,
) → numpy.ndarray[numpy.float64[3, 3]]

Get the inertia tensor of the satellite system.

Returns:

The inertia tensor of the satellite system.

Return type:

Matrix3d

get_mass(
self: ostk.astrodynamics.flight.System,
) → ostk.physics.unit.Mass

Get the mass of the system.

Returns:

The mass of the system.

Return type:

Mass

get_propulsion_system(
self: ostk.astrodynamics.flight.system.SatelliteSystem,
) → ostk.astrodynamics.flight.system.PropulsionSystem

Get the propulsion system of the satellite system.

Returns:

The propulsion system of the satellite system.

Return type:

PropulsionSystem

is_defined(
self: ostk.astrodynamics.flight.system.SatelliteSystem,
) → bool

Check if the satellite system is defined.

Returns:

True if the satellite system is defined, False otherwise.

Return type:

bool

static undefined() → ostk.astrodynamics.flight.system.SatelliteSystem

Create an undefined satellite system.

Returns:

The undefined satellite system.

Return type:

SatelliteSystem

\ No newline at end of file + ostk.astrodynamics.flight.system.SatelliteSystem — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.system.SatelliteSystem

class SatelliteSystem(
self: ostk.astrodynamics.flight.system.SatelliteSystem,
mass: ostk.physics.unit.Mass,
satellite_geometry: ostk.mathematics.geometry.d3.object.Composite,
inertia_tensor: numpy.ndarray[numpy.float64[3, 3]],
cross_sectional_surface_area: ostk.core.type.Real,
drag_coefficient: ostk.core.type.Real,
propulsion_system: ostk.astrodynamics.flight.system.PropulsionSystem = undefined,
)

Bases: System

A Satellite System.

Constructor.

Parameters:

  • mass (Mass) -- The mass of the satellite system.

  • satellite_geometry (Composite) -- The geometry of the satellite system.

  • inertia_tensor (np.ndarray) -- The inertia tensor of the satellite system.

  • cross_sectional_surface_area (float) -- The cross-sectional surface area of the satellite system.

  • drag_coefficient (float) -- The drag coefficient of the satellite system.

  • propulsion_system (PropulsionSystem) -- The propulsion system of the satellite system.

Methods

default

Create a default satellite system.

get_cross_sectional_surface_area

Get the cross-sectional surface area of the satellite system.

get_drag_coefficient

Get the drag coefficient of the satellite system.

get_geometry

Get the geometry of the system.

get_inertia_tensor

Get the inertia tensor of the satellite system.

get_mass

Get the mass of the system.

get_propulsion_system

Get the propulsion system of the satellite system.

is_defined

Check if the satellite system is defined.

undefined

Create an undefined satellite system.

static default() → ostk.astrodynamics.flight.system.SatelliteSystem

Create a default satellite system.

Returns:

The default satellite system.

Return type:

SatelliteSystem

get_cross_sectional_surface_area(
self: ostk.astrodynamics.flight.system.SatelliteSystem,
) → ostk.core.type.Real

Get the cross-sectional surface area of the satellite system.

Returns:

The cross-sectional surface area of the satellite system.

Return type:

float

get_drag_coefficient(
self: ostk.astrodynamics.flight.system.SatelliteSystem,
) → ostk.core.type.Real

Get the drag coefficient of the satellite system.

Returns:

The drag coefficient of the satellite system.

Return type:

float

get_geometry(
self: ostk.astrodynamics.flight.System,
) → ostk.mathematics.geometry.d3.object.Composite

Get the geometry of the system.

Returns:

The geometry of the system.

Return type:

Composite

get_inertia_tensor(
self: ostk.astrodynamics.flight.system.SatelliteSystem,
) → numpy.ndarray[numpy.float64[3, 3]]

Get the inertia tensor of the satellite system.

Returns:

The inertia tensor of the satellite system.

Return type:

Matrix3d

get_mass(
self: ostk.astrodynamics.flight.System,
) → ostk.physics.unit.Mass

Get the mass of the system.

Returns:

The mass of the system.

Return type:

Mass

get_propulsion_system(
self: ostk.astrodynamics.flight.system.SatelliteSystem,
) → ostk.astrodynamics.flight.system.PropulsionSystem

Get the propulsion system of the satellite system.

Returns:

The propulsion system of the satellite system.

Return type:

PropulsionSystem

is_defined(
self: ostk.astrodynamics.flight.system.SatelliteSystem,
) → bool

Check if the satellite system is defined.

Returns:

True if the satellite system is defined, False otherwise.

Return type:

bool

static undefined() → ostk.astrodynamics.flight.system.SatelliteSystem

Create an undefined satellite system.

Returns:

The undefined satellite system.

Return type:

SatelliteSystem

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.flight.system.SatelliteSystemBuilder.html b/_build/html/_autosummary/ostk.astrodynamics.flight.system.SatelliteSystemBuilder.html index 8eaa29366..dcc1fa0f3 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.flight.system.SatelliteSystemBuilder.html +++ b/_build/html/_autosummary/ostk.astrodynamics.flight.system.SatelliteSystemBuilder.html @@ -1,3 +1,3 @@ ostk.astrodynamics.flight.system.SatelliteSystemBuilder — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.flight.system.SatelliteSystemBuilder

class SatelliteSystemBuilder(self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder)

Bases: pybind11_object

A Satellite System Builder, meant to simplify creation of a SatelliteSystem, by allowing you to only specify the parameters you want. There are two ways of doing this:

Chaining together your desired parameters like so:

satellite_system = SatelliteSystemBuilder().with_dry_mass(X).with_area(Y).build()

Using the default SatelliteSystem and changing one parameters like so:

satellite_system = SatelliteSystemBuilder.default().with_dry_mass(X)
-

Constructor.

Methods

build

Build a new satellite system.

default

Create a satellite system builder with default values.

with_cross_sectional_surface_area

Set the dry mass.

with_drag_coefficient

Set the drag coefficient.

with_dry_mass

Set the dry mass.

with_geometry

Set the geometry.

with_inertia_tensor

Set the inertia tensor.

with_propulsion_system

Set the propulsion system.

build(
self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder,
) → ostk.astrodynamics.flight.system.SatelliteSystem

Build a new satellite system.

Returns:

A new satellite system.

Return type:

SatelliteSystem

static default() → ostk.astrodynamics.flight.system.SatelliteSystemBuilder

Create a satellite system builder with default values.

Returns:

The satellite system builder with default values.

Return type:

SatelliteSystem

with_cross_sectional_surface_area(
self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder,
cross_sectional_surface_area: ostk.core.type.Real,
) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder

Set the dry mass.

Parameters:

cross_sectional_surface_area (float) -- The cross-sectional surface area.

Returns:

The builder.

Return type:

SatelliteSystemBuilder

with_drag_coefficient(
self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder,
drag_coefficient: ostk.core.type.Real,
) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder

Set the drag coefficient.

Parameters:

drag_coefficient (float) -- The drag coefficient.

Returns:

The builder.

Return type:

SatelliteSystemBuilder

with_dry_mass(
self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder,
dry_mass: ostk.physics.unit.Mass,
) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder

Set the dry mass.

Parameters:

dry_mass (Mass) -- The dry mass.

Returns:

The builder.

Return type:

SatelliteSystemBuilder

with_geometry(
self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder,
geometry: ostk.mathematics.geometry.d3.object.Composite,
) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder

Set the geometry.

Parameters:

geometry (Composite) -- The geometry.

Returns:

The builder.

Return type:

SatelliteSystemBuilder

with_inertia_tensor(
self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder,
inertia_tensor: numpy.ndarray[numpy.float64[3, 3]],
) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder

Set the inertia tensor.

Parameters:

inertia_tensor (Matrix3d) -- The inertia tensor.

Returns:

The builder.

Return type:

SatelliteSystemBuilder

with_propulsion_system(
self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder,
propulsion_system: ostk.astrodynamics.flight.system.PropulsionSystem,
) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder

Set the propulsion system.

Parameters:

propulsion_system (PropulsionSystem) -- The propulsion system.

Returns:

The builder.

Return type:

SatelliteSystemBuilder

\ No newline at end of file +

Constructor.

Methods

build

Build a new satellite system.

default

Create a satellite system builder with default values.

with_cross_sectional_surface_area

Set the dry mass.

with_drag_coefficient

Set the drag coefficient.

with_dry_mass

Set the dry mass.

with_geometry

Set the geometry.

with_inertia_tensor

Set the inertia tensor.

with_propulsion_system

Set the propulsion system.

build(
self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder,
) → ostk.astrodynamics.flight.system.SatelliteSystem

Build a new satellite system.

Returns:

A new satellite system.

Return type:

SatelliteSystem

static default() → ostk.astrodynamics.flight.system.SatelliteSystemBuilder

Create a satellite system builder with default values.

Returns:

The satellite system builder with default values.

Return type:

SatelliteSystem

with_cross_sectional_surface_area(
self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder,
cross_sectional_surface_area: ostk.core.type.Real,
) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder

Set the dry mass.

Parameters:

cross_sectional_surface_area (float) -- The cross-sectional surface area.

Returns:

The builder.

Return type:

SatelliteSystemBuilder

with_drag_coefficient(
self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder,
drag_coefficient: ostk.core.type.Real,
) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder

Set the drag coefficient.

Parameters:

drag_coefficient (float) -- The drag coefficient.

Returns:

The builder.

Return type:

SatelliteSystemBuilder

with_dry_mass(
self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder,
dry_mass: ostk.physics.unit.Mass,
) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder

Set the dry mass.

Parameters:

dry_mass (Mass) -- The dry mass.

Returns:

The builder.

Return type:

SatelliteSystemBuilder

with_geometry(
self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder,
geometry: ostk.mathematics.geometry.d3.object.Composite,
) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder

Set the geometry.

Parameters:

geometry (Composite) -- The geometry.

Returns:

The builder.

Return type:

SatelliteSystemBuilder

with_inertia_tensor(
self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder,
inertia_tensor: numpy.ndarray[numpy.float64[3, 3]],
) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder

Set the inertia tensor.

Parameters:

inertia_tensor (Matrix3d) -- The inertia tensor.

Returns:

The builder.

Return type:

SatelliteSystemBuilder

with_propulsion_system(
self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder,
propulsion_system: ostk.astrodynamics.flight.system.PropulsionSystem,
) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder

Set the propulsion system.

Parameters:

propulsion_system (PropulsionSystem) -- The propulsion system.

Returns:

The builder.

Return type:

SatelliteSystemBuilder

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.guidance_law.ConstantThrust.html b/_build/html/_autosummary/ostk.astrodynamics.guidance_law.ConstantThrust.html index 1b40447c9..e37e9960a 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.guidance_law.ConstantThrust.html +++ b/_build/html/_autosummary/ostk.astrodynamics.guidance_law.ConstantThrust.html @@ -1 +1 @@ - ostk.astrodynamics.guidance_law.ConstantThrust — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.guidance_law.ConstantThrust

class ConstantThrust(
self: ostk.astrodynamics.guidance_law.ConstantThrust,
thrust_direction: ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection,
)

Bases: GuidanceLaw

Constant Thrust, Constant Direction dynamics.

Constructor.

Parameters:

thrust_direction (LocalOrbitalFrameDirection) -- The thrust direction.

Methods

calculate_thrust_acceleration_at

Compute the acceleration due to constant thrust.

get_local_thrust_direction

Get the local thrust direction.

get_name

Get the name of the guidance law.

intrack

Create a constant thrust in the in-track direction.

calculate_thrust_acceleration_at(
self: ostk.astrodynamics.guidance_law.ConstantThrust,
instant: ostk.physics.time.Instant,
position_coordinates: numpy.ndarray[numpy.float64[3, 1]],
velocity_coordinates: numpy.ndarray[numpy.float64[3, 1]],
thrust_acceleration: ostk.core.type.Real,
output_frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[3, 1]]

Compute the acceleration due to constant thrust.

Parameters:

  • instant (Instant) -- The instant of the state vector.

  • position_coordinates (numpy.ndarray) -- The position coordinates.

  • velocity_coordinates (numpy.ndarray) -- The velocity coordinates.

  • thrust_acceleration (float) -- The thrust acceleration magnitude.

  • output_frame (Frame) -- The frame the acceleration will be expressed in.

Returns:

The contribution of the constant thrust to the state vector.

Return type:

numpy.ndarray

get_local_thrust_direction(
self: ostk.astrodynamics.guidance_law.ConstantThrust,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection

Get the local thrust direction.

Returns:

The local thrust direction.

Return type:

LocalOrbitalFrameDirection

get_name(self: ostk.astrodynamics.GuidanceLaw) → ostk.core.type.String

Get the name of the guidance law.

Returns:

The name of the guidance law.

Return type:

str

static intrack(
velocity_direction: bool = True,
) → ostk.astrodynamics.guidance_law.ConstantThrust

Create a constant thrust in the in-track direction.

Parameters:

  • satellite_system (SatelliteSystem) -- The satellite system.

  • velocity_direction (bool, optional) -- If True, the thrust is applied in the velocity direction. Otherwise, it is applied in the opposite direction.

  • frame (Frame, optional) -- The reference frame.

Returns:

The constant thrust.

Return type:

ConstantThrust

\ No newline at end of file + ostk.astrodynamics.guidance_law.ConstantThrust — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.guidance_law.ConstantThrust

class ConstantThrust(
self: ostk.astrodynamics.guidance_law.ConstantThrust,
thrust_direction: ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection,
)

Bases: GuidanceLaw

Constant Thrust, Constant Direction dynamics.

Constructor.

Parameters:

thrust_direction (LocalOrbitalFrameDirection) -- The thrust direction.

Methods

calculate_thrust_acceleration_at

Compute the acceleration due to constant thrust.

get_local_thrust_direction

Get the local thrust direction.

get_name

Get the name of the guidance law.

intrack

Create a constant thrust in the in-track direction.

calculate_thrust_acceleration_at(
self: ostk.astrodynamics.guidance_law.ConstantThrust,
instant: ostk.physics.time.Instant,
position_coordinates: numpy.ndarray[numpy.float64[3, 1]],
velocity_coordinates: numpy.ndarray[numpy.float64[3, 1]],
thrust_acceleration: ostk.core.type.Real,
output_frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[3, 1]]

Compute the acceleration due to constant thrust.

Parameters:

  • instant (Instant) -- The instant of the state vector.

  • position_coordinates (numpy.ndarray) -- The position coordinates.

  • velocity_coordinates (numpy.ndarray) -- The velocity coordinates.

  • thrust_acceleration (float) -- The thrust acceleration magnitude.

  • output_frame (Frame) -- The frame the acceleration will be expressed in.

Returns:

The contribution of the constant thrust to the state vector.

Return type:

numpy.ndarray

get_local_thrust_direction(
self: ostk.astrodynamics.guidance_law.ConstantThrust,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection

Get the local thrust direction.

Returns:

The local thrust direction.

Return type:

LocalOrbitalFrameDirection

get_name(self: ostk.astrodynamics.GuidanceLaw) → ostk.core.type.String

Get the name of the guidance law.

Returns:

The name of the guidance law.

Return type:

str

static intrack(
velocity_direction: bool = True,
) → ostk.astrodynamics.guidance_law.ConstantThrust

Create a constant thrust in the in-track direction.

Parameters:

  • satellite_system (SatelliteSystem) -- The satellite system.

  • velocity_direction (bool, optional) -- If True, the thrust is applied in the velocity direction. Otherwise, it is applied in the opposite direction.

  • frame (Frame, optional) -- The reference frame.

Returns:

The constant thrust.

Return type:

ConstantThrust

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.guidance_law.QLaw.html b/_build/html/_autosummary/ostk.astrodynamics.guidance_law.QLaw.html index e35a45e99..0257be78c 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.guidance_law.QLaw.html +++ b/_build/html/_autosummary/ostk.astrodynamics.guidance_law.QLaw.html @@ -1 +1 @@ - ostk.astrodynamics.guidance_law.QLaw — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.guidance_law.QLaw

class QLaw(
self: ostk.astrodynamics.guidance_law.QLaw,
target_coe: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
parameters: ostk.astrodynamics.guidance_law.QLaw.Parameters,
gradient_strategy: ostk.astrodynamics.guidance_law.QLaw.GradientStrategy = <GradientStrategy.FiniteDifference: 1>,
)

Bases: GuidanceLaw

This class implements the Q-law guidance law.

The Q-law is a Lyapunov feedback control law developed by Petropoulos, based on analytic expressions for maximum rates of change of the orbit elements and the desired changes in the elements. Q, the proximity quotient, serves as a candidate Lyapunov function. As the spacecraft approaches the target orbit, Q decreases monotonically (becoming zero at the target orbit).

Constructor.

Parameters:

  • coe (COE) -- The target orbit described by Classical Orbital Elements.

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

  • parameters (QLaw.Parameters) -- A set of parameters for the QLaw.

  • gradient_strategy (QLaw.GradientStrategy) -- The strategy used to compute the gradient dQ_dOE. Defaults to FiniteDifference.

Methods

calculate_thrust_acceleration_at

Calculate the thrust acceleration at the provided coordinates and instant.

get_gradient_strategy

Get the gradient strategy.

get_name

Get the name of the guidance law.

get_parameters

Get the parameters.

get_target_coe

Get the target COE.

class GradientStrategy(
self: ostk.astrodynamics.guidance_law.QLaw.GradientStrategy,
value: int,
)

Bases: pybind11_object

Gradient strategy.

Members:

Analytical : Analytical

FiniteDifference : Finite Differenced

property name
class Parameters(
self: ostk.astrodynamics.guidance_law.QLaw.Parameters,
element_weights: Dict[ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element, Tuple[float, float]],
m: int = 3,
n: int = 4,
r: int = 2,
b: float = 0.01,
k: int = 100,
periapsis_weight: float = 0.0,
minimum_periapsis_radius: ostk.physics.unit.Length = Length.kilometers(6578.0),
absolute_effectivity_threshold: ostk.core.type.Real = Undefined,
relative_effectivity_threshold: ostk.core.type.Real = Undefined,
)

Bases: pybind11_object

Q-law parameters.

Constructor.

Parameters:

  • element_weights (dict) -- Key-value pair of COE elements and the (weights, tolerances) for the targeter.

  • m (int) -- Scaling parameter for Semi-Major Axis delta. Default to 3.

  • n (int) -- Scaling parameter for Semi-Major Axis delta. Default to 4.

  • r (int) -- Scaling parameter for Semi-Major Axis delta. Default to 2.

  • b (float) -- Scaling parameter for Argument of Periapsis maximal change. Default to 0.01.

  • k (int) -- Penalty parameter for periapsis. Default to 100.

  • periapsis_weight (float) -- Periapsis weight. Default to 0.0.

  • minimum_periapsis_radius (Length) -- Minimum periapsis radius. Default to 6578.0 km.

  • absolute_effectivity_threshold (Real) -- Absolute effectivity threshold. Default to undefined (not used).

  • relative_effectivity_threshold (Real) -- Relative effectivity threshold. Default to undefined (not used).

property absolute_effectivity_threshold

Absolute effectivity threshold.

Type:

Real

property b

Scaling parameter for Argument of Periapsis.

Type:

float

get_control_weights(
self: ostk.astrodynamics.guidance_law.QLaw.Parameters,
) → numpy.ndarray[numpy.float64[5, 1]]

Get the control weights.

Returns:

The control weights.

Return type:

np.array

get_minimum_periapsis_radius(
self: ostk.astrodynamics.guidance_law.QLaw.Parameters,
) → ostk.physics.unit.Length

Get the minimum periapsis radius.

Returns:

The minimum periapsis radius.

Return type:

Length

property k

Penalty parameter for periapsis.

Type:

int

property m

Scaling parameter for Semi-Major Axis delta.

Type:

int

property n

Scaling parameter for Semi-Major Axis delta.

Type:

int

property periapsis_weight

Periapsis weight.

Type:

float

property r

Scaling parameter for Semi-Major Axis delta.

Type:

int

property relative_effectivity_threshold

Relative effectivity threshold.

Type:

Real

calculate_thrust_acceleration_at(
self: ostk.astrodynamics.guidance_law.QLaw,
instant: ostk.physics.time.Instant,
position_coordinates: numpy.ndarray[numpy.float64[3, 1]],
velocity_coordinates: numpy.ndarray[numpy.float64[3, 1]],
thrust_acceleration: ostk.core.type.Real,
output_frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[3, 1]]

Calculate the thrust acceleration at the provided coordinates and instant.

Parameters:

  • instant (Instant) -- Instant of computation.

  • position_coordinates (np.array) -- Position coordinates.

  • velocity_coordinates (np.array) -- Velocity coordinates.

  • thrust_acceleration (float) -- Thrust acceleration magnitude.

  • output_frame (Frame) -- The frame the acceleration is expressed in.

Returns:

The acceleration.

Return type:

np.array

get_gradient_strategy(
self: ostk.astrodynamics.guidance_law.QLaw,
) → ostk.astrodynamics.guidance_law.QLaw.GradientStrategy

Get the gradient strategy.

Returns:

The gradient strategy.

Return type:

QLaw.GradientStrategy

get_name(self: ostk.astrodynamics.GuidanceLaw) → ostk.core.type.String

Get the name of the guidance law.

Returns:

The name of the guidance law.

Return type:

str

get_parameters(
self: ostk.astrodynamics.guidance_law.QLaw,
) → ostk.astrodynamics.guidance_law.QLaw.Parameters

Get the parameters.

Returns:

The parameters.

Return type:

QLaw.Parameters

get_target_coe(
self: ostk.astrodynamics.guidance_law.QLaw,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Get the target COE.

Returns:

The target COE.

Return type:

COE

\ No newline at end of file + ostk.astrodynamics.guidance_law.QLaw — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.guidance_law.QLaw

class QLaw(
self: ostk.astrodynamics.guidance_law.QLaw,
target_coe: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
parameters: ostk.astrodynamics.guidance_law.QLaw.Parameters,
gradient_strategy: ostk.astrodynamics.guidance_law.QLaw.GradientStrategy = <GradientStrategy.FiniteDifference: 1>,
)

Bases: GuidanceLaw

This class implements the Q-law guidance law.

The Q-law is a Lyapunov feedback control law developed by Petropoulos, based on analytic expressions for maximum rates of change of the orbit elements and the desired changes in the elements. Q, the proximity quotient, serves as a candidate Lyapunov function. As the spacecraft approaches the target orbit, Q decreases monotonically (becoming zero at the target orbit).

Constructor.

Parameters:

  • coe (COE) -- The target orbit described by Classical Orbital Elements.

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

  • parameters (QLaw.Parameters) -- A set of parameters for the QLaw.

  • gradient_strategy (QLaw.GradientStrategy) -- The strategy used to compute the gradient dQ_dOE. Defaults to FiniteDifference.

Methods

calculate_thrust_acceleration_at

Calculate the thrust acceleration at the provided coordinates and instant.

get_gradient_strategy

Get the gradient strategy.

get_name

Get the name of the guidance law.

get_parameters

Get the parameters.

get_target_coe

Get the target COE.

class GradientStrategy(
self: ostk.astrodynamics.guidance_law.QLaw.GradientStrategy,
value: int,
)

Bases: pybind11_object

Gradient strategy.

Members:

Analytical : Analytical

FiniteDifference : Finite Differenced

property name
class Parameters(
self: ostk.astrodynamics.guidance_law.QLaw.Parameters,
element_weights: Dict[ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element, Tuple[float, float]],
m: int = 3,
n: int = 4,
r: int = 2,
b: float = 0.01,
k: int = 100,
periapsis_weight: float = 0.0,
minimum_periapsis_radius: ostk.physics.unit.Length = Length.kilometers(6578.0),
absolute_effectivity_threshold: ostk.core.type.Real = Undefined,
relative_effectivity_threshold: ostk.core.type.Real = Undefined,
)

Bases: pybind11_object

Q-law parameters.

Constructor.

Parameters:

  • element_weights (dict) -- Key-value pair of COE elements and the (weights, tolerances) for the targeter.

  • m (int) -- Scaling parameter for Semi-Major Axis delta. Default to 3.

  • n (int) -- Scaling parameter for Semi-Major Axis delta. Default to 4.

  • r (int) -- Scaling parameter for Semi-Major Axis delta. Default to 2.

  • b (float) -- Scaling parameter for Argument of Periapsis maximal change. Default to 0.01.

  • k (int) -- Penalty parameter for periapsis. Default to 100.

  • periapsis_weight (float) -- Periapsis weight. Default to 0.0.

  • minimum_periapsis_radius (Length) -- Minimum periapsis radius. Default to 6578.0 km.

  • absolute_effectivity_threshold (Real) -- Absolute effectivity threshold. Default to undefined (not used).

  • relative_effectivity_threshold (Real) -- Relative effectivity threshold. Default to undefined (not used).

property absolute_effectivity_threshold

Absolute effectivity threshold.

Type:

Real

property b

Scaling parameter for Argument of Periapsis.

Type:

float

get_control_weights(
self: ostk.astrodynamics.guidance_law.QLaw.Parameters,
) → numpy.ndarray[numpy.float64[5, 1]]

Get the control weights.

Returns:

The control weights.

Return type:

np.array

get_minimum_periapsis_radius(
self: ostk.astrodynamics.guidance_law.QLaw.Parameters,
) → ostk.physics.unit.Length

Get the minimum periapsis radius.

Returns:

The minimum periapsis radius.

Return type:

Length

property k

Penalty parameter for periapsis.

Type:

int

property m

Scaling parameter for Semi-Major Axis delta.

Type:

int

property n

Scaling parameter for Semi-Major Axis delta.

Type:

int

property periapsis_weight

Periapsis weight.

Type:

float

property r

Scaling parameter for Semi-Major Axis delta.

Type:

int

property relative_effectivity_threshold

Relative effectivity threshold.

Type:

Real

calculate_thrust_acceleration_at(
self: ostk.astrodynamics.guidance_law.QLaw,
instant: ostk.physics.time.Instant,
position_coordinates: numpy.ndarray[numpy.float64[3, 1]],
velocity_coordinates: numpy.ndarray[numpy.float64[3, 1]],
thrust_acceleration: ostk.core.type.Real,
output_frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[3, 1]]

Calculate the thrust acceleration at the provided coordinates and instant.

Parameters:

  • instant (Instant) -- Instant of computation.

  • position_coordinates (np.array) -- Position coordinates.

  • velocity_coordinates (np.array) -- Velocity coordinates.

  • thrust_acceleration (float) -- Thrust acceleration magnitude.

  • output_frame (Frame) -- The frame the acceleration is expressed in.

Returns:

The acceleration.

Return type:

np.array

get_gradient_strategy(
self: ostk.astrodynamics.guidance_law.QLaw,
) → ostk.astrodynamics.guidance_law.QLaw.GradientStrategy

Get the gradient strategy.

Returns:

The gradient strategy.

Return type:

QLaw.GradientStrategy

get_name(self: ostk.astrodynamics.GuidanceLaw) → ostk.core.type.String

Get the name of the guidance law.

Returns:

The name of the guidance law.

Return type:

str

get_parameters(
self: ostk.astrodynamics.guidance_law.QLaw,
) → ostk.astrodynamics.guidance_law.QLaw.Parameters

Get the parameters.

Returns:

The parameters.

Return type:

QLaw.Parameters

get_target_coe(
self: ostk.astrodynamics.guidance_law.QLaw,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Get the target COE.

Returns:

The target COE.

Return type:

COE

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.solver.FiniteDifferenceSolver.html b/_build/html/_autosummary/ostk.astrodynamics.solver.FiniteDifferenceSolver.html index a0aad375a..313d05976 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.solver.FiniteDifferenceSolver.html +++ b/_build/html/_autosummary/ostk.astrodynamics.solver.FiniteDifferenceSolver.html @@ -1 +1 @@ - ostk.astrodynamics.solver.FiniteDifferenceSolver — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.solver.FiniteDifferenceSolver

class FiniteDifferenceSolver(
self: ostk.astrodynamics.solver.FiniteDifferenceSolver,
type: ostk.astrodynamics.solver.FiniteDifferenceSolver.Type,
step_percentage: ostk.core.type.Real,
step_duration: ostk.physics.time.Duration,
)

Bases: pybind11_object

A Finite Difference Solver to compute the gradient, and jacobian of a function.

Construct a FiniteDifferenceSolver.

Parameters:

  • type (FiniteDifferenceSolver.Type) -- Type of finite difference scheme.

  • step_percentage (float) -- The step percentage to use for computing the STM.

  • step_duration (Duration) -- The step duration to use for computing the gradient.

Returns:

The FiniteDifferenceSolver.

Return type:

FiniteDifferenceSolver

Methods

compute_gradient

Compute the gradient.

compute_jacobian

Overloaded function.

default

Get the default Finite Difference Solver.

get_step_duration

Get the step duration used for computing the gradient.

get_step_percentage

Get the step percentage used for computing the STM.

get_type

Get the type.

string_from_type

Convert a type to string.

class Type(
self: ostk.astrodynamics.solver.FiniteDifferenceSolver.Type,
value: int,
)

Bases: pybind11_object

Type of finite difference scheme.

Members:

Forward : Forward difference scheme.

Backward : Backward difference scheme.

Central : Central difference scheme.

property name
compute_gradient(self: ostk.astrodynamics.solver.FiniteDifferenceSolver, state: ostk::astrodynamics::trajectory::State, generate_state_coordinates: Callable[[ostk::astrodynamics::trajectory::State, ostk.physics.time.Instant], numpy.ndarray[numpy.float64[m, 1]]]) → numpy.ndarray[numpy.float64[m, 1]]

Compute the gradient.

Parameters:

  • state (State) -- The state.

  • generate_state_coordinates (function) -- The function to generate the state coordinates.

Returns:

The jacobian.

Return type:

np.array

compute_jacobian(*args, **kwargs)

Overloaded function.

  1. compute_jacobian(self: ostk.astrodynamics.solver.FiniteDifferenceSolver, state: ostk::astrodynamics::trajectory::State, instants: List[ostk.physics.time.Instant], generate_states_coordinates: Callable[[ostk::astrodynamics::trajectory::State, List[ostk.physics.time.Instant]], numpy.ndarray[numpy.float64[m, n]]], coordinates_dimension: int) -> numpy.ndarray[numpy.float64[m, n]]

    Compute the jacobian.

    Args:

    state (State): The state. instants (Array(Instant)): The instants at which to calculate the STM. generate_states_coordinates (function): The function to get the states. coordinates_dimension (int): The dimension of the coordinates produced by generate_states_coordinates.

    Returns:

    np.array: The jacobian.

  2. compute_jacobian(self: ostk.astrodynamics.solver.FiniteDifferenceSolver, state: ostk::astrodynamics::trajectory::State, instant: ostk.physics.time.Instant, generate_state_coordinates: Callable[[ostk::astrodynamics::trajectory::State, ostk.physics.time.Instant], numpy.ndarray[numpy.float64[m, 1]]], coordinates_dimension: int) -> numpy.ndarray[numpy.float64[m, n]]

    Compute the jacobian.

    Args:

    state (State): The state. instant (Instant): The instant at which to calculate the STM. generate_state_coordinates (function): The function to get the state. coordinates_dimension (int): The dimension of the coordinates produced by generate_state_coordinates

    Returns:

    np.array: The jacobian.

static default() → ostk.astrodynamics.solver.FiniteDifferenceSolver

Get the default Finite Difference Solver.

Returns:

The default Finite Difference Solver.

Return type:

FiniteDifferenceSolver

get_step_duration(
self: ostk.astrodynamics.solver.FiniteDifferenceSolver,
) → ostk.physics.time.Duration

Get the step duration used for computing the gradient.

Returns:

The step duration.

Return type:

Duration

get_step_percentage(
self: ostk.astrodynamics.solver.FiniteDifferenceSolver,
) → ostk.core.type.Real

Get the step percentage used for computing the STM.

Returns:

The step percentage.

Return type:

float

get_type(
self: ostk.astrodynamics.solver.FiniteDifferenceSolver,
) → ostk.astrodynamics.solver.FiniteDifferenceSolver.Type

Get the type.

Returns:

The type.

Return type:

FiniteDifferenceSolver.Type

static string_from_type(
type: ostk.astrodynamics.solver.FiniteDifferenceSolver.Type,
) → ostk.core.type.String

Convert a type to string.

Parameters:

type (FiniteDifferenceSolver.Type) -- The type.

Returns:

The string name of the type.

Return type:

str

\ No newline at end of file + ostk.astrodynamics.solver.FiniteDifferenceSolver — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.solver.FiniteDifferenceSolver

class FiniteDifferenceSolver(
self: ostk.astrodynamics.solver.FiniteDifferenceSolver,
type: ostk.astrodynamics.solver.FiniteDifferenceSolver.Type,
step_percentage: ostk.core.type.Real,
step_duration: ostk.physics.time.Duration,
)

Bases: pybind11_object

A Finite Difference Solver to compute the gradient, and jacobian of a function.

Construct a FiniteDifferenceSolver.

Parameters:

  • type (FiniteDifferenceSolver.Type) -- Type of finite difference scheme.

  • step_percentage (float) -- The step percentage to use for computing the STM.

  • step_duration (Duration) -- The step duration to use for computing the gradient.

Returns:

The FiniteDifferenceSolver.

Return type:

FiniteDifferenceSolver

Methods

compute_gradient

Compute the gradient.

compute_jacobian

Overloaded function.

default

Get the default Finite Difference Solver.

get_step_duration

Get the step duration used for computing the gradient.

get_step_percentage

Get the step percentage used for computing the STM.

get_type

Get the type.

string_from_type

Convert a type to string.

class Type(
self: ostk.astrodynamics.solver.FiniteDifferenceSolver.Type,
value: int,
)

Bases: pybind11_object

Type of finite difference scheme.

Members:

Forward : Forward difference scheme.

Backward : Backward difference scheme.

Central : Central difference scheme.

property name
compute_gradient(self: ostk.astrodynamics.solver.FiniteDifferenceSolver, state: ostk::astrodynamics::trajectory::State, generate_state_coordinates: Callable[[ostk::astrodynamics::trajectory::State, ostk.physics.time.Instant], numpy.ndarray[numpy.float64[m, 1]]]) → numpy.ndarray[numpy.float64[m, 1]]

Compute the gradient.

Parameters:

  • state (State) -- The state.

  • generate_state_coordinates (function) -- The function to generate the state coordinates.

Returns:

The jacobian.

Return type:

np.array

compute_jacobian(*args, **kwargs)

Overloaded function.

  1. compute_jacobian(self: ostk.astrodynamics.solver.FiniteDifferenceSolver, state: ostk::astrodynamics::trajectory::State, instants: List[ostk.physics.time.Instant], generate_states_coordinates: Callable[[ostk::astrodynamics::trajectory::State, List[ostk.physics.time.Instant]], numpy.ndarray[numpy.float64[m, n]]], coordinates_dimension: int) -> numpy.ndarray[numpy.float64[m, n]]

    Compute the jacobian.

    Args:

    state (State): The state. instants (Array(Instant)): The instants at which to calculate the STM. generate_states_coordinates (function): The function to get the states. coordinates_dimension (int): The dimension of the coordinates produced by generate_states_coordinates.

    Returns:

    np.array: The jacobian.

  2. compute_jacobian(self: ostk.astrodynamics.solver.FiniteDifferenceSolver, state: ostk::astrodynamics::trajectory::State, instant: ostk.physics.time.Instant, generate_state_coordinates: Callable[[ostk::astrodynamics::trajectory::State, ostk.physics.time.Instant], numpy.ndarray[numpy.float64[m, 1]]], coordinates_dimension: int) -> numpy.ndarray[numpy.float64[m, n]]

    Compute the jacobian.

    Args:

    state (State): The state. instant (Instant): The instant at which to calculate the STM. generate_state_coordinates (function): The function to get the state. coordinates_dimension (int): The dimension of the coordinates produced by generate_state_coordinates

    Returns:

    np.array: The jacobian.

static default() → ostk.astrodynamics.solver.FiniteDifferenceSolver

Get the default Finite Difference Solver.

Returns:

The default Finite Difference Solver.

Return type:

FiniteDifferenceSolver

get_step_duration(
self: ostk.astrodynamics.solver.FiniteDifferenceSolver,
) → ostk.physics.time.Duration

Get the step duration used for computing the gradient.

Returns:

The step duration.

Return type:

Duration

get_step_percentage(
self: ostk.astrodynamics.solver.FiniteDifferenceSolver,
) → ostk.core.type.Real

Get the step percentage used for computing the STM.

Returns:

The step percentage.

Return type:

float

get_type(
self: ostk.astrodynamics.solver.FiniteDifferenceSolver,
) → ostk.astrodynamics.solver.FiniteDifferenceSolver.Type

Get the type.

Returns:

The type.

Return type:

FiniteDifferenceSolver.Type

static string_from_type(
type: ostk.astrodynamics.solver.FiniteDifferenceSolver.Type,
) → ostk.core.type.String

Convert a type to string.

Parameters:

type (FiniteDifferenceSolver.Type) -- The type.

Returns:

The string name of the type.

Return type:

str

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.solver.TemporalConditionSolver.html b/_build/html/_autosummary/ostk.astrodynamics.solver.TemporalConditionSolver.html index 4c237c8d3..6e6fc165a 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.solver.TemporalConditionSolver.html +++ b/_build/html/_autosummary/ostk.astrodynamics.solver.TemporalConditionSolver.html @@ -1 +1 @@ - ostk.astrodynamics.solver.TemporalConditionSolver — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.solver.TemporalConditionSolver

class TemporalConditionSolver(
self: ostk.astrodynamics.solver.TemporalConditionSolver,
time_step: ostk.physics.time.Duration,
tolerance: ostk.physics.time.Duration,
maximum_iteration_count: int = 500,
)

Bases: pybind11_object

Given a set of conditions and a time interval, the solver computes all sub-intervals over which conditions are met.

Constructor.

Parameters:

  • time_step (Duration) -- The time step.

  • tolerance (Duration) -- The tolerance of the solver.

  • maximum_iteration_count (int) -- The maximum number of iterations allowed.

Methods

get_maximum_iteration_count

Get the maximum number of iterations allowed.

get_time_step

Get the time step.

get_tolerance

Get the tolerance.

solve

Overloaded function.

get_maximum_iteration_count(
self: ostk.astrodynamics.solver.TemporalConditionSolver,
) → int

Get the maximum number of iterations allowed.

Returns:

The maximum number of iterations allowed.

Return type:

int

get_time_step(
self: ostk.astrodynamics.solver.TemporalConditionSolver,
) → ostk.physics.time.Duration

Get the time step.

Returns:

The time step.

Return type:

Duration

get_tolerance(
self: ostk.astrodynamics.solver.TemporalConditionSolver,
) → ostk.physics.time.Duration

Get the tolerance.

Returns:

The tolerance.

Return type:

Duration

solve(*args, **kwargs)

Overloaded function.

  1. solve(self: ostk.astrodynamics.solver.TemporalConditionSolver, condition: Callable[[ostk.physics.time.Instant], bool], interval: ostk.physics.time.Interval) -> List[ostk.physics.time.Interval]

    Solve a temporal condition.

    Args:

    condition (function): The condition to solve. interval (Interval): The interval to solve the condition over.

    Returns:

    Duration: The time at which the condition is satisfied.

  2. solve(self: ostk.astrodynamics.solver.TemporalConditionSolver, conditions: List[Callable[[ostk.physics.time.Instant], bool]], interval: ostk.physics.time.Interval) -> List[ostk.physics.time.Interval]

    Solve an array of temporal conditions.

    Args:

    conditions (list): The conditions to solve. interval (Interval): The interval to solve the conditions over.

    Returns:

    list: The times at which the conditions are satisfied.

\ No newline at end of file + ostk.astrodynamics.solver.TemporalConditionSolver — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.solver.TemporalConditionSolver

class TemporalConditionSolver(
self: ostk.astrodynamics.solver.TemporalConditionSolver,
time_step: ostk.physics.time.Duration,
tolerance: ostk.physics.time.Duration,
maximum_iteration_count: int = 500,
)

Bases: pybind11_object

Given a set of conditions and a time interval, the solver computes all sub-intervals over which conditions are met.

Constructor.

Parameters:

  • time_step (Duration) -- The time step.

  • tolerance (Duration) -- The tolerance of the solver.

  • maximum_iteration_count (int) -- The maximum number of iterations allowed.

Methods

get_maximum_iteration_count

Get the maximum number of iterations allowed.

get_time_step

Get the time step.

get_tolerance

Get the tolerance.

solve

Overloaded function.

get_maximum_iteration_count(
self: ostk.astrodynamics.solver.TemporalConditionSolver,
) → int

Get the maximum number of iterations allowed.

Returns:

The maximum number of iterations allowed.

Return type:

int

get_time_step(
self: ostk.astrodynamics.solver.TemporalConditionSolver,
) → ostk.physics.time.Duration

Get the time step.

Returns:

The time step.

Return type:

Duration

get_tolerance(
self: ostk.astrodynamics.solver.TemporalConditionSolver,
) → ostk.physics.time.Duration

Get the tolerance.

Returns:

The tolerance.

Return type:

Duration

solve(*args, **kwargs)

Overloaded function.

  1. solve(self: ostk.astrodynamics.solver.TemporalConditionSolver, condition: Callable[[ostk.physics.time.Instant], bool], interval: ostk.physics.time.Interval) -> List[ostk.physics.time.Interval]

    Solve a temporal condition.

    Args:

    condition (function): The condition to solve. interval (Interval): The interval to solve the condition over.

    Returns:

    Duration: The time at which the condition is satisfied.

  2. solve(self: ostk.astrodynamics.solver.TemporalConditionSolver, conditions: List[Callable[[ostk.physics.time.Instant], bool]], interval: ostk.physics.time.Interval) -> List[ostk.physics.time.Interval]

    Solve an array of temporal conditions.

    Args:

    conditions (list): The conditions to solve. interval (Interval): The interval to solve the conditions over.

    Returns:

    list: The times at which the conditions are satisfied.

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory.html index 3fb627224..8bf8fbfae 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

class LocalOrbitalFrameFactory

Bases: pybind11_object

The local orbital frame factory.

Methods

LVLH

Get a Local Vertical Local Horizontal (LVLH) local orbital frame factory.

NED

Get a North-East-Down (NED) local orbital frame factory.

QSW

Get a Quasi-Satellite World (QSW) local orbital frame factory.

TNW

Get a Topocentric North-West-Up (TNW) local orbital frame factory.

VNC

Get a Velocity-Normal-Co-normal (VNC) local orbital frame factory.

VVLH

Get a Velocity Local Vertical Local Horizontal (VVLH) local orbital frame factory.

access_parent_frame

Get the parent frame.

generate_frame

Generate a local orbital frame.

is_defined

Check if the local orbital frame factory is defined.

undefined

Get an undefined local orbital frame factory.

static LVLH(
parent_frame: ostk.physics.coordinate.Frame,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get a Local Vertical Local Horizontal (LVLH) local orbital frame factory.

Parameters:

parent_frame (Frame) -- The parent frame.

Returns:

The LVLH local orbital frame factory.

Return type:

LocalOrbitalFrameFactory

static NED(
parent_frame: ostk.physics.coordinate.Frame,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get a North-East-Down (NED) local orbital frame factory.

Parameters:

parent_frame (Frame) -- The parent frame.

Returns:

The NED local orbital frame factory.

Return type:

LocalOrbitalFrameFactory

static QSW(
parent_frame: ostk.physics.coordinate.Frame,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get a Quasi-Satellite World (QSW) local orbital frame factory.

Parameters:

parent_frame (Frame) -- The parent frame.

Returns:

The QSW local orbital frame factory.

Return type:

LocalOrbitalFrameFactory

static TNW(
parent_frame: ostk.physics.coordinate.Frame,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get a Topocentric North-West-Up (TNW) local orbital frame factory.

Parameters:

parent_frame (Frame) -- The parent frame.

Returns:

The TNW local orbital frame factory.

Return type:

LocalOrbitalFrameFactory

static VNC(
parent_frame: ostk.physics.coordinate.Frame,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get a Velocity-Normal-Co-normal (VNC) local orbital frame factory.

Parameters:

parent_frame (Frame) -- The parent frame.

Returns:

The VNC local orbital frame factory.

Return type:

LocalOrbitalFrameFactory

static VVLH(
parent_frame: ostk.physics.coordinate.Frame,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get a Velocity Local Vertical Local Horizontal (VVLH) local orbital frame factory.

Parameters:

parent_frame (Frame) -- The parent frame.

Returns:

The VVLH local orbital frame factory.

Return type:

LocalOrbitalFrameFactory

access_parent_frame(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory,
) → ostk.physics.coordinate.Frame

Get the parent frame.

Returns:

The parent frame.

Return type:

Frame

generate_frame(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory,
instant: ostk.physics.time.Instant,
position_vector: numpy.ndarray[numpy.float64[3, 1]],
velocity_vector: numpy.ndarray[numpy.float64[3, 1]],
) → ostk.physics.coordinate.Frame

Generate a local orbital frame.

Parameters:

  • instant (Instant) -- The instant.

  • position_vector (numpy.ndarray) -- The position vector.

  • velocity_vector (numpy.ndarray) -- The velocity vector.

Returns:

The local orbital frame.

Return type:

Frame

is_defined(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory,
) → bool

Check if the local orbital frame factory is defined.

Returns:

True if the local orbital frame factory is defined, False otherwise.

Return type:

Frame

static undefined() → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get an undefined local orbital frame factory.

Returns:

The undefined local orbital frame factory.

Return type:

LocalOrbitalFrameFactory

\ No newline at end of file + ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

class LocalOrbitalFrameFactory

Bases: pybind11_object

The local orbital frame factory.

Methods

LVLH

Get a Local Vertical Local Horizontal (LVLH) local orbital frame factory.

NED

Get a North-East-Down (NED) local orbital frame factory.

QSW

Get a Quasi-Satellite World (QSW) local orbital frame factory.

TNW

Get a Topocentric North-West-Up (TNW) local orbital frame factory.

VNC

Get a Velocity-Normal-Co-normal (VNC) local orbital frame factory.

VVLH

Get a Velocity Local Vertical Local Horizontal (VVLH) local orbital frame factory.

access_parent_frame

Get the parent frame.

generate_frame

Generate a local orbital frame.

is_defined

Check if the local orbital frame factory is defined.

undefined

Get an undefined local orbital frame factory.

static LVLH(
parent_frame: ostk.physics.coordinate.Frame,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get a Local Vertical Local Horizontal (LVLH) local orbital frame factory.

Parameters:

parent_frame (Frame) -- The parent frame.

Returns:

The LVLH local orbital frame factory.

Return type:

LocalOrbitalFrameFactory

static NED(
parent_frame: ostk.physics.coordinate.Frame,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get a North-East-Down (NED) local orbital frame factory.

Parameters:

parent_frame (Frame) -- The parent frame.

Returns:

The NED local orbital frame factory.

Return type:

LocalOrbitalFrameFactory

static QSW(
parent_frame: ostk.physics.coordinate.Frame,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get a Quasi-Satellite World (QSW) local orbital frame factory.

Parameters:

parent_frame (Frame) -- The parent frame.

Returns:

The QSW local orbital frame factory.

Return type:

LocalOrbitalFrameFactory

static TNW(
parent_frame: ostk.physics.coordinate.Frame,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get a Topocentric North-West-Up (TNW) local orbital frame factory.

Parameters:

parent_frame (Frame) -- The parent frame.

Returns:

The TNW local orbital frame factory.

Return type:

LocalOrbitalFrameFactory

static VNC(
parent_frame: ostk.physics.coordinate.Frame,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get a Velocity-Normal-Co-normal (VNC) local orbital frame factory.

Parameters:

parent_frame (Frame) -- The parent frame.

Returns:

The VNC local orbital frame factory.

Return type:

LocalOrbitalFrameFactory

static VVLH(
parent_frame: ostk.physics.coordinate.Frame,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get a Velocity Local Vertical Local Horizontal (VVLH) local orbital frame factory.

Parameters:

parent_frame (Frame) -- The parent frame.

Returns:

The VVLH local orbital frame factory.

Return type:

LocalOrbitalFrameFactory

access_parent_frame(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory,
) → ostk.physics.coordinate.Frame

Get the parent frame.

Returns:

The parent frame.

Return type:

Frame

generate_frame(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory,
instant: ostk.physics.time.Instant,
position_vector: numpy.ndarray[numpy.float64[3, 1]],
velocity_vector: numpy.ndarray[numpy.float64[3, 1]],
) → ostk.physics.coordinate.Frame

Generate a local orbital frame.

Parameters:

  • instant (Instant) -- The instant.

  • position_vector (numpy.ndarray) -- The position vector.

  • velocity_vector (numpy.ndarray) -- The velocity vector.

Returns:

The local orbital frame.

Return type:

Frame

is_defined(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory,
) → bool

Check if the local orbital frame factory is defined.

Returns:

True if the local orbital frame factory is defined, False otherwise.

Return type:

Frame

static undefined() → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get an undefined local orbital frame factory.

Returns:

The undefined local orbital frame factory.

Return type:

LocalOrbitalFrameFactory

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider.html index 2f4e1ac24..2b930ab70 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider

class LocalOrbitalFrameTransformProvider

Bases: pybind11_object

Local orbital frame transform provider, frame provider. Generates a specific transform based on instant, position, velocity and a LOF type.

Methods

get_transform_at

Returns the transform at a given instant.

is_defined

Returns true if the provider is defined.

class Type(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider.Type,
value: int,
)

Bases: pybind11_object

The local orbital frame type.

Members:

Undefined : Undefined

NED : North-East-Down

LVLH : Local Vertical-Local Horizontal

LVLHGD : Local Vertical-Local Horizontal Geodetic

VVLH : Vertical-Local Horizontal

QSW : Quasi-Satellite West

TNW : Topocentric North-West

VNC : Velocity-Normal-Co-normal

property name
get_transform_at(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider,
instant: ostk.physics.time.Instant,
) → ostk.physics.coordinate.Transform

Returns the transform at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The transform at the given instant.

Return type:

Transform

is_defined(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider,
) → bool

Returns true if the provider is defined.

Returns:

True if the provider is defined.

Return type:

bool

\ No newline at end of file + ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider

class LocalOrbitalFrameTransformProvider

Bases: pybind11_object

Local orbital frame transform provider, frame provider. Generates a specific transform based on instant, position, velocity and a LOF type.

Methods

get_transform_at

Returns the transform at a given instant.

is_defined

Returns true if the provider is defined.

class Type(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider.Type,
value: int,
)

Bases: pybind11_object

The local orbital frame type.

Members:

Undefined : Undefined

NED : North-East-Down

LVLH : Local Vertical-Local Horizontal

LVLHGD : Local Vertical-Local Horizontal Geodetic

VVLH : Vertical-Local Horizontal

QSW : Quasi-Satellite West

TNW : Topocentric North-West

VNC : Velocity-Normal-Co-normal

property name
get_transform_at(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider,
instant: ostk.physics.time.Instant,
) → ostk.physics.coordinate.Transform

Returns the transform at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The transform at the given instant.

Return type:

Transform

is_defined(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider,
) → bool

Returns true if the provider is defined.

Returns:

True if the provider is defined.

Return type:

bool

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.Model.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.Model.html index fe3e72b9a..21c11680e 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.Model.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.Model.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.Model — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.Model

class Model

Bases: pybind11_object

Orbital model.

Methods

calculate_state_at

Calculate the state at a given instant.

calculate_states_at

Calculate the states at given instants.

is_defined

Check if the model is defined.

calculate_state_at(
self: ostk.astrodynamics.trajectory.Model,
instant: ostk.physics.time.Instant,
) → ostk.astrodynamics.trajectory.State

Calculate the state at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state at the given instant.

Return type:

State

calculate_states_at(
self: ostk.astrodynamics.trajectory.Model,
instants: List[ostk.physics.time.Instant],
) → List[ostk.astrodynamics.trajectory.State]

Calculate the states at given instants. It can be more performant than looping calculate_state_at for multiple instants.

@param instants The instants.

Returns:

The states at the given instants.

Return type:

Array<State>

is_defined(self: ostk.astrodynamics.trajectory.Model) → bool

Check if the model is defined.

Returns:

True if the model is defined, False otherwise.

Return type:

bool

\ No newline at end of file + ostk.astrodynamics.trajectory.Model — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.Model

class Model

Bases: pybind11_object

Orbital model.

Methods

calculate_state_at

Calculate the state at a given instant.

calculate_states_at

Calculate the states at given instants.

is_defined

Check if the model is defined.

calculate_state_at(
self: ostk.astrodynamics.trajectory.Model,
instant: ostk.physics.time.Instant,
) → ostk.astrodynamics.trajectory.State

Calculate the state at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state at the given instant.

Return type:

State

calculate_states_at(
self: ostk.astrodynamics.trajectory.Model,
instants: List[ostk.physics.time.Instant],
) → List[ostk.astrodynamics.trajectory.State]

Calculate the states at given instants. It can be more performant than looping calculate_state_at for multiple instants.

@param instants The instants.

Returns:

The states at the given instants.

Return type:

Array<State>

is_defined(self: ostk.astrodynamics.trajectory.Model) → bool

Check if the model is defined.

Returns:

True if the model is defined, False otherwise.

Return type:

bool

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.Orbit.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.Orbit.html index 01e3cf791..c844a693b 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.Orbit.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.Orbit.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.Orbit — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.Orbit

class Orbit(*args, **kwargs)

Bases: Trajectory

Gravitationally curved trajectory of an object.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.Orbit, model: ostk::astrodynamics::trajectory::orbit::Model, celestial_object: ostk.physics.environment.object.Celestial) -> None

    Constructs an Orbit object.

    Args:

    model (orbit.Model): The orbit model. celestial_object (Celestial): The celestial object.

  2. __init__(self: ostk.astrodynamics.trajectory.Orbit, states: List[ostk.astrodynamics.trajectory.State], initial_revolution_number: ostk.core.type.Integer, celestial_object: ostk.physics.environment.object.Celestial) -> None

    Constructs an Orbit object.

    Args:

    states (Array<State>): The states. initial_revolution_number (Integer): The initial revolution number. celestial_object (Celestial): The celestial object.

Methods

access_kepler_model

Access the Kepler orbit model.

access_model

Access the orbit model.

access_propagated_model

Access the propagated orbit model.

access_sgp4_model

Access the SGP4 orbit model.

access_tabulated_model

Access the tabulated orbit model.

circular

Create a circular Orbit object.

circular_equatorial

Create a circular equatorial Orbit object.

compute_passes

Compute passes from a set of states.

equatorial

Create an equatorial Orbit object.

geo_synchronous

Create a geosynchronous Orbit object.

get_orbital_frame

Get the orbital frame.

get_pass_at

Get the pass at a given instant.

get_pass_with_revolution_number

Get the pass with a given revolution number.

get_revolution_number_at

Get the revolution number at a given instant.

get_state_at

Get the state of the trajectory at a given instant.

get_states_at

Get the states of the trajectory at a given set of instants.

is_defined

Check if the Orbit object is defined.

position

Create a Trajectory object representing a position.

sun_synchronous

Create a sun-synchronous Orbit object.

undefined

Get an undefined Orbit object.

class FrameType(self: ostk.astrodynamics.trajectory.Orbit.FrameType, value: int)

Bases: pybind11_object

The local orbital frame type.

Members:

Undefined : Undefined

NED : North-East-Down

LVLH : Local Vertical-Local Horizontal

LVLHGD : Local Vertical-Local Horizontal GeoDetic

LVLHGDGT : Local Vertical-Local Horizontal GeoDetic Ground Track

VVLH : Vertical-Local Horizontal

QSW : Quasi-Satellite West

TNW : Topocentric North-West

VNC : Velocity-Normal-Co-normal

property name
access_kepler_model(
self: ostk.astrodynamics.trajectory.Orbit,
) → ostk::astrodynamics::trajectory::orbit::model::Kepler

Access the Kepler orbit model.

Returns:

The Kepler orbit model.

Return type:

Kepler

access_model(
self: ostk.astrodynamics.trajectory.Orbit,
) → ostk::astrodynamics::trajectory::Model

Access the orbit model.

Returns:

The orbit model.

Return type:

orbit.Model

access_propagated_model(
self: ostk.astrodynamics.trajectory.Orbit,
) → ostk::astrodynamics::trajectory::orbit::model::Propagated

Access the propagated orbit model.

Returns:

The propagated orbit model.

Return type:

Propagated

access_sgp4_model(
self: ostk.astrodynamics.trajectory.Orbit,
) → ostk::astrodynamics::trajectory::orbit::model::SGP4

Access the SGP4 orbit model.

Returns:

The SGP4 orbit model.

Return type:

SGP4

access_tabulated_model(
self: ostk.astrodynamics.trajectory.Orbit,
) → ostk::astrodynamics::trajectory::orbit::model::Tabulated

Access the tabulated orbit model.

Returns:

The tabulated orbit model.

Return type:

Tabulated

static circular(
epoch: ostk.physics.time.Instant,
altitude: ostk.physics.unit.Length,
inclination: ostk.physics.unit.Angle,
celestial_object: ostk.physics.environment.object.Celestial,
) → ostk.astrodynamics.trajectory.Orbit

Create a circular Orbit object.

Parameters:

  • epoch (Instant) -- The epoch.

  • altitude (Length) -- The altitude.

  • inclination (Angle) -- The inclination.

  • celestial_object (Celestial) -- The celestial object.

Returns:

The circular Orbit object.

Return type:

Orbit

static circular_equatorial(
epoch: ostk.physics.time.Instant,
altitude: ostk.physics.unit.Length,
celestial_object: ostk.physics.environment.object.Celestial,
) → ostk.astrodynamics.trajectory.Orbit

Create a circular equatorial Orbit object.

Parameters:

  • epoch (Instant) -- The epoch.

  • altitude (Length) -- The altitude.

  • celestial_object (Celestial) -- The celestial object.

Returns:

The circular equatorial Orbit object.

Return type:

Orbit

static compute_passes(
states: List[ostk.astrodynamics.trajectory.State],
initial_revolution_number: ostk.core.type.Integer,
) → List[Tuple[int, ostk::astrodynamics::trajectory::orbit::Pass]]

Compute passes from a set of states.

Parameters:

  • states (Array<State>) -- The states.

  • initial_revolution_number (Integer) -- The initial revolution number.

Returns:

List of index-pass pairs

Return type:

list[tuple[int, Pass]]

static equatorial(
epoch: ostk.physics.time.Instant,
apoapsis_altitude: ostk.physics.unit.Length,
periapsis_altitude: ostk.physics.unit.Length,
celestial_object: ostk.physics.environment.object.Celestial,
) → ostk.astrodynamics.trajectory.Orbit

Create an equatorial Orbit object.

Parameters:

  • epoch (Instant) -- The epoch.

  • apoapsis_altitude (Length) -- The apoapsis altitude.

  • periapsis_altitude (Length) -- The periapsis altitude.

  • celestial_object (Celestial) -- The celestial object.

Returns:

The equatorial Orbit object.

Return type:

Orbit

static geo_synchronous(
epoch: ostk.physics.time.Instant,
inclination: ostk.physics.unit.Angle,
longitude: ostk.physics.unit.Angle,
celestial_object: ostk.physics.environment.object.Celestial,
) → ostk.astrodynamics.trajectory.Orbit

Create a geosynchronous Orbit object.

Parameters:

  • epoch (Instant) -- The epoch.

  • inclination (Angle) -- The inclination.

  • longitude (double) -- The longitude.

  • celestial_object (Celestial) -- The celestial object.

Returns:

The geosynchronous Orbit object.

Return type:

Orbit

get_orbital_frame(
self: ostk.astrodynamics.trajectory.Orbit,
frame_type: ostk.astrodynamics.trajectory.Orbit.FrameType,
) → ostk.physics.coordinate.Frame

Get the orbital frame.

Parameters:

frame_type (Orbit::FrameType) -- The frame type.

Returns:

The orbital frame.

Return type:

Frame

get_pass_at(
self: ostk.astrodynamics.trajectory.Orbit,
instant: ostk.physics.time.Instant,
) → ostk::astrodynamics::trajectory::orbit::Pass

Get the pass at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The pass.

Return type:

ostk::astrodynamics::trajectory::orbit::Pass

get_pass_with_revolution_number(
self: ostk.astrodynamics.trajectory.Orbit,
revolution_number: ostk.core.type.Integer,
) → ostk::astrodynamics::trajectory::orbit::Pass

Get the pass with a given revolution number.

Parameters:

revolution_number (int) -- The revolution number.

Returns:

The pass.

Return type:

Pass

get_revolution_number_at(
self: ostk.astrodynamics.trajectory.Orbit,
instant: ostk.physics.time.Instant,
) → ostk.core.type.Integer

Get the revolution number at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The revolution number.

Return type:

int

get_state_at(
self: ostk.astrodynamics.Trajectory,
instant: ostk.physics.time.Instant,
) → ostk::astrodynamics::trajectory::State

Get the state of the trajectory at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state of the trajectory at the given instant.

Return type:

State

get_states_at(
self: ostk.astrodynamics.Trajectory,
instants: List[ostk.physics.time.Instant],
) → List[ostk::astrodynamics::trajectory::State]

Get the states of the trajectory at a given set of instants. It can be more performant than looping calculate_state_at for multiple instants.

Parameters:

instants (list[Instant]) -- The instants.

Returns:

The states of the trajectory at the given instants.

Return type:

list[State]

is_defined(self: ostk.astrodynamics.trajectory.Orbit) → bool

Check if the Orbit object is defined.

Returns:

True if the Orbit object is defined, False otherwise.

Return type:

bool

static position(
position: ostk.physics.coordinate.Position,
) → ostk.astrodynamics.Trajectory

Create a Trajectory object representing a position.

Parameters:

position (Position) -- The position.

Returns:

The Trajectory object representing the position.

Return type:

Trajectory

static sun_synchronous(
epoch: ostk.physics.time.Instant,
altitude: ostk.physics.unit.Length,
local_time_at_descending_node: ostk.physics.time.Time,
celestial_object: ostk.physics.environment.object.Celestial,
argument_of_latitude: ostk.physics.unit.Angle = Angle.zero(),
) → ostk.astrodynamics.trajectory.Orbit

Create a sun-synchronous Orbit object.

Parameters:

  • epoch (Instant) -- The epoch.

  • altitude (Length) -- The altitude.

  • local_time_at_descending_node (Time) -- The local time at descending node.

  • celestial_object (Celestial) -- The celestial object.

  • argument_of_latitude (Angle) -- The argument of latitude.

Returns:

The sun-synchronous Orbit object.

Return type:

Orbit

static undefined() → ostk.astrodynamics.trajectory.Orbit

Get an undefined Orbit object.

Returns:

The undefined Orbit object.

Return type:

Orbit

\ No newline at end of file + ostk.astrodynamics.trajectory.Orbit — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.Orbit

class Orbit(*args, **kwargs)

Bases: Trajectory

Gravitationally curved trajectory of an object.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.Orbit, model: ostk::astrodynamics::trajectory::orbit::Model, celestial_object: ostk.physics.environment.object.Celestial) -> None

    Constructs an Orbit object.

    Args:

    model (orbit.Model): The orbit model. celestial_object (Celestial): The celestial object.

  2. __init__(self: ostk.astrodynamics.trajectory.Orbit, states: List[ostk.astrodynamics.trajectory.State], initial_revolution_number: ostk.core.type.Integer, celestial_object: ostk.physics.environment.object.Celestial) -> None

    Constructs an Orbit object.

    Args:

    states (Array<State>): The states. initial_revolution_number (Integer): The initial revolution number. celestial_object (Celestial): The celestial object.

Methods

access_kepler_model

Access the Kepler orbit model.

access_model

Access the orbit model.

access_propagated_model

Access the propagated orbit model.

access_sgp4_model

Access the SGP4 orbit model.

access_tabulated_model

Access the tabulated orbit model.

circular

Create a circular Orbit object.

circular_equatorial

Create a circular equatorial Orbit object.

compute_passes

Compute passes from a set of states.

equatorial

Create an equatorial Orbit object.

geo_synchronous

Create a geosynchronous Orbit object.

get_orbital_frame

Get the orbital frame.

get_pass_at

Get the pass at a given instant.

get_pass_with_revolution_number

Get the pass with a given revolution number.

get_revolution_number_at

Get the revolution number at a given instant.

get_state_at

Get the state of the trajectory at a given instant.

get_states_at

Get the states of the trajectory at a given set of instants.

is_defined

Check if the Orbit object is defined.

position

Create a Trajectory object representing a position.

sun_synchronous

Create a sun-synchronous Orbit object.

undefined

Get an undefined Orbit object.

class FrameType(self: ostk.astrodynamics.trajectory.Orbit.FrameType, value: int)

Bases: pybind11_object

The local orbital frame type.

Members:

Undefined : Undefined

NED : North-East-Down

LVLH : Local Vertical-Local Horizontal

LVLHGD : Local Vertical-Local Horizontal GeoDetic

LVLHGDGT : Local Vertical-Local Horizontal GeoDetic Ground Track

VVLH : Vertical-Local Horizontal

QSW : Quasi-Satellite West

TNW : Topocentric North-West

VNC : Velocity-Normal-Co-normal

property name
access_kepler_model(
self: ostk.astrodynamics.trajectory.Orbit,
) → ostk::astrodynamics::trajectory::orbit::model::Kepler

Access the Kepler orbit model.

Returns:

The Kepler orbit model.

Return type:

Kepler

access_model(
self: ostk.astrodynamics.trajectory.Orbit,
) → ostk::astrodynamics::trajectory::Model

Access the orbit model.

Returns:

The orbit model.

Return type:

orbit.Model

access_propagated_model(
self: ostk.astrodynamics.trajectory.Orbit,
) → ostk::astrodynamics::trajectory::orbit::model::Propagated

Access the propagated orbit model.

Returns:

The propagated orbit model.

Return type:

Propagated

access_sgp4_model(
self: ostk.astrodynamics.trajectory.Orbit,
) → ostk::astrodynamics::trajectory::orbit::model::SGP4

Access the SGP4 orbit model.

Returns:

The SGP4 orbit model.

Return type:

SGP4

access_tabulated_model(
self: ostk.astrodynamics.trajectory.Orbit,
) → ostk::astrodynamics::trajectory::orbit::model::Tabulated

Access the tabulated orbit model.

Returns:

The tabulated orbit model.

Return type:

Tabulated

static circular(
epoch: ostk.physics.time.Instant,
altitude: ostk.physics.unit.Length,
inclination: ostk.physics.unit.Angle,
celestial_object: ostk.physics.environment.object.Celestial,
) → ostk.astrodynamics.trajectory.Orbit

Create a circular Orbit object.

Parameters:

  • epoch (Instant) -- The epoch.

  • altitude (Length) -- The altitude.

  • inclination (Angle) -- The inclination.

  • celestial_object (Celestial) -- The celestial object.

Returns:

The circular Orbit object.

Return type:

Orbit

static circular_equatorial(
epoch: ostk.physics.time.Instant,
altitude: ostk.physics.unit.Length,
celestial_object: ostk.physics.environment.object.Celestial,
) → ostk.astrodynamics.trajectory.Orbit

Create a circular equatorial Orbit object.

Parameters:

  • epoch (Instant) -- The epoch.

  • altitude (Length) -- The altitude.

  • celestial_object (Celestial) -- The celestial object.

Returns:

The circular equatorial Orbit object.

Return type:

Orbit

static compute_passes(
states: List[ostk.astrodynamics.trajectory.State],
initial_revolution_number: ostk.core.type.Integer,
) → List[Tuple[int, ostk::astrodynamics::trajectory::orbit::Pass]]

Compute passes from a set of states.

Parameters:

  • states (Array<State>) -- The states.

  • initial_revolution_number (Integer) -- The initial revolution number.

Returns:

List of index-pass pairs

Return type:

list[tuple[int, Pass]]

static equatorial(
epoch: ostk.physics.time.Instant,
apoapsis_altitude: ostk.physics.unit.Length,
periapsis_altitude: ostk.physics.unit.Length,
celestial_object: ostk.physics.environment.object.Celestial,
) → ostk.astrodynamics.trajectory.Orbit

Create an equatorial Orbit object.

Parameters:

  • epoch (Instant) -- The epoch.

  • apoapsis_altitude (Length) -- The apoapsis altitude.

  • periapsis_altitude (Length) -- The periapsis altitude.

  • celestial_object (Celestial) -- The celestial object.

Returns:

The equatorial Orbit object.

Return type:

Orbit

static geo_synchronous(
epoch: ostk.physics.time.Instant,
inclination: ostk.physics.unit.Angle,
longitude: ostk.physics.unit.Angle,
celestial_object: ostk.physics.environment.object.Celestial,
) → ostk.astrodynamics.trajectory.Orbit

Create a geosynchronous Orbit object.

Parameters:

  • epoch (Instant) -- The epoch.

  • inclination (Angle) -- The inclination.

  • longitude (double) -- The longitude.

  • celestial_object (Celestial) -- The celestial object.

Returns:

The geosynchronous Orbit object.

Return type:

Orbit

get_orbital_frame(
self: ostk.astrodynamics.trajectory.Orbit,
frame_type: ostk.astrodynamics.trajectory.Orbit.FrameType,
) → ostk.physics.coordinate.Frame

Get the orbital frame.

Parameters:

frame_type (Orbit::FrameType) -- The frame type.

Returns:

The orbital frame.

Return type:

Frame

get_pass_at(
self: ostk.astrodynamics.trajectory.Orbit,
instant: ostk.physics.time.Instant,
) → ostk::astrodynamics::trajectory::orbit::Pass

Get the pass at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The pass.

Return type:

ostk::astrodynamics::trajectory::orbit::Pass

get_pass_with_revolution_number(
self: ostk.astrodynamics.trajectory.Orbit,
revolution_number: ostk.core.type.Integer,
) → ostk::astrodynamics::trajectory::orbit::Pass

Get the pass with a given revolution number.

Parameters:

revolution_number (int) -- The revolution number.

Returns:

The pass.

Return type:

Pass

get_revolution_number_at(
self: ostk.astrodynamics.trajectory.Orbit,
instant: ostk.physics.time.Instant,
) → ostk.core.type.Integer

Get the revolution number at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The revolution number.

Return type:

int

get_state_at(
self: ostk.astrodynamics.Trajectory,
instant: ostk.physics.time.Instant,
) → ostk::astrodynamics::trajectory::State

Get the state of the trajectory at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state of the trajectory at the given instant.

Return type:

State

get_states_at(
self: ostk.astrodynamics.Trajectory,
instants: List[ostk.physics.time.Instant],
) → List[ostk::astrodynamics::trajectory::State]

Get the states of the trajectory at a given set of instants. It can be more performant than looping calculate_state_at for multiple instants.

Parameters:

instants (list[Instant]) -- The instants.

Returns:

The states of the trajectory at the given instants.

Return type:

list[State]

is_defined(self: ostk.astrodynamics.trajectory.Orbit) → bool

Check if the Orbit object is defined.

Returns:

True if the Orbit object is defined, False otherwise.

Return type:

bool

static position(
position: ostk.physics.coordinate.Position,
) → ostk.astrodynamics.Trajectory

Create a Trajectory object representing a position.

Parameters:

position (Position) -- The position.

Returns:

The Trajectory object representing the position.

Return type:

Trajectory

static sun_synchronous(
epoch: ostk.physics.time.Instant,
altitude: ostk.physics.unit.Length,
local_time_at_descending_node: ostk.physics.time.Time,
celestial_object: ostk.physics.environment.object.Celestial,
argument_of_latitude: ostk.physics.unit.Angle = Angle.zero(),
) → ostk.astrodynamics.trajectory.Orbit

Create a sun-synchronous Orbit object.

Parameters:

  • epoch (Instant) -- The epoch.

  • altitude (Length) -- The altitude.

  • local_time_at_descending_node (Time) -- The local time at descending node.

  • celestial_object (Celestial) -- The celestial object.

  • argument_of_latitude (Angle) -- The argument of latitude.

Returns:

The sun-synchronous Orbit object.

Return type:

Orbit

static undefined() → ostk.astrodynamics.trajectory.Orbit

Get an undefined Orbit object.

Returns:

The undefined Orbit object.

Return type:

Orbit

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.Propagator.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.Propagator.html index 5fd65c257..4df5479a2 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.Propagator.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.Propagator.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.Propagator — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.Propagator

class Propagator(*args, **kwargs)

Bases: pybind11_object

A Propagator that propagates the provided State using it's NumericalSolver under the set Dynamics.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.Propagator, numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver, dynamics: List[ostk.astrodynamics.Dynamics] = []) -> None

    Construct a new Propagator object.

    Args:

    numerical_solver (NumericalSolver) The numerical solver. dynamics (list[Dynamics], optional) The dynamics.

    Returns:

    Propagator: The new Propagator object.

  2. __init__(self: ostk.astrodynamics.trajectory.Propagator, numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver, dynamics: List[ostk.astrodynamics.Dynamics], maneuvers: List[ostk.astrodynamics.flight.Maneuver], interpolation_type: ostk.mathematics.curve_fitting.Interpolator.Type = <Type.BarycentricRational: 0>) -> None

    Construct a new Propagator object with maneuvers.

    Args:

    numerical_solver (NumericalSolver) The numerical solver. dynamics (list[Dynamics]) The dynamics. maneuvers (list[Maneuver]) The maneuvers. interpolation_type (Interpolator.Type, optional) The interpolation type. Defaults to Barycentric Rational.

    Returns:

    Propagator: The new Propagator object.

Methods

access_numerical_solver

Access the numerical solver.

add_dynamics

Add dynamics.

add_maneuver

Add a maneuver.

calculate_state_at

Calculate the state at a given instant.

calculate_state_to_condition

Calculate the state up to a given event condition.

calculate_states_at

Calculate the states at given instants.

clear_dynamics

Clear the dynamics.

default

Overloaded function.

from_environment

Create a propagator from an environment.

get_dynamics

Get the dynamics.

get_number_of_coordinates

Get the number of coordinates.

is_defined

Check if the propagator is defined.

set_dynamics

Set the dynamics.

access_numerical_solver(
self: ostk.astrodynamics.trajectory.Propagator,
) → ostk.astrodynamics.trajectory.state.NumericalSolver

Access the numerical solver.

Returns:

The numerical solver.

Return type:

NumericalSolver&

add_dynamics(
self: ostk.astrodynamics.trajectory.Propagator,
dynamics: ostk.astrodynamics.Dynamics,
) → None

Add dynamics.

Parameters:

dynamics (Dynamics)

add_maneuver(
self: ostk.astrodynamics.trajectory.Propagator,
maneuver: ostk.astrodynamics.flight.Maneuver,
interpolation_type: ostk.mathematics.curve_fitting.Interpolator.Type = <Type.BarycentricRational: 0>,
) → None

Add a maneuver.

Parameters:

  • maneuver (Maneuver)

  • interpolation_type (Interpolator.Type, optional)

calculate_state_at(
self: ostk.astrodynamics.trajectory.Propagator,
state: ostk.astrodynamics.trajectory.State,
instant: ostk.physics.time.Instant,
) → ostk.astrodynamics.trajectory.State

Calculate the state at a given instant.

Parameters:

  • state (State)

  • instant (Instant)

Returns:

The state at the given instant.

Return type:

State

calculate_state_to_condition(
self: ostk.astrodynamics.trajectory.Propagator,
state: ostk.astrodynamics.trajectory.State,
instant: ostk.physics.time.Instant,
event_condition: ostk::astrodynamics::EventCondition,
) → ostk.astrodynamics.trajectory.state.NumericalSolver.ConditionSolution

Calculate the state up to a given event condition.

Parameters:
Returns:

The state up to the given event condition.

Return type:

State

calculate_states_at(
self: ostk.astrodynamics.trajectory.Propagator,
state: ostk.astrodynamics.trajectory.State,
instants: List[ostk.physics.time.Instant],
) → List[ostk.astrodynamics.trajectory.State]

Calculate the states at given instants. It is more performant than looping calculate_state_at for multiple instants.

Parameters:
Returns:

The states at the given instants.

Return type:

list[State]

clear_dynamics(self: ostk.astrodynamics.trajectory.Propagator) → None

Clear the dynamics.

static default(*args, **kwargs)

Overloaded function.

  1. default() -> ostk.astrodynamics.trajectory.Propagator

    Get the default propagator.

    Returns:

    Propagator: The default propagator.

  2. default(environment: ostk.physics.Environment) -> ostk.astrodynamics.trajectory.Propagator

    Get the default propagator for a given environment.

    Args:

    environment (Environment) The environment.

    Returns:

    Propagator: The default propagator for the given environment.

static from_environment(
numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver,
environment: ostk.physics.Environment,
) → ostk.astrodynamics.trajectory.Propagator

Create a propagator from an environment.

Parameters:
Returns:

The propagator.

Return type:

Propagator

get_dynamics(
self: ostk.astrodynamics.trajectory.Propagator,
) → List[ostk.astrodynamics.Dynamics]

Get the dynamics.

Returns:

The dynamics.

Return type:

list[Dynamics]

get_number_of_coordinates(
self: ostk.astrodynamics.trajectory.Propagator,
) → int

Get the number of coordinates.

Returns:

The number of coordinates.

Return type:

int

is_defined(self: ostk.astrodynamics.trajectory.Propagator) → bool

Check if the propagator is defined.

Returns:

True if the propagator is defined, False otherwise.

Return type:

bool

set_dynamics(
self: ostk.astrodynamics.trajectory.Propagator,
dynamics: List[ostk.astrodynamics.Dynamics],
) → None

Set the dynamics.

Parameters:

dynamics (list[Dynamics])

\ No newline at end of file + ostk.astrodynamics.trajectory.Propagator — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.Propagator

class Propagator(*args, **kwargs)

Bases: pybind11_object

A Propagator that propagates the provided State using it's NumericalSolver under the set Dynamics.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.Propagator, numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver, dynamics: List[ostk.astrodynamics.Dynamics] = []) -> None

    Construct a new Propagator object.

    Args:

    numerical_solver (NumericalSolver) The numerical solver. dynamics (list[Dynamics], optional) The dynamics.

    Returns:

    Propagator: The new Propagator object.

  2. __init__(self: ostk.astrodynamics.trajectory.Propagator, numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver, dynamics: List[ostk.astrodynamics.Dynamics], maneuvers: List[ostk.astrodynamics.flight.Maneuver], interpolation_type: ostk.mathematics.curve_fitting.Interpolator.Type = <Type.BarycentricRational: 0>) -> None

    Construct a new Propagator object with maneuvers.

    Args:

    numerical_solver (NumericalSolver) The numerical solver. dynamics (list[Dynamics]) The dynamics. maneuvers (list[Maneuver]) The maneuvers. interpolation_type (Interpolator.Type, optional) The interpolation type. Defaults to Barycentric Rational.

    Returns:

    Propagator: The new Propagator object.

Methods

access_numerical_solver

Access the numerical solver.

add_dynamics

Add dynamics.

add_maneuver

Add a maneuver.

calculate_state_at

Calculate the state at a given instant.

calculate_state_to_condition

Calculate the state up to a given event condition.

calculate_states_at

Calculate the states at given instants.

clear_dynamics

Clear the dynamics.

default

Overloaded function.

from_environment

Create a propagator from an environment.

get_dynamics

Get the dynamics.

get_number_of_coordinates

Get the number of coordinates.

is_defined

Check if the propagator is defined.

set_dynamics

Set the dynamics.

access_numerical_solver(
self: ostk.astrodynamics.trajectory.Propagator,
) → ostk.astrodynamics.trajectory.state.NumericalSolver

Access the numerical solver.

Returns:

The numerical solver.

Return type:

NumericalSolver&

add_dynamics(
self: ostk.astrodynamics.trajectory.Propagator,
dynamics: ostk.astrodynamics.Dynamics,
) → None

Add dynamics.

Parameters:

dynamics (Dynamics)

add_maneuver(
self: ostk.astrodynamics.trajectory.Propagator,
maneuver: ostk.astrodynamics.flight.Maneuver,
interpolation_type: ostk.mathematics.curve_fitting.Interpolator.Type = <Type.BarycentricRational: 0>,
) → None

Add a maneuver.

Parameters:

  • maneuver (Maneuver)

  • interpolation_type (Interpolator.Type, optional)

calculate_state_at(
self: ostk.astrodynamics.trajectory.Propagator,
state: ostk.astrodynamics.trajectory.State,
instant: ostk.physics.time.Instant,
) → ostk.astrodynamics.trajectory.State

Calculate the state at a given instant.

Parameters:

  • state (State)

  • instant (Instant)

Returns:

The state at the given instant.

Return type:

State

calculate_state_to_condition(
self: ostk.astrodynamics.trajectory.Propagator,
state: ostk.astrodynamics.trajectory.State,
instant: ostk.physics.time.Instant,
event_condition: ostk::astrodynamics::EventCondition,
) → ostk.astrodynamics.trajectory.state.NumericalSolver.ConditionSolution

Calculate the state up to a given event condition.

Parameters:
Returns:

The state up to the given event condition.

Return type:

State

calculate_states_at(
self: ostk.astrodynamics.trajectory.Propagator,
state: ostk.astrodynamics.trajectory.State,
instants: List[ostk.physics.time.Instant],
) → List[ostk.astrodynamics.trajectory.State]

Calculate the states at given instants. It is more performant than looping calculate_state_at for multiple instants.

Parameters:
Returns:

The states at the given instants.

Return type:

list[State]

clear_dynamics(self: ostk.astrodynamics.trajectory.Propagator) → None

Clear the dynamics.

static default(*args, **kwargs)

Overloaded function.

  1. default() -> ostk.astrodynamics.trajectory.Propagator

    Get the default propagator.

    Returns:

    Propagator: The default propagator.

  2. default(environment: ostk.physics.Environment) -> ostk.astrodynamics.trajectory.Propagator

    Get the default propagator for a given environment.

    Args:

    environment (Environment) The environment.

    Returns:

    Propagator: The default propagator for the given environment.

static from_environment(
numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver,
environment: ostk.physics.Environment,
) → ostk.astrodynamics.trajectory.Propagator

Create a propagator from an environment.

Parameters:
Returns:

The propagator.

Return type:

Propagator

get_dynamics(
self: ostk.astrodynamics.trajectory.Propagator,
) → List[ostk.astrodynamics.Dynamics]

Get the dynamics.

Returns:

The dynamics.

Return type:

list[Dynamics]

get_number_of_coordinates(
self: ostk.astrodynamics.trajectory.Propagator,
) → int

Get the number of coordinates.

Returns:

The number of coordinates.

Return type:

int

is_defined(self: ostk.astrodynamics.trajectory.Propagator) → bool

Check if the propagator is defined.

Returns:

True if the propagator is defined, False otherwise.

Return type:

bool

set_dynamics(
self: ostk.astrodynamics.trajectory.Propagator,
dynamics: List[ostk.astrodynamics.Dynamics],
) → None

Set the dynamics.

Parameters:

dynamics (list[Dynamics])

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.Segment.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.Segment.html index f0ab51bc6..f92d9c1ca 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.Segment.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.Segment.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.Segment — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.Segment

class Segment

Bases: pybind11_object

A Segment that can be solved provided an initial State and termination Event Condition.

Methods

coast

Create a coast segment.

get_dynamics

Get the dynamics.

get_event_condition

Get the event condition.

get_name

Get the name of the segment.

get_numerical_solver

Get the numerical solver.

get_type

Get the type of the segment.

maneuver

Create a maneuver segment.

solve

Solve the segment.

class Solution(self: ostk.astrodynamics.trajectory.Segment.Solution, name: ostk.core.type.String, dynamics: List[ostk.astrodynamics.Dynamics], states: List[ostk.astrodynamics.trajectory.State], condition_is_satisfied: bool, segment_type: ostk::astrodynamics::trajectory::Segment::Type)

Bases: pybind11_object

The Solution object returned when a Segment is solved.

Construct a Segment Solution.

Parameters:

  • name (str) -- The name of the segment.

  • dynamics (list[Dynamics]) -- The dynamics.

  • states (list[State]) -- The states.

  • condition_is_satisfied (bool) -- Whether the event condition is satisfied.

  • segment_type (Type) -- The type of the segment.

access_end_instant(
self: ostk.astrodynamics.trajectory.Segment.Solution,
) → ostk.physics.time.Instant

Get the instant at which the segment ends.

Returns:

The instant at which the segment ends.

Return type:

Instant

access_start_instant(
self: ostk.astrodynamics.trajectory.Segment.Solution,
) → ostk.physics.time.Instant

Get the instant at which the segment starts.

Returns:

The instant at which the segment starts.

Return type:

Instant

calculate_states_at(
self: ostk.astrodynamics.trajectory.Segment.Solution,
instants: List[ostk.physics.time.Instant],
numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver,
) → List[ostk.astrodynamics.trajectory.State]

Calculate the states in this segment's solution at the given instants.

Parameters:

  • instants (list[Instant]) -- The instants at which the states will be calculated.

  • numerical_solver (NumericalSolver) -- The numerical solver used to calculate the states.

Returns:

The states at the provided instants.

Return type:

list[State]

compute_delta_mass(
self: ostk.astrodynamics.trajectory.Segment.Solution,
) → ostk.physics.unit.Mass

Compute the delta mass.

Returns:

The delta mass.

Return type:

Mass

compute_delta_v(
self: ostk.astrodynamics.trajectory.Segment.Solution,
specific_impulse: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the delta V.

Parameters:

specific_impulse (float) -- The specific impulse.

Returns:

The delta V (m/s).

Return type:

float

property condition_is_satisfied

Whether the event condition is satisfied.

Type:

bool

property dynamics

The dynamics.

Type:

Dynamics

extract_maneuvers(
self: ostk.astrodynamics.trajectory.Segment.Solution,
frame: ostk.physics.coordinate.Frame,
) → List[ostk.astrodynamics.flight.Maneuver]

Extract maneuvers from the (maneuvering) segment.

Returns:

The list of maneuvers.

Return type:

list[Maneuver]

get_all_dynamics_contributions(
self: ostk.astrodynamics.trajectory.Segment.Solution,
frame: ostk.physics.coordinate.Frame,
) → Dict[ostk.astrodynamics.Dynamics, numpy.ndarray[numpy.float64[m, n]]]

Compute the contributions of all segment's dynamics in the provided frame for all states assocated with the segment.

Parameters:

frame (Frame) -- The frame.

Returns:

The list of matrices with individual dynamics contributions.

Return type:

dict[Dynamics, np.ndarray]

get_dynamics_acceleration_contribution(
self: ostk.astrodynamics.trajectory.Segment.Solution,
dynamics: ostk.astrodynamics.Dynamics,
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, n]]

Compute the contribution of the provided dynamics to the acceleration in the provided frame for all states associated with the segment.

Parameters:

  • dynamics (Dynamics) -- The dynamics.

  • frame (Frame) -- The frame.

Returns:

The matrix of dynamics contributions to acceleration.

Return type:

np.ndarray

get_dynamics_contribution(
self: ostk.astrodynamics.trajectory.Segment.Solution,
dynamics: ostk.astrodynamics.Dynamics,
frame: ostk.physics.coordinate.Frame,
coordinate_subsets: List[ostk.astrodynamics.trajectory.state.CoordinateSubset] = [],
) → numpy.ndarray[numpy.float64[m, n]]

Compute the contribution of the provided dynamics in the provided frame for all states associated with the segment.

Parameters:

  • dynamics (Dynamics) -- The dynamics.

  • frame (Frame) -- The frame.

  • coordinate_subsets (list[CoordinateSubset], optional) -- A subset of the dynamics writing coordinate subsets to consider.

Returns:

The matrix of dynamics contributions for the selected coordinate subsets of the dynamics.

Return type:

MatrixXd

get_final_mass(
self: ostk.astrodynamics.trajectory.Segment.Solution,
) → ostk.physics.unit.Mass

Get the final mass.

Returns:

The final mass.

Return type:

Mass

get_initial_mass(
self: ostk.astrodynamics.trajectory.Segment.Solution,
) → ostk.physics.unit.Mass

Get the initial mass.

Returns:

The initial mass.

Return type:

Mass

get_propagation_duration(
self: ostk.astrodynamics.trajectory.Segment.Solution,
) → ostk.physics.time.Duration

Get the propagation duration.

Returns:

The propagation duration.

Return type:

Duration

property name

The name of the segment.

Type:

str

property segment_type

The type of the segment.

Type:

Type

property states

The states.

Type:

list[State]

class Type(self: ostk.astrodynamics.trajectory.Segment.Type, value: int)

Bases: pybind11_object

Segment type.

Members:

Coast : Coast

Maneuver : Maneuver

property name
static coast(name: ostk.core.type.String, event_condition: ostk::astrodynamics::EventCondition, dynamics: List[ostk.astrodynamics.Dynamics], numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver) → ostk.astrodynamics.trajectory.Segment

Create a coast segment.

Parameters:
Returns:

The coast segment.

Return type:

Segment

get_dynamics(
self: ostk.astrodynamics.trajectory.Segment,
) → List[ostk.astrodynamics.Dynamics]

Get the dynamics.

Returns:

The dynamics.

Return type:

Dynamics

get_event_condition(
self: ostk.astrodynamics.trajectory.Segment,
) → ostk::astrodynamics::EventCondition

Get the event condition.

Returns:

The event condition.

Return type:

EventCondition

get_name(self: ostk.astrodynamics.trajectory.Segment) → ostk.core.type.String

Get the name of the segment.

Returns:

The name of the segment.

Return type:

str

get_numerical_solver(
self: ostk.astrodynamics.trajectory.Segment,
) → ostk.astrodynamics.trajectory.state.NumericalSolver

Get the numerical solver.

Returns:

The numerical solver.

Return type:

NumericalSolver

get_type(
self: ostk.astrodynamics.trajectory.Segment,
) → ostk.astrodynamics.trajectory.Segment.Type

Get the type of the segment.

Returns:

The type of the segment.

Return type:

Type

static maneuver(name: ostk.core.type.String, event_condition: ostk::astrodynamics::EventCondition, thruster_dynamics: ostk.astrodynamics.dynamics.Thruster, dynamics: List[ostk.astrodynamics.Dynamics], numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver) → ostk.astrodynamics.trajectory.Segment

Create a maneuver segment.

Parameters:

  • name (str) -- The name of the segment.

  • event_condition (EventCondition) -- The event condition.

  • thruster_dynamics (ThrusterDynamics) -- The thruster dynamics.

  • dynamics (Dynamics) -- The dynamics.

  • numerical_solver (NumericalSolver) -- The numerical solver.

Returns:

The maneuver segment.

Return type:

Segment

solve(
self: ostk.astrodynamics.trajectory.Segment,
state: ostk.astrodynamics.trajectory.State,
maximum_propagation_duration: ostk.physics.time.Duration = Duration.days(30.0),
) → ostk.astrodynamics.trajectory.Segment.Solution

Solve the segment.

Parameters:

  • state (State) -- The state.

  • maximum_propagation_duration (Duration, optional) -- The maximum propagation duration.

Returns:

The segment solution.

Return type:

SegmentSolution

\ No newline at end of file + ostk.astrodynamics.trajectory.Segment — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.Segment

class Segment

Bases: pybind11_object

A Segment that can be solved provided an initial State and termination Event Condition.

Methods

coast

Create a coast segment.

get_dynamics

Get the dynamics.

get_event_condition

Get the event condition.

get_name

Get the name of the segment.

get_numerical_solver

Get the numerical solver.

get_type

Get the type of the segment.

maneuver

Create a maneuver segment.

solve

Solve the segment.

class Solution(self: ostk.astrodynamics.trajectory.Segment.Solution, name: ostk.core.type.String, dynamics: List[ostk.astrodynamics.Dynamics], states: List[ostk.astrodynamics.trajectory.State], condition_is_satisfied: bool, segment_type: ostk::astrodynamics::trajectory::Segment::Type)

Bases: pybind11_object

The Solution object returned when a Segment is solved.

Construct a Segment Solution.

Parameters:

  • name (str) -- The name of the segment.

  • dynamics (list[Dynamics]) -- The dynamics.

  • states (list[State]) -- The states.

  • condition_is_satisfied (bool) -- Whether the event condition is satisfied.

  • segment_type (Type) -- The type of the segment.

access_end_instant(
self: ostk.astrodynamics.trajectory.Segment.Solution,
) → ostk.physics.time.Instant

Get the instant at which the segment ends.

Returns:

The instant at which the segment ends.

Return type:

Instant

access_start_instant(
self: ostk.astrodynamics.trajectory.Segment.Solution,
) → ostk.physics.time.Instant

Get the instant at which the segment starts.

Returns:

The instant at which the segment starts.

Return type:

Instant

calculate_states_at(
self: ostk.astrodynamics.trajectory.Segment.Solution,
instants: List[ostk.physics.time.Instant],
numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver,
) → List[ostk.astrodynamics.trajectory.State]

Calculate the states in this segment's solution at the given instants.

Parameters:

  • instants (list[Instant]) -- The instants at which the states will be calculated.

  • numerical_solver (NumericalSolver) -- The numerical solver used to calculate the states.

Returns:

The states at the provided instants.

Return type:

list[State]

compute_delta_mass(
self: ostk.astrodynamics.trajectory.Segment.Solution,
) → ostk.physics.unit.Mass

Compute the delta mass.

Returns:

The delta mass.

Return type:

Mass

compute_delta_v(
self: ostk.astrodynamics.trajectory.Segment.Solution,
specific_impulse: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the delta V.

Parameters:

specific_impulse (float) -- The specific impulse.

Returns:

The delta V (m/s).

Return type:

float

property condition_is_satisfied

Whether the event condition is satisfied.

Type:

bool

property dynamics

The dynamics.

Type:

Dynamics

extract_maneuvers(
self: ostk.astrodynamics.trajectory.Segment.Solution,
frame: ostk.physics.coordinate.Frame,
) → List[ostk.astrodynamics.flight.Maneuver]

Extract maneuvers from the (maneuvering) segment.

Returns:

The list of maneuvers.

Return type:

list[Maneuver]

get_all_dynamics_contributions(
self: ostk.astrodynamics.trajectory.Segment.Solution,
frame: ostk.physics.coordinate.Frame,
) → Dict[ostk.astrodynamics.Dynamics, numpy.ndarray[numpy.float64[m, n]]]

Compute the contributions of all segment's dynamics in the provided frame for all states assocated with the segment.

Parameters:

frame (Frame) -- The frame.

Returns:

The list of matrices with individual dynamics contributions.

Return type:

dict[Dynamics, np.ndarray]

get_dynamics_acceleration_contribution(
self: ostk.astrodynamics.trajectory.Segment.Solution,
dynamics: ostk.astrodynamics.Dynamics,
frame: ostk.physics.coordinate.Frame,
) → numpy.ndarray[numpy.float64[m, n]]

Compute the contribution of the provided dynamics to the acceleration in the provided frame for all states associated with the segment.

Parameters:

  • dynamics (Dynamics) -- The dynamics.

  • frame (Frame) -- The frame.

Returns:

The matrix of dynamics contributions to acceleration.

Return type:

np.ndarray

get_dynamics_contribution(
self: ostk.astrodynamics.trajectory.Segment.Solution,
dynamics: ostk.astrodynamics.Dynamics,
frame: ostk.physics.coordinate.Frame,
coordinate_subsets: List[ostk.astrodynamics.trajectory.state.CoordinateSubset] = [],
) → numpy.ndarray[numpy.float64[m, n]]

Compute the contribution of the provided dynamics in the provided frame for all states associated with the segment.

Parameters:

  • dynamics (Dynamics) -- The dynamics.

  • frame (Frame) -- The frame.

  • coordinate_subsets (list[CoordinateSubset], optional) -- A subset of the dynamics writing coordinate subsets to consider.

Returns:

The matrix of dynamics contributions for the selected coordinate subsets of the dynamics.

Return type:

MatrixXd

get_final_mass(
self: ostk.astrodynamics.trajectory.Segment.Solution,
) → ostk.physics.unit.Mass

Get the final mass.

Returns:

The final mass.

Return type:

Mass

get_initial_mass(
self: ostk.astrodynamics.trajectory.Segment.Solution,
) → ostk.physics.unit.Mass

Get the initial mass.

Returns:

The initial mass.

Return type:

Mass

get_propagation_duration(
self: ostk.astrodynamics.trajectory.Segment.Solution,
) → ostk.physics.time.Duration

Get the propagation duration.

Returns:

The propagation duration.

Return type:

Duration

property name

The name of the segment.

Type:

str

property segment_type

The type of the segment.

Type:

Type

property states

The states.

Type:

list[State]

class Type(self: ostk.astrodynamics.trajectory.Segment.Type, value: int)

Bases: pybind11_object

Segment type.

Members:

Coast : Coast

Maneuver : Maneuver

property name
static coast(name: ostk.core.type.String, event_condition: ostk::astrodynamics::EventCondition, dynamics: List[ostk.astrodynamics.Dynamics], numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver) → ostk.astrodynamics.trajectory.Segment

Create a coast segment.

Parameters:
Returns:

The coast segment.

Return type:

Segment

get_dynamics(
self: ostk.astrodynamics.trajectory.Segment,
) → List[ostk.astrodynamics.Dynamics]

Get the dynamics.

Returns:

The dynamics.

Return type:

Dynamics

get_event_condition(
self: ostk.astrodynamics.trajectory.Segment,
) → ostk::astrodynamics::EventCondition

Get the event condition.

Returns:

The event condition.

Return type:

EventCondition

get_name(self: ostk.astrodynamics.trajectory.Segment) → ostk.core.type.String

Get the name of the segment.

Returns:

The name of the segment.

Return type:

str

get_numerical_solver(
self: ostk.astrodynamics.trajectory.Segment,
) → ostk.astrodynamics.trajectory.state.NumericalSolver

Get the numerical solver.

Returns:

The numerical solver.

Return type:

NumericalSolver

get_type(
self: ostk.astrodynamics.trajectory.Segment,
) → ostk.astrodynamics.trajectory.Segment.Type

Get the type of the segment.

Returns:

The type of the segment.

Return type:

Type

static maneuver(name: ostk.core.type.String, event_condition: ostk::astrodynamics::EventCondition, thruster_dynamics: ostk.astrodynamics.dynamics.Thruster, dynamics: List[ostk.astrodynamics.Dynamics], numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver) → ostk.astrodynamics.trajectory.Segment

Create a maneuver segment.

Parameters:

  • name (str) -- The name of the segment.

  • event_condition (EventCondition) -- The event condition.

  • thruster_dynamics (ThrusterDynamics) -- The thruster dynamics.

  • dynamics (Dynamics) -- The dynamics.

  • numerical_solver (NumericalSolver) -- The numerical solver.

Returns:

The maneuver segment.

Return type:

Segment

solve(
self: ostk.astrodynamics.trajectory.Segment,
state: ostk.astrodynamics.trajectory.State,
maximum_propagation_duration: ostk.physics.time.Duration = Duration.days(30.0),
) → ostk.astrodynamics.trajectory.Segment.Solution

Solve the segment.

Parameters:

  • state (State) -- The state.

  • maximum_propagation_duration (Duration, optional) -- The maximum propagation duration.

Returns:

The segment solution.

Return type:

SegmentSolution

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.Sequence.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.Sequence.html index 94c061bbd..d31dc6d29 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.Sequence.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.Sequence.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.Sequence — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.Sequence

class Sequence(
self: ostk.astrodynamics.trajectory.Sequence,
segments: List[ostk.astrodynamics.trajectory.Segment] = [],
numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver = NumericalSolver.default_conditional(),
dynamics: List[ostk.astrodynamics.Dynamics] = [],
maximum_propagation_duration: ostk.physics.time.Duration = duration.days(30.0),
verbosity: int = 1,
)

Bases: pybind11_object

A mission Sequence. Consists of a list of Segment objects and various configuration parameters.

Construct a new Sequence object.

Args: segments (list[Segment], optional): The segments. numerical_solver (NumericalSolver, optional): The numerical solver. dynamics (list[Dynamics], optional): The dynamics. maximum_propagation_duration (Duration, optional): The maximum propagation duration. verbosity (int, optional): The verbosity level.

Returns:

The new Sequence object.

Return type:

Sequence

Methods

add_coast_segment

Add a coast segment.

add_maneuver_segment

Add a maneuver segment.

add_segment

Add a segment.

add_segments

Add segments.

get_dynamics

Get the dynamics.

get_maximum_propagation_duration

Get the maximum propagation duration.

get_numerical_solver

Get the numerical solver.

get_segments

Get the segments.

solve

Solve the sequence.

solve_to_condition

Solve the sequence until the event condition is met.

class Solution(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
segment_solutions: List[ostk.astrodynamics.trajectory.Segment.Solution],
execution_is_complete: bool,
)

Bases: pybind11_object

The Solution object that is returned when a Sequence is solved.

Construct a new Sequence.Solution object.

Args: segment_solutions (list[Segment.Solution]): The segment solutions. execution_is_complete (bool): Whether the execution is complete.

Returns:

The new Sequence.Solution object.

Return type:

Sequence

access_end_instant(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
) → ostk.physics.time.Instant

Get the instant at which the access ends.

Returns:

The instant at which the access ends.

Return type:

Instant

access_start_instant(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
) → ostk.physics.time.Instant

Get the instant at which the access starts.

Returns:

The instant at which the access starts.

Return type:

Instant

calculate_states_at(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
instants: List[ostk.physics.time.Instant],
numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver,
) → List[ostk.astrodynamics.trajectory.State]

Calculate states in this sequence's solution at provided instants.

Parameters:

  • instants (list[Instant]) -- The instants at which the states will be calculated.

  • numerical_solver (NumericalSolver) -- The numerical solver used to calculate the states.

Returns:

The states at the provided instants.

Return type:

list[State]

compute_delta_mass(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
) → ostk.physics.unit.Mass

Compute the delta mass.

Returns:

The delta mass.

Return type:

float

compute_delta_v(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
specific_impulse: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the delta V.

Parameters:

specific_impulse (float) -- The specific impulse.

Returns:

The delta V (m/s).

Return type:

float

property execution_is_complete

Whether the execution is complete.

Type:

bool

get_final_mass(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
) → ostk.physics.unit.Mass

Get the final mass.

Returns:

The final mass.

Return type:

float

get_initial_mass(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
) → ostk.physics.unit.Mass

Get the initial mass.

Returns:

The initial mass.

Return type:

float

get_propagation_duration(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
) → ostk.physics.time.Duration

Get the propagation duration.

Returns:

The propagation duration.

Return type:

Duration

get_states(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
) → List[ostk.astrodynamics.trajectory.State]

Get the states.

Returns:

The states.

Return type:

list[State]

property segment_solutions

The solutions for each segment.

Type:

list[SegmentSolution]

add_coast_segment(
self: ostk.astrodynamics.trajectory.Sequence,
event_condition: ostk::astrodynamics::EventCondition,
) → None

Add a coast segment.

Parameters:

event_condition (EventCondition) -- The event condition.

add_maneuver_segment(
self: ostk.astrodynamics.trajectory.Sequence,
event_condition: ostk::astrodynamics::EventCondition,
thruster_dynamics: ostk.astrodynamics.dynamics.Thruster,
) → None

Add a maneuver segment.

Parameters:

  • event_condition (EventCondition) -- The event condition.

  • thruster_dynamics (Thruster) -- The thruster dynamics.

add_segment(
self: ostk.astrodynamics.trajectory.Sequence,
segment: ostk.astrodynamics.trajectory.Segment,
) → None

Add a segment.

Parameters:

segment (Segment) -- The segment.

add_segments(
self: ostk.astrodynamics.trajectory.Sequence,
segments: List[ostk.astrodynamics.trajectory.Segment],
) → None

Add segments.

Parameters:

segments (list[Segment]) -- The segments.

get_dynamics(
self: ostk.astrodynamics.trajectory.Sequence,
) → List[ostk.astrodynamics.Dynamics]

Get the dynamics.

Returns:

The dynamics.

Return type:

list[Dynamics]

get_maximum_propagation_duration(
self: ostk.astrodynamics.trajectory.Sequence,
) → ostk.physics.time.Duration

Get the maximum propagation duration.

Returns:

The maximum propagation duration.

Return type:

Duration

get_numerical_solver(
self: ostk.astrodynamics.trajectory.Sequence,
) → ostk.astrodynamics.trajectory.state.NumericalSolver

Get the numerical solver.

Returns:

The numerical solver.

Return type:

NumericalSolver

get_segments(
self: ostk.astrodynamics.trajectory.Sequence,
) → List[ostk.astrodynamics.trajectory.Segment]

Get the segments.

Returns:

The segments.

Return type:

list[Segment]

solve(
self: ostk.astrodynamics.trajectory.Sequence,
state: ostk.astrodynamics.trajectory.State,
repetition_count: int = 1,
) → ostk.astrodynamics.trajectory.Sequence.Solution

Solve the sequence.

Parameters:

  • state (State) -- The state.

  • repetition_count (int, optional) -- The repetition count. Defaults to 1.

Returns:

The sequence solution.

Return type:

SequenceSolution

solve_to_condition(
self: ostk.astrodynamics.trajectory.Sequence,
state: ostk.astrodynamics.trajectory.State,
event_condition: ostk::astrodynamics::EventCondition,
maximum_propagation_duration_limit: ostk.physics.time.Duration = Duration.days(30.0),
) → ostk.astrodynamics.trajectory.Sequence.Solution

Solve the sequence until the event condition is met.

In the case that the event condition is not met due to maximum propagation duration limit, it will return the SequenceSolution with executionIsComplete set to False.

Parameters:

  • state (State) -- The state.

  • event_condition (EventCondition) -- The event condition.

  • maximum_propagation_duration_limit (Duration, optional) -- The maximum propagation duration limit for the sequence. Defaults to 30 days.

Returns:

The sequence solution.

Return type:

SequenceSolution

\ No newline at end of file + ostk.astrodynamics.trajectory.Sequence — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.Sequence

class Sequence(
self: ostk.astrodynamics.trajectory.Sequence,
segments: List[ostk.astrodynamics.trajectory.Segment] = [],
numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver = NumericalSolver.default_conditional(),
dynamics: List[ostk.astrodynamics.Dynamics] = [],
maximum_propagation_duration: ostk.physics.time.Duration = duration.days(30.0),
verbosity: int = 1,
)

Bases: pybind11_object

A mission Sequence. Consists of a list of Segment objects and various configuration parameters.

Construct a new Sequence object.

Args: segments (list[Segment], optional): The segments. numerical_solver (NumericalSolver, optional): The numerical solver. dynamics (list[Dynamics], optional): The dynamics. maximum_propagation_duration (Duration, optional): The maximum propagation duration. verbosity (int, optional): The verbosity level.

Returns:

The new Sequence object.

Return type:

Sequence

Methods

add_coast_segment

Add a coast segment.

add_maneuver_segment

Add a maneuver segment.

add_segment

Add a segment.

add_segments

Add segments.

get_dynamics

Get the dynamics.

get_maximum_propagation_duration

Get the maximum propagation duration.

get_numerical_solver

Get the numerical solver.

get_segments

Get the segments.

solve

Solve the sequence.

solve_to_condition

Solve the sequence until the event condition is met.

class Solution(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
segment_solutions: List[ostk.astrodynamics.trajectory.Segment.Solution],
execution_is_complete: bool,
)

Bases: pybind11_object

The Solution object that is returned when a Sequence is solved.

Construct a new Sequence.Solution object.

Args: segment_solutions (list[Segment.Solution]): The segment solutions. execution_is_complete (bool): Whether the execution is complete.

Returns:

The new Sequence.Solution object.

Return type:

Sequence

access_end_instant(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
) → ostk.physics.time.Instant

Get the instant at which the access ends.

Returns:

The instant at which the access ends.

Return type:

Instant

access_start_instant(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
) → ostk.physics.time.Instant

Get the instant at which the access starts.

Returns:

The instant at which the access starts.

Return type:

Instant

calculate_states_at(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
instants: List[ostk.physics.time.Instant],
numerical_solver: ostk.astrodynamics.trajectory.state.NumericalSolver,
) → List[ostk.astrodynamics.trajectory.State]

Calculate states in this sequence's solution at provided instants.

Parameters:

  • instants (list[Instant]) -- The instants at which the states will be calculated.

  • numerical_solver (NumericalSolver) -- The numerical solver used to calculate the states.

Returns:

The states at the provided instants.

Return type:

list[State]

compute_delta_mass(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
) → ostk.physics.unit.Mass

Compute the delta mass.

Returns:

The delta mass.

Return type:

float

compute_delta_v(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
specific_impulse: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the delta V.

Parameters:

specific_impulse (float) -- The specific impulse.

Returns:

The delta V (m/s).

Return type:

float

property execution_is_complete

Whether the execution is complete.

Type:

bool

get_final_mass(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
) → ostk.physics.unit.Mass

Get the final mass.

Returns:

The final mass.

Return type:

float

get_initial_mass(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
) → ostk.physics.unit.Mass

Get the initial mass.

Returns:

The initial mass.

Return type:

float

get_propagation_duration(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
) → ostk.physics.time.Duration

Get the propagation duration.

Returns:

The propagation duration.

Return type:

Duration

get_states(
self: ostk.astrodynamics.trajectory.Sequence.Solution,
) → List[ostk.astrodynamics.trajectory.State]

Get the states.

Returns:

The states.

Return type:

list[State]

property segment_solutions

The solutions for each segment.

Type:

list[SegmentSolution]

add_coast_segment(
self: ostk.astrodynamics.trajectory.Sequence,
event_condition: ostk::astrodynamics::EventCondition,
) → None

Add a coast segment.

Parameters:

event_condition (EventCondition) -- The event condition.

add_maneuver_segment(
self: ostk.astrodynamics.trajectory.Sequence,
event_condition: ostk::astrodynamics::EventCondition,
thruster_dynamics: ostk.astrodynamics.dynamics.Thruster,
) → None

Add a maneuver segment.

Parameters:

  • event_condition (EventCondition) -- The event condition.

  • thruster_dynamics (Thruster) -- The thruster dynamics.

add_segment(
self: ostk.astrodynamics.trajectory.Sequence,
segment: ostk.astrodynamics.trajectory.Segment,
) → None

Add a segment.

Parameters:

segment (Segment) -- The segment.

add_segments(
self: ostk.astrodynamics.trajectory.Sequence,
segments: List[ostk.astrodynamics.trajectory.Segment],
) → None

Add segments.

Parameters:

segments (list[Segment]) -- The segments.

get_dynamics(
self: ostk.astrodynamics.trajectory.Sequence,
) → List[ostk.astrodynamics.Dynamics]

Get the dynamics.

Returns:

The dynamics.

Return type:

list[Dynamics]

get_maximum_propagation_duration(
self: ostk.astrodynamics.trajectory.Sequence,
) → ostk.physics.time.Duration

Get the maximum propagation duration.

Returns:

The maximum propagation duration.

Return type:

Duration

get_numerical_solver(
self: ostk.astrodynamics.trajectory.Sequence,
) → ostk.astrodynamics.trajectory.state.NumericalSolver

Get the numerical solver.

Returns:

The numerical solver.

Return type:

NumericalSolver

get_segments(
self: ostk.astrodynamics.trajectory.Sequence,
) → List[ostk.astrodynamics.trajectory.Segment]

Get the segments.

Returns:

The segments.

Return type:

list[Segment]

solve(
self: ostk.astrodynamics.trajectory.Sequence,
state: ostk.astrodynamics.trajectory.State,
repetition_count: int = 1,
) → ostk.astrodynamics.trajectory.Sequence.Solution

Solve the sequence.

Parameters:

  • state (State) -- The state.

  • repetition_count (int, optional) -- The repetition count. Defaults to 1.

Returns:

The sequence solution.

Return type:

SequenceSolution

solve_to_condition(
self: ostk.astrodynamics.trajectory.Sequence,
state: ostk.astrodynamics.trajectory.State,
event_condition: ostk::astrodynamics::EventCondition,
maximum_propagation_duration_limit: ostk.physics.time.Duration = Duration.days(30.0),
) → ostk.astrodynamics.trajectory.Sequence.Solution

Solve the sequence until the event condition is met.

In the case that the event condition is not met due to maximum propagation duration limit, it will return the SequenceSolution with executionIsComplete set to False.

Parameters:

  • state (State) -- The state.

  • event_condition (EventCondition) -- The event condition.

  • maximum_propagation_duration_limit (Duration, optional) -- The maximum propagation duration limit for the sequence. Defaults to 30 days.

Returns:

The sequence solution.

Return type:

SequenceSolution

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.State.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.State.html index 0abf455ad..38e066992 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.State.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.State.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.State — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.State

class State(*args, **kwargs)

Bases: pybind11_object

This class represents the physical state of an object.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.State, instant: ostk.physics.time.Instant, position: ostk.physics.coordinate.Position, velocity: ostk.physics.coordinate.Velocity) -> None

    Utility constructor for Position/Velocity only.

    Args:

    instant (Instant): An instant position (Position): The cartesian position at the instant velocity (Velocity): The cartesian velocity at the instant

  2. __init__(self: ostk.astrodynamics.trajectory.State, instant: ostk.physics.time.Instant, position: ostk.physics.coordinate.Position, velocity: ostk.physics.coordinate.Velocity, attitude: ostk.mathematics.geometry.d3.transformation.rotation.Quaternion, angular_velocity: numpy.ndarray[numpy.float64[3, 1]], attitude_frame: ostk.physics.coordinate.Frame) -> None

    Utility constructor for Position/Velocity/Attitude/Angular velocity.

    Args:

    instant (Instant): An instant position (Position): The cartesian position at the instant velocity (Velocity): The cartesian velocity at the instant attitude (Quaternion): The attitude at the instant, representing the rotation required to go from the attitude reference frame to the satellite body frame angular_velocity (numpy.ndarray): The angular velocity at the instant, representing the angular velocity of the satellite body frame with respect ot teh attitude frame, expressed in body frame attitude_frame (Frame): The attitude reference frame

  3. __init__(self: ostk.astrodynamics.trajectory.State, instant: ostk.physics.time.Instant, coordinates: numpy.ndarray[numpy.float64[m, 1]], frame: ostk.physics.coordinate.Frame, coordinate_broker: ostk::astrodynamics::trajectory::state::CoordinateBroker) -> None

    Constructor with a pre-defined Coordinates Broker.

    Args:

    instant (Instant): An instant coordinates (numpy.ndarray): The coordinates at the instant in International System of Units frame (Frame): The reference frame in which the coordinates are referenced to and resolved in coordinate_broker (CoordinateBroker): The coordinate broker associated to the coordinates

  4. __init__(self: ostk.astrodynamics.trajectory.State, instant: ostk.physics.time.Instant, coordinates: numpy.ndarray[numpy.float64[m, 1]], frame: ostk.physics.coordinate.Frame, coordinate_subsets: List[ostk::astrodynamics::trajectory::state::CoordinateSubset]) -> None

    Constructor with coordinate subsets.

    Args:

    instant (Instant): An instant coordinates (numpy.ndarray): The coordinates at the instant in International System of Units frame (Frame): The reference frame in which the coordinates are referenced to and resolved in coordinate_subsets (CoordinateBroker): The coordinate subsets associated to the coordinates

  5. __init__(self: ostk.astrodynamics.trajectory.State, state: ostk.astrodynamics.trajectory.State) -> None

Methods

extract_coordinate

Extract the coordinates associated to a subset of the state.

extract_coordinates

Extract the coordinates associated to a set of subsets of the state.

get_angular_velocity

Get the angular velocity of the state.

get_attitude

Get the attitude of the state.

get_coordinate_subsets

Get the coordinate subsets associated to the state.

get_coordinates

Get the coordinates of the state.

get_frame

Get the reference frame of the state.

get_instant

Get the instant of the state.

get_position

Get the position of the state.

get_size

Get the size of the state.

get_velocity

Get the velocity of the state.

has_subset

Check if the state has a given subset.

in_frame

Check if the state is in a given reference frame.

is_defined

Check if the state is defined.

template

Emit a custom class type for States.

undefined

Get an undefined state.

__add__(
self: ostk.astrodynamics.trajectory.State,
arg0: ostk.astrodynamics.trajectory.State,
) → ostk.astrodynamics.trajectory.State
extract_coordinate(
self: ostk.astrodynamics.trajectory.State,
coordinate_subset: ostk::astrodynamics::trajectory::state::CoordinateSubset,
) → numpy.ndarray[numpy.float64[m, 1]]

Extract the coordinates associated to a subset of the state.

Parameters:

coordinate_subset (CoordinateSubset) -- The coordinate subset to extract.

Returns:

The coordinates associated to the subset.

Return type:

np.array

extract_coordinates(self: ostk.astrodynamics.trajectory.State, coordinate_subsets: List[ostk::astrodynamics::trajectory::state::CoordinateSubset]) → numpy.ndarray[numpy.float64[m, 1]]

Extract the coordinates associated to a set of subsets of the state.

Parameters:

coordinate_subsets (list[CoordinateSubset]) -- The coordinate subsets to extract.

Returns:

The coordinates associated to the subsets.

Return type:

np.array

get_angular_velocity(
self: ostk.astrodynamics.trajectory.State,
) → numpy.ndarray[numpy.float64[3, 1]]

Get the angular velocity of the state.

Returns:

The angular velocity of the state.

Return type:

np.array

get_attitude(
self: ostk.astrodynamics.trajectory.State,
) → ostk.mathematics.geometry.d3.transformation.rotation.Quaternion

Get the attitude of the state.

Returns:

The attitude of the state.

Return type:

Quaternion

get_coordinate_subsets(
self: ostk.astrodynamics.trajectory.State,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets associated to the state.

Returns:

The coordinate subsets associated to the state.

Return type:

list[CoordinateSubset]

get_coordinates(
self: ostk.astrodynamics.trajectory.State,
) → numpy.ndarray[numpy.float64[m, 1]]

Get the coordinates of the state.

Returns:

The coordinates of the state.

Return type:

np.array

get_frame(
self: ostk.astrodynamics.trajectory.State,
) → ostk.physics.coordinate.Frame

Get the reference frame of the state.

Returns:

The reference frame of the state.

Return type:

Frame

get_instant(
self: ostk.astrodynamics.trajectory.State,
) → ostk.physics.time.Instant

Get the instant of the state.

Returns:

The instant of the state.

Return type:

Instant

get_position(
self: ostk.astrodynamics.trajectory.State,
) → ostk.physics.coordinate.Position

Get the position of the state.

Returns:

The position of the state.

Return type:

Position

get_size(self: ostk.astrodynamics.trajectory.State) → int

Get the size of the state.

Returns:

The size of the state.

Return type:

int

get_velocity(
self: ostk.astrodynamics.trajectory.State,
) → ostk.physics.coordinate.Velocity

Get the velocity of the state.

Returns:

The velocity of the state.

Return type:

Velocity

has_subset(
self: ostk.astrodynamics.trajectory.State,
subset: ostk::astrodynamics::trajectory::state::CoordinateSubset,
) → bool

Check if the state has a given subset.

Parameters:

subset (CoordinateSubset) -- The subset to check.

Returns:

True if the state has the subset, False otherwise.

Return type:

bool

in_frame(
self: ostk.astrodynamics.trajectory.State,
frame: ostk.physics.coordinate.Frame,
) → ostk.astrodynamics.trajectory.State

Check if the state is in a given reference frame.

Parameters:

frame (Frame) -- The reference frame to check.

Returns:

True if the state is in the reference frame, False otherwise.

Return type:

bool

is_defined(self: ostk.astrodynamics.trajectory.State) → bool

Check if the state is defined.

Returns:

True if the state is defined, False otherwise.

Return type:

bool

static template(frame: Frame, coordinate_subsets: list) → type

Emit a custom class type for States. This is meta-programming syntactic sugar on top of the StateBuilder class.

StateType = State.template(frame, coordinate_subsets) state = StateType(instant, coordinates)

is equivalent to

state_builder = StateBuilder(frame, coordinate_subsets) state = state_builder.build(instant, coordinates)

static undefined() → ostk.astrodynamics.trajectory.State

Get an undefined state.

Returns:

An undefined state.

Return type:

State

\ No newline at end of file + ostk.astrodynamics.trajectory.State — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.State

class State(*args, **kwargs)

Bases: pybind11_object

This class represents the physical state of an object.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.State, instant: ostk.physics.time.Instant, position: ostk.physics.coordinate.Position, velocity: ostk.physics.coordinate.Velocity) -> None

    Utility constructor for Position/Velocity only.

    Args:

    instant (Instant): An instant position (Position): The cartesian position at the instant velocity (Velocity): The cartesian velocity at the instant

  2. __init__(self: ostk.astrodynamics.trajectory.State, instant: ostk.physics.time.Instant, position: ostk.physics.coordinate.Position, velocity: ostk.physics.coordinate.Velocity, attitude: ostk.mathematics.geometry.d3.transformation.rotation.Quaternion, angular_velocity: numpy.ndarray[numpy.float64[3, 1]], attitude_frame: ostk.physics.coordinate.Frame) -> None

    Utility constructor for Position/Velocity/Attitude/Angular velocity.

    Args:

    instant (Instant): An instant position (Position): The cartesian position at the instant velocity (Velocity): The cartesian velocity at the instant attitude (Quaternion): The attitude at the instant, representing the rotation required to go from the attitude reference frame to the satellite body frame angular_velocity (numpy.ndarray): The angular velocity at the instant, representing the angular velocity of the satellite body frame with respect ot teh attitude frame, expressed in body frame attitude_frame (Frame): The attitude reference frame

  3. __init__(self: ostk.astrodynamics.trajectory.State, instant: ostk.physics.time.Instant, coordinates: numpy.ndarray[numpy.float64[m, 1]], frame: ostk.physics.coordinate.Frame, coordinate_broker: ostk::astrodynamics::trajectory::state::CoordinateBroker) -> None

    Constructor with a pre-defined Coordinates Broker.

    Args:

    instant (Instant): An instant coordinates (numpy.ndarray): The coordinates at the instant in International System of Units frame (Frame): The reference frame in which the coordinates are referenced to and resolved in coordinate_broker (CoordinateBroker): The coordinate broker associated to the coordinates

  4. __init__(self: ostk.astrodynamics.trajectory.State, instant: ostk.physics.time.Instant, coordinates: numpy.ndarray[numpy.float64[m, 1]], frame: ostk.physics.coordinate.Frame, coordinate_subsets: List[ostk::astrodynamics::trajectory::state::CoordinateSubset]) -> None

    Constructor with coordinate subsets.

    Args:

    instant (Instant): An instant coordinates (numpy.ndarray): The coordinates at the instant in International System of Units frame (Frame): The reference frame in which the coordinates are referenced to and resolved in coordinate_subsets (CoordinateBroker): The coordinate subsets associated to the coordinates

  5. __init__(self: ostk.astrodynamics.trajectory.State, state: ostk.astrodynamics.trajectory.State) -> None

Methods

extract_coordinate

Extract the coordinates associated to a subset of the state.

extract_coordinates

Extract the coordinates associated to a set of subsets of the state.

get_angular_velocity

Get the angular velocity of the state.

get_attitude

Get the attitude of the state.

get_coordinate_subsets

Get the coordinate subsets associated to the state.

get_coordinates

Get the coordinates of the state.

get_frame

Get the reference frame of the state.

get_instant

Get the instant of the state.

get_position

Get the position of the state.

get_size

Get the size of the state.

get_velocity

Get the velocity of the state.

has_subset

Check if the state has a given subset.

in_frame

Check if the state is in a given reference frame.

is_defined

Check if the state is defined.

template

Emit a custom class type for States.

undefined

Get an undefined state.

__add__(
self: ostk.astrodynamics.trajectory.State,
arg0: ostk.astrodynamics.trajectory.State,
) → ostk.astrodynamics.trajectory.State
extract_coordinate(
self: ostk.astrodynamics.trajectory.State,
coordinate_subset: ostk::astrodynamics::trajectory::state::CoordinateSubset,
) → numpy.ndarray[numpy.float64[m, 1]]

Extract the coordinates associated to a subset of the state.

Parameters:

coordinate_subset (CoordinateSubset) -- The coordinate subset to extract.

Returns:

The coordinates associated to the subset.

Return type:

np.array

extract_coordinates(self: ostk.astrodynamics.trajectory.State, coordinate_subsets: List[ostk::astrodynamics::trajectory::state::CoordinateSubset]) → numpy.ndarray[numpy.float64[m, 1]]

Extract the coordinates associated to a set of subsets of the state.

Parameters:

coordinate_subsets (list[CoordinateSubset]) -- The coordinate subsets to extract.

Returns:

The coordinates associated to the subsets.

Return type:

np.array

get_angular_velocity(
self: ostk.astrodynamics.trajectory.State,
) → numpy.ndarray[numpy.float64[3, 1]]

Get the angular velocity of the state.

Returns:

The angular velocity of the state.

Return type:

np.array

get_attitude(
self: ostk.astrodynamics.trajectory.State,
) → ostk.mathematics.geometry.d3.transformation.rotation.Quaternion

Get the attitude of the state.

Returns:

The attitude of the state.

Return type:

Quaternion

get_coordinate_subsets(
self: ostk.astrodynamics.trajectory.State,
) → List[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the coordinate subsets associated to the state.

Returns:

The coordinate subsets associated to the state.

Return type:

list[CoordinateSubset]

get_coordinates(
self: ostk.astrodynamics.trajectory.State,
) → numpy.ndarray[numpy.float64[m, 1]]

Get the coordinates of the state.

Returns:

The coordinates of the state.

Return type:

np.array

get_frame(
self: ostk.astrodynamics.trajectory.State,
) → ostk.physics.coordinate.Frame

Get the reference frame of the state.

Returns:

The reference frame of the state.

Return type:

Frame

get_instant(
self: ostk.astrodynamics.trajectory.State,
) → ostk.physics.time.Instant

Get the instant of the state.

Returns:

The instant of the state.

Return type:

Instant

get_position(
self: ostk.astrodynamics.trajectory.State,
) → ostk.physics.coordinate.Position

Get the position of the state.

Returns:

The position of the state.

Return type:

Position

get_size(self: ostk.astrodynamics.trajectory.State) → int

Get the size of the state.

Returns:

The size of the state.

Return type:

int

get_velocity(
self: ostk.astrodynamics.trajectory.State,
) → ostk.physics.coordinate.Velocity

Get the velocity of the state.

Returns:

The velocity of the state.

Return type:

Velocity

has_subset(
self: ostk.astrodynamics.trajectory.State,
subset: ostk::astrodynamics::trajectory::state::CoordinateSubset,
) → bool

Check if the state has a given subset.

Parameters:

subset (CoordinateSubset) -- The subset to check.

Returns:

True if the state has the subset, False otherwise.

Return type:

bool

in_frame(
self: ostk.astrodynamics.trajectory.State,
frame: ostk.physics.coordinate.Frame,
) → ostk.astrodynamics.trajectory.State

Check if the state is in a given reference frame.

Parameters:

frame (Frame) -- The reference frame to check.

Returns:

True if the state is in the reference frame, False otherwise.

Return type:

bool

is_defined(self: ostk.astrodynamics.trajectory.State) → bool

Check if the state is defined.

Returns:

True if the state is defined, False otherwise.

Return type:

bool

static template(frame: Frame, coordinate_subsets: list) → type

Emit a custom class type for States. This is meta-programming syntactic sugar on top of the StateBuilder class.

StateType = State.template(frame, coordinate_subsets) state = StateType(instant, coordinates)

is equivalent to

state_builder = StateBuilder(frame, coordinate_subsets) state = state_builder.build(instant, coordinates)

static undefined() → ostk.astrodynamics.trajectory.State

Get an undefined state.

Returns:

An undefined state.

Return type:

State

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.StateBuilder.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.StateBuilder.html index 08ea96cb5..452c361be 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.StateBuilder.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.StateBuilder.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.StateBuilder — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.StateBuilder

class StateBuilder(*args, **kwargs)

Bases: pybind11_object

This class makes it convenient to build a State object.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.StateBuilder, frame: ostk.physics.coordinate.Frame, coordinate_subsets: List[ostk.astrodynamics.trajectory.state.CoordinateSubset]) -> None

    Construct a new StateBuilder object.

    Arguments:

    frame (Frame): The reference frame. coordinate_subsets list[CoordinateSubset]: The coordinate subsets.

    Returns:

    StateBuilder

  2. __init__(self: ostk.astrodynamics.trajectory.StateBuilder, frame: ostk.physics.coordinate.Frame, coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker) -> None

    Construct a new StateBuilder object.

    Arguments:

    frame (Frame): The reference frame. coordinate_broker (CoordinateBroker): The coordinate broker.

    Returns:

    StateBuilder: The new StateBuilder object.

  3. __init__(self: ostk.astrodynamics.trajectory.StateBuilder, state: ostk.astrodynamics.trajectory.State) -> None

    Construct a new StateBuilder object.

    Arguments:

    state (State): The state.

    Returns:

    StateBuilder: The new StateBuilder object.

Methods

access_coordinate_broker

Access the coordinate broker of the StateBuilder.

build

Build a State object from the StateBuilder.

expand

Expand a State object to the StateBuilder.

get_coordinate_subsets

Get the coordinate subsets of the StateBuilder.

get_frame

Get the reference frame of the StateBuilder.

is_defined

Check if the StateBuilder is defined.

reduce

Reduce a State object to the StateBuilder.

undefined

Get an undefined StateBuilder.

__add__(
self: ostk.astrodynamics.trajectory.StateBuilder,
arg0: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.astrodynamics.trajectory.StateBuilder

Add a coordinate subset to the StateBuilder.

Parameters:

coordinate_subsets (CoordinateSubset) -- The coordinate subset to add.

Returns:

The StateBuilder with the added coordinate subset.

Return type:

StateBuilder

access_coordinate_broker(
self: ostk.astrodynamics.trajectory.StateBuilder,
) → ostk.astrodynamics.trajectory.state.CoordinateBroker

Access the coordinate broker of the StateBuilder.

Returns:

The coordinate broker of the StateBuilder.

Return type:

CoordinateBroker

build(
self: ostk.astrodynamics.trajectory.StateBuilder,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
) → ostk.astrodynamics.trajectory.State

Build a State object from the StateBuilder.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (VectorXd) -- The coordinates of the state.

Returns:

The State object built from the StateBuilder.

Return type:

State

expand(
self: ostk.astrodynamics.trajectory.StateBuilder,
state: ostk.astrodynamics.trajectory.State,
default_state: ostk.astrodynamics.trajectory.State,
) → ostk.astrodynamics.trajectory.State

Expand a State object to the StateBuilder.

Parameters:

  • state (State) -- The State object to expand.

  • default_state (State) -- The default State object.

Returns:

The StateBuilder object expanded from the State.

Return type:

StateBuilder

get_coordinate_subsets(
self: ostk.astrodynamics.trajectory.StateBuilder,
) → List[ostk.astrodynamics.trajectory.state.CoordinateSubset]

Get the coordinate subsets of the StateBuilder.

Returns:

The coordinate subsets of the StateBuilder.

Return type:

Array<Shared<const CoordinateSubset>>

get_frame(
self: ostk.astrodynamics.trajectory.StateBuilder,
) → ostk.physics.coordinate.Frame

Get the reference frame of the StateBuilder.

Returns:

The reference frame of the StateBuilder.

Return type:

Frame

is_defined(self: ostk.astrodynamics.trajectory.StateBuilder) → bool

Check if the StateBuilder is defined.

Returns:

True if the StateBuilder is defined, False otherwise.

Return type:

bool

reduce(
self: ostk.astrodynamics.trajectory.StateBuilder,
state: ostk.astrodynamics.trajectory.State,
) → ostk.astrodynamics.trajectory.State

Reduce a State object to the StateBuilder.

Parameters:

state (State) -- The State object to reduce.

Returns:

The StateBuilder object reduced from the State.

Return type:

StateBuilder

static undefined() → ostk.astrodynamics.trajectory.StateBuilder

Get an undefined StateBuilder.

Returns:

The undefined StateBuilder.

Return type:

StateBuilder

\ No newline at end of file + ostk.astrodynamics.trajectory.StateBuilder — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.StateBuilder

class StateBuilder(*args, **kwargs)

Bases: pybind11_object

This class makes it convenient to build a State object.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.StateBuilder, frame: ostk.physics.coordinate.Frame, coordinate_subsets: List[ostk.astrodynamics.trajectory.state.CoordinateSubset]) -> None

    Construct a new StateBuilder object.

    Arguments:

    frame (Frame): The reference frame. coordinate_subsets list[CoordinateSubset]: The coordinate subsets.

    Returns:

    StateBuilder

  2. __init__(self: ostk.astrodynamics.trajectory.StateBuilder, frame: ostk.physics.coordinate.Frame, coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker) -> None

    Construct a new StateBuilder object.

    Arguments:

    frame (Frame): The reference frame. coordinate_broker (CoordinateBroker): The coordinate broker.

    Returns:

    StateBuilder: The new StateBuilder object.

  3. __init__(self: ostk.astrodynamics.trajectory.StateBuilder, state: ostk.astrodynamics.trajectory.State) -> None

    Construct a new StateBuilder object.

    Arguments:

    state (State): The state.

    Returns:

    StateBuilder: The new StateBuilder object.

Methods

access_coordinate_broker

Access the coordinate broker of the StateBuilder.

build

Build a State object from the StateBuilder.

expand

Expand a State object to the StateBuilder.

get_coordinate_subsets

Get the coordinate subsets of the StateBuilder.

get_frame

Get the reference frame of the StateBuilder.

is_defined

Check if the StateBuilder is defined.

reduce

Reduce a State object to the StateBuilder.

undefined

Get an undefined StateBuilder.

__add__(
self: ostk.astrodynamics.trajectory.StateBuilder,
arg0: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.astrodynamics.trajectory.StateBuilder

Add a coordinate subset to the StateBuilder.

Parameters:

coordinate_subsets (CoordinateSubset) -- The coordinate subset to add.

Returns:

The StateBuilder with the added coordinate subset.

Return type:

StateBuilder

access_coordinate_broker(
self: ostk.astrodynamics.trajectory.StateBuilder,
) → ostk.astrodynamics.trajectory.state.CoordinateBroker

Access the coordinate broker of the StateBuilder.

Returns:

The coordinate broker of the StateBuilder.

Return type:

CoordinateBroker

build(
self: ostk.astrodynamics.trajectory.StateBuilder,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
) → ostk.astrodynamics.trajectory.State

Build a State object from the StateBuilder.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (VectorXd) -- The coordinates of the state.

Returns:

The State object built from the StateBuilder.

Return type:

State

expand(
self: ostk.astrodynamics.trajectory.StateBuilder,
state: ostk.astrodynamics.trajectory.State,
default_state: ostk.astrodynamics.trajectory.State,
) → ostk.astrodynamics.trajectory.State

Expand a State object to the StateBuilder.

Parameters:

  • state (State) -- The State object to expand.

  • default_state (State) -- The default State object.

Returns:

The StateBuilder object expanded from the State.

Return type:

StateBuilder

get_coordinate_subsets(
self: ostk.astrodynamics.trajectory.StateBuilder,
) → List[ostk.astrodynamics.trajectory.state.CoordinateSubset]

Get the coordinate subsets of the StateBuilder.

Returns:

The coordinate subsets of the StateBuilder.

Return type:

Array<Shared<const CoordinateSubset>>

get_frame(
self: ostk.astrodynamics.trajectory.StateBuilder,
) → ostk.physics.coordinate.Frame

Get the reference frame of the StateBuilder.

Returns:

The reference frame of the StateBuilder.

Return type:

Frame

is_defined(self: ostk.astrodynamics.trajectory.StateBuilder) → bool

Check if the StateBuilder is defined.

Returns:

True if the StateBuilder is defined, False otherwise.

Return type:

bool

reduce(
self: ostk.astrodynamics.trajectory.StateBuilder,
state: ostk.astrodynamics.trajectory.State,
) → ostk.astrodynamics.trajectory.State

Reduce a State object to the StateBuilder.

Parameters:

state (State) -- The State object to reduce.

Returns:

The StateBuilder object reduced from the State.

Return type:

StateBuilder

static undefined() → ostk.astrodynamics.trajectory.StateBuilder

Get an undefined StateBuilder.

Returns:

The undefined StateBuilder.

Return type:

StateBuilder

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.OrbitModel.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.OrbitModel.html index 372fe2407..55448d032 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.OrbitModel.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.OrbitModel.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.orbit.OrbitModel — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.OrbitModel

class OrbitModel

Bases: pybind11_object

Base class for orbit models.

Provides the interface for orbit models.

Methods

as_kepler

Cast the orbit model to a Kepler model.

as_propagated

Cast the orbit model to a propagated model.

as_sgp4

Cast the orbit model to an SGP4 model.

calculate_revolution_number_at

Calculate the revolution number of the orbit model at a given instant.

calculate_state_at

Calculate the state of the orbit model at a given instant.

get_epoch

Get the epoch of the orbit model.

get_revolution_number_at_epoch

Get the revolution number at the epoch of the orbit model.

is_defined

Check if the orbit model is defined.

is_kepler

Check if the orbit model is a Kepler model.

is_propagated

Check if the orbit model is a propagated model.

is_sgp4

Check if the orbit model is an SGP4 model.

as_kepler(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Kepler

Cast the orbit model to a Kepler model.

Returns:

The Kepler model.

Return type:

Kepler

as_propagated(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Propagated

Cast the orbit model to a propagated model.

Returns:

The propagated model.

Return type:

Propagated

as_sgp4(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::SGP4

Cast the orbit model to an SGP4 model.

Returns:

The SGP4 model.

Return type:

SGP4

calculate_revolution_number_at(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
instant: ostk.physics.time.Instant,
) → ostk.core.type.Integer

Calculate the revolution number of the orbit model at a given instant.

Parameters:

instant (Instant) -- The instant at which to calculate the revolution number.

Returns:

The revolution number of the orbit model at the given instant.

Return type:

int

calculate_state_at(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
instant: ostk.physics.time.Instant,
) → ostk.astrodynamics.trajectory.State

Calculate the state of the orbit model at a given instant.

Parameters:

instant (Instant) -- The instant at which to calculate the state.

Returns:

The state of the orbit model at the given instant.

Return type:

State

get_epoch(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk.physics.time.Instant

Get the epoch of the orbit model.

Returns:

The epoch of the orbit model.

Return type:

Instant

get_revolution_number_at_epoch(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk.core.type.Integer

Get the revolution number at the epoch of the orbit model.

Returns:

The revolution number at the epoch of the orbit model.

Return type:

int

is_defined(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is defined.

Returns:

True if the orbit model is defined, False otherwise.

Return type:

bool

is_kepler(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a Kepler model.

Returns:

True if the orbit model is a Kepler model, False otherwise.

Return type:

bool

is_propagated(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a propagated model.

Returns:

True if the orbit model is a propagated model, False otherwise.

Return type:

bool

is_sgp4(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is an SGP4 model.

Returns:

True if the orbit model is an SGP4 model, False otherwise.

Return type:

bool

\ No newline at end of file + ostk.astrodynamics.trajectory.orbit.OrbitModel — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.OrbitModel

class OrbitModel

Bases: pybind11_object

Base class for orbit models.

Provides the interface for orbit models.

Methods

as_kepler

Cast the orbit model to a Kepler model.

as_propagated

Cast the orbit model to a propagated model.

as_sgp4

Cast the orbit model to an SGP4 model.

calculate_revolution_number_at

Calculate the revolution number of the orbit model at a given instant.

calculate_state_at

Calculate the state of the orbit model at a given instant.

get_epoch

Get the epoch of the orbit model.

get_revolution_number_at_epoch

Get the revolution number at the epoch of the orbit model.

is_defined

Check if the orbit model is defined.

is_kepler

Check if the orbit model is a Kepler model.

is_propagated

Check if the orbit model is a propagated model.

is_sgp4

Check if the orbit model is an SGP4 model.

as_kepler(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Kepler

Cast the orbit model to a Kepler model.

Returns:

The Kepler model.

Return type:

Kepler

as_propagated(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Propagated

Cast the orbit model to a propagated model.

Returns:

The propagated model.

Return type:

Propagated

as_sgp4(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::SGP4

Cast the orbit model to an SGP4 model.

Returns:

The SGP4 model.

Return type:

SGP4

calculate_revolution_number_at(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
instant: ostk.physics.time.Instant,
) → ostk.core.type.Integer

Calculate the revolution number of the orbit model at a given instant.

Parameters:

instant (Instant) -- The instant at which to calculate the revolution number.

Returns:

The revolution number of the orbit model at the given instant.

Return type:

int

calculate_state_at(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
instant: ostk.physics.time.Instant,
) → ostk.astrodynamics.trajectory.State

Calculate the state of the orbit model at a given instant.

Parameters:

instant (Instant) -- The instant at which to calculate the state.

Returns:

The state of the orbit model at the given instant.

Return type:

State

get_epoch(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk.physics.time.Instant

Get the epoch of the orbit model.

Returns:

The epoch of the orbit model.

Return type:

Instant

get_revolution_number_at_epoch(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk.core.type.Integer

Get the revolution number at the epoch of the orbit model.

Returns:

The revolution number at the epoch of the orbit model.

Return type:

int

is_defined(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is defined.

Returns:

True if the orbit model is defined, False otherwise.

Return type:

bool

is_kepler(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a Kepler model.

Returns:

True if the orbit model is a Kepler model, False otherwise.

Return type:

bool

is_propagated(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a propagated model.

Returns:

True if the orbit model is a propagated model, False otherwise.

Return type:

bool

is_sgp4(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is an SGP4 model.

Returns:

True if the orbit model is an SGP4 model, False otherwise.

Return type:

bool

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.Pass.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.Pass.html index 6f53cbaa1..a531ddfc2 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.Pass.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.Pass.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.orbit.Pass — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.Pass

class Pass(
self: ostk.astrodynamics.trajectory.orbit.Pass,
revolution_number: ostk.core.type.Integer,
instant_at_ascending_node: ostk.physics.time.Instant,
instant_at_north_point: ostk.physics.time.Instant,
instant_at_descending_node: ostk.physics.time.Instant,
instant_at_south_point: ostk.physics.time.Instant,
instant_at_pass_break: ostk.physics.time.Instant,
)

Bases: pybind11_object

A revolution of an orbiting object.

Constructor.

Parameters:

  • revolution_number (int) -- The revolution number of the pass.

  • instant_at_ascending_node (Instant) -- The instant at the ascending node of the pass.

  • instant_at_north_point (Instant) -- The instant at the north point of the pass.

  • instant_at_descending_node (Instant) -- The instant at the descending node of the pass.

  • instant_at_south_point (Instant) -- The instant at the south point of the pass.

  • instant_at_pass_break (Instant) -- The instant at break of the pass.

Methods

get_duration

Get the duration of the pass.

get_instant_at_ascending_node

Get the instant at the ascending node of the pass.

get_instant_at_descending_node

Get the instant at the descending node of the pass.

get_instant_at_north_point

Get the instant at the north point of the pass.

get_instant_at_pass_break

Get the instant at the break of the pass, i.e. the ascending node of the next pass.

get_instant_at_south_point

Get the instant at the south point of the pass.

get_revolution_number

Get the revolution number of the pass.

get_type

Get the type of the pass.

is_complete

Check if the pass is complete.

is_defined

Check if the pass is defined.

string_from_phase

Get the string representation of a pass phase.

string_from_type

Get the string representation of a pass type.

undefined

Get an undefined pass.

class Phase(self: ostk.astrodynamics.trajectory.orbit.Pass.Phase, value: int)

Bases: pybind11_object

The phase of the Pass.

Members:

Undefined : Undefined

Ascending : Ascending

Descending : Descending

property name
class Type(self: ostk.astrodynamics.trajectory.orbit.Pass.Type, value: int)

Bases: pybind11_object

The type of Pass.

Members:

Undefined : Undefined

Complete : Complete

Partial : Partial

property name
get_duration(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.physics.time.Duration

Get the duration of the pass. Undefined if the pass is not complete.

Returns:

The duration of the pass.

Return type:

Duration

get_instant_at_ascending_node(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.physics.time.Instant

Get the instant at the ascending node of the pass. i.e. z = 0 & vz > 0 in an ECI frame.

Returns:

The instant at the ascending node of the pass.

Return type:

Instant

get_instant_at_descending_node(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.physics.time.Instant

Get the instant at the descending node of the pass. i.e. z = 0 and vz < 0 in an ECI frame.

Returns:

The instant at the descending node of the pass.

Return type:

Instant

get_instant_at_north_point(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.physics.time.Instant

Get the instant at the north point of the pass. i.e. z = maximum and vz = 0 in an ECI frame.

Returns:

The instant at the north point of the pass.

Return type:

Instant

get_instant_at_pass_break(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.physics.time.Instant

Get the instant at the break of the pass, i.e. the ascending node of the next pass.

Returns:

The instant at the break of the pass.

Return type:

Instant

get_instant_at_south_point(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.physics.time.Instant

Get the instant at the south point of the pass. i.e. z = minimum and vz = 0 in an ECI frame.

Returns:

The instant at the south point of the pass.

Return type:

Instant

get_revolution_number(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.core.type.Integer

Get the revolution number of the pass.

Returns:

The revolution number of the pass.

Return type:

int

get_type(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.astrodynamics.trajectory.orbit.Pass.Type

Get the type of the pass.

Returns:

The type of the pass.

Return type:

Pass.Type

is_complete(self: ostk.astrodynamics.trajectory.orbit.Pass) → bool

Check if the pass is complete.

Returns:

True if the pass is complete, False otherwise.

Return type:

bool

is_defined(self: ostk.astrodynamics.trajectory.orbit.Pass) → bool

Check if the pass is defined.

Returns:

True if the pass is defined, False otherwise.

Return type:

bool

static string_from_phase(
phase: ostk.astrodynamics.trajectory.orbit.Pass.Phase,
) → ostk.core.type.String

Get the string representation of a pass phase.

Parameters:

phase (Pass.Phase) -- The pass phase.

Returns:

The string representation of the pass phase.

Return type:

str

static string_from_type(
type: ostk.astrodynamics.trajectory.orbit.Pass.Type,
) → ostk.core.type.String

Get the string representation of a pass type.

Parameters:

type (Pass.Type) -- The pass type.

Returns:

The string representation of the pass type.

Return type:

str

static undefined() → ostk.astrodynamics.trajectory.orbit.Pass

Get an undefined pass.

Returns:

The undefined pass.

Return type:

Pass

\ No newline at end of file + ostk.astrodynamics.trajectory.orbit.Pass — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.Pass

class Pass(
self: ostk.astrodynamics.trajectory.orbit.Pass,
revolution_number: ostk.core.type.Integer,
instant_at_ascending_node: ostk.physics.time.Instant,
instant_at_north_point: ostk.physics.time.Instant,
instant_at_descending_node: ostk.physics.time.Instant,
instant_at_south_point: ostk.physics.time.Instant,
instant_at_pass_break: ostk.physics.time.Instant,
)

Bases: pybind11_object

A revolution of an orbiting object.

Constructor.

Parameters:

  • revolution_number (int) -- The revolution number of the pass.

  • instant_at_ascending_node (Instant) -- The instant at the ascending node of the pass.

  • instant_at_north_point (Instant) -- The instant at the north point of the pass.

  • instant_at_descending_node (Instant) -- The instant at the descending node of the pass.

  • instant_at_south_point (Instant) -- The instant at the south point of the pass.

  • instant_at_pass_break (Instant) -- The instant at break of the pass.

Methods

get_duration

Get the duration of the pass.

get_instant_at_ascending_node

Get the instant at the ascending node of the pass.

get_instant_at_descending_node

Get the instant at the descending node of the pass.

get_instant_at_north_point

Get the instant at the north point of the pass.

get_instant_at_pass_break

Get the instant at the break of the pass, i.e. the ascending node of the next pass.

get_instant_at_south_point

Get the instant at the south point of the pass.

get_revolution_number

Get the revolution number of the pass.

get_type

Get the type of the pass.

is_complete

Check if the pass is complete.

is_defined

Check if the pass is defined.

string_from_phase

Get the string representation of a pass phase.

string_from_type

Get the string representation of a pass type.

undefined

Get an undefined pass.

class Phase(self: ostk.astrodynamics.trajectory.orbit.Pass.Phase, value: int)

Bases: pybind11_object

The phase of the Pass.

Members:

Undefined : Undefined

Ascending : Ascending

Descending : Descending

property name
class Type(self: ostk.astrodynamics.trajectory.orbit.Pass.Type, value: int)

Bases: pybind11_object

The type of Pass.

Members:

Undefined : Undefined

Complete : Complete

Partial : Partial

property name
get_duration(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.physics.time.Duration

Get the duration of the pass. Undefined if the pass is not complete.

Returns:

The duration of the pass.

Return type:

Duration

get_instant_at_ascending_node(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.physics.time.Instant

Get the instant at the ascending node of the pass. i.e. z = 0 & vz > 0 in an ECI frame.

Returns:

The instant at the ascending node of the pass.

Return type:

Instant

get_instant_at_descending_node(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.physics.time.Instant

Get the instant at the descending node of the pass. i.e. z = 0 and vz < 0 in an ECI frame.

Returns:

The instant at the descending node of the pass.

Return type:

Instant

get_instant_at_north_point(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.physics.time.Instant

Get the instant at the north point of the pass. i.e. z = maximum and vz = 0 in an ECI frame.

Returns:

The instant at the north point of the pass.

Return type:

Instant

get_instant_at_pass_break(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.physics.time.Instant

Get the instant at the break of the pass, i.e. the ascending node of the next pass.

Returns:

The instant at the break of the pass.

Return type:

Instant

get_instant_at_south_point(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.physics.time.Instant

Get the instant at the south point of the pass. i.e. z = minimum and vz = 0 in an ECI frame.

Returns:

The instant at the south point of the pass.

Return type:

Instant

get_revolution_number(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.core.type.Integer

Get the revolution number of the pass.

Returns:

The revolution number of the pass.

Return type:

int

get_type(
self: ostk.astrodynamics.trajectory.orbit.Pass,
) → ostk.astrodynamics.trajectory.orbit.Pass.Type

Get the type of the pass.

Returns:

The type of the pass.

Return type:

Pass.Type

is_complete(self: ostk.astrodynamics.trajectory.orbit.Pass) → bool

Check if the pass is complete.

Returns:

True if the pass is complete, False otherwise.

Return type:

bool

is_defined(self: ostk.astrodynamics.trajectory.orbit.Pass) → bool

Check if the pass is defined.

Returns:

True if the pass is defined, False otherwise.

Return type:

bool

static string_from_phase(
phase: ostk.astrodynamics.trajectory.orbit.Pass.Phase,
) → ostk.core.type.String

Get the string representation of a pass phase.

Parameters:

phase (Pass.Phase) -- The pass phase.

Returns:

The string representation of the pass phase.

Return type:

str

static string_from_type(
type: ostk.astrodynamics.trajectory.orbit.Pass.Type,
) → ostk.core.type.String

Get the string representation of a pass type.

Parameters:

type (Pass.Type) -- The pass type.

Returns:

The string representation of the pass type.

Return type:

str

static undefined() → ostk.astrodynamics.trajectory.orbit.Pass

Get an undefined pass.

Returns:

The undefined pass.

Return type:

Pass

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.html index 78736c657..477d75c29 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.orbit.message.spacex.OPM — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.message.spacex.OPM

class OPM(self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM, header: ostk::astrodynamics::trajectory::orbit::message::spacex::OPM::Header, deployments: List[ostk::astrodynamics::trajectory::orbit::message::spacex::OPM::Deployment])

Bases: pybind11_object

The SpaceX OPM message.

See also

SpaceX OPM.

Constructor.

Parameters:

  • header (Header) -- The header of the OPM message.

  • deployments (list[Deployment]) -- The deployments of the OPM message.

Methods

dictionary

Build an OPM message from a dictionary.

get_deployment_at

Get the deployment at a given index.

get_deployment_with_name

Get the deployment with a given name.

get_deployments

Get the deployments of the OPM message.

get_header

Get the header of the OPM message.

is_defined

Check if the OPM message is defined.

load

Load an OPM message from a file.

parse

Parse an OPM message from a string.

undefined

Return an undefined OPM message.

class Deployment(
self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.Deployment,
name: ostk.core.type.String,
sequence_number: ostk.core.type.Integer,
mission_time: ostk.physics.time.Duration,
date: ostk.physics.time.Instant,
position: ostk.physics.coordinate.Position,
velocity: ostk.physics.coordinate.Velocity,
mean_perigee_altitude: ostk.physics.unit.Length,
mean_apogee_altitude: ostk.physics.unit.Length,
mean_inclination: ostk.physics.unit.Angle,
mean_argument_of_perigee: ostk.physics.unit.Angle,
mean_longitude_ascending_node: ostk.physics.unit.Angle,
mean_mean_anomaly: ostk.physics.unit.Angle,
ballistic_coefficient: ostk.core.type.Real,
)

Bases: pybind11_object

The deployment of the SpaceX OPM message.

Constructor.

Parameters:

  • name (str) -- The name of the deployment.

  • sequence_number (int) -- The sequence number of the deployment.

  • mission_time (Duration) -- The mission time of the deployment.

  • date (Instant) -- The date of the deployment.

  • position (Position) -- The position of the deployment.

  • velocity (Velocity) -- The velocity of the deployment.

  • mean_perigee_altitude (Length) -- The mean perigee altitude of the deployment.

  • mean_apogee_altitude (Length) -- The mean apogee altitude of the deployment.

  • mean_inclination (Angle) -- The mean inclination of the deployment.

  • mean_argument_of_perigee (Angle) -- The mean argument of perigee of the deployment.

  • mean_longitude_ascending_node (Angle) -- The mean longitude of the ascending node of the deployment.

  • mean_mean_anomaly (Angle) -- The mean mean anomaly of the deployment.

  • ballistic_coefficient (float) -- The ballistic coefficient of the deployment.

property ballistic_coefficient

Get the ballistic coefficient of the deployment.

Type:

float

property date

Get the date of the deployment.

Type:

Instant

property mean_apogee_altitude

Get the mean apogee altitude of the deployment.

Type:

Length

property mean_argument_of_perigee

Get the mean argument of perigee of the deployment.

Type:

Angle

property mean_inclination

Get the mean inclination of the deployment.

Type:

Angle

property mean_longitude_ascending_node

Get the mean longitude of the ascending node of the deployment.

Type:

Angle

property mean_mean_anomaly

Get the mean mean anomaly of the deployment.

Type:

Angle

property mean_perigee_altitude

Get the mean perigee altitude of the deployment.

Type:

Length

property mission_time

Get the mission time of the deployment.

Type:

Duration

property name

Get the name of the deployment.

Type:

str

property position

Get the position of the deployment.

Type:

Position

property sequence_number

Get the sequence number of the deployment.

Type:

int

to_state(
self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.Deployment,
) → ostk.astrodynamics.trajectory.State

Convert the deployment to a state.

Returns:

The state of the deployment.

Return type:

state (State)

property velocity

Get the velocity of the deployment.

Type:

Velocity

class Header(
self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.Header,
generation_date: ostk.physics.time.Instant,
launch_date: ostk.physics.time.Instant,
)

Bases: pybind11_object

The header of the SpaceX OPM message.

Constructor.

Parameters:

  • generation_date (Instant) -- The date at which the OPM message was generated.

  • launch_date (Instant) -- The date at which the spacecraft was launched.

property generation_date

Get the date at which the OPM message was generated.

Returns:

The date at which the OPM message was generated.

Return type:

instant (Instant)

property launch_date

Get the date at which the spacecraft was launched.

Returns:

The date at which the spacecraft was launched.

Return type:

instant (Instant)

static dictionary(
dictionary: ostk.core.container.Dictionary,
) → ostk.astrodynamics.trajectory.orbit.message.spacex.OPM

Build an OPM message from a dictionary.

Parameters:

dictionary (dict) -- The dictionary containing the OPM message information.

Returns:

The OPM message.

Return type:

opm (OPM)

get_deployment_at(
self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM,
index: int,
) → ostk::astrodynamics::trajectory::orbit::message::spacex::OPM::Deployment

Get the deployment at a given index.

Parameters:

index (int) -- The index of the deployment.

Returns:

The deployment at the given index.

Return type:

deployment (Deployment)

get_deployment_with_name(
self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM,
name: ostk.core.type.String,
) → ostk::astrodynamics::trajectory::orbit::message::spacex::OPM::Deployment

Get the deployment with a given name.

Parameters:

name (str) -- The name of the deployment.

Returns:

The deployment with the given name.

Return type:

deployment (Deployment)

get_deployments(
self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM,
) → List[ostk::astrodynamics::trajectory::orbit::message::spacex::OPM::Deployment]

Get the deployments of the OPM message.

Returns:

The deployments of the OPM message.

Return type:

deployments (list[Deployment])

get_header(
self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM,
) → ostk::astrodynamics::trajectory::orbit::message::spacex::OPM::Header

Get the header of the OPM message.

Returns:

The header of the OPM message.

Return type:

header (Header)

is_defined(self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM) → bool

Check if the OPM message is defined.

Returns:

True if the OPM message is defined, False otherwise.

Return type:

is_defined (bool)

static load(
file: ostk.core.filesystem.File,
) → ostk.astrodynamics.trajectory.orbit.message.spacex.OPM

Load an OPM message from a file.

Parameters:

file (str) -- The path to the file containing the OPM message.

Returns:

The OPM message.

Return type:

opm (OPM)

static parse(
string: ostk.core.type.String,
) → ostk.astrodynamics.trajectory.orbit.message.spacex.OPM

Parse an OPM message from a string.

Parameters:

string (str) -- The string containing the OPM message.

Returns:

The OPM message.

Return type:

opm (OPM)

static undefined() → ostk.astrodynamics.trajectory.orbit.message.spacex.OPM

Return an undefined OPM message.

Returns:

An undefined OPM message.

Return type:

opm (OPM)

\ No newline at end of file + ostk.astrodynamics.trajectory.orbit.message.spacex.OPM — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.message.spacex.OPM

class OPM(self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM, header: ostk::astrodynamics::trajectory::orbit::message::spacex::OPM::Header, deployments: List[ostk::astrodynamics::trajectory::orbit::message::spacex::OPM::Deployment])

Bases: pybind11_object

The SpaceX OPM message.

See also

SpaceX OPM.

Constructor.

Parameters:

  • header (Header) -- The header of the OPM message.

  • deployments (list[Deployment]) -- The deployments of the OPM message.

Methods

dictionary

Build an OPM message from a dictionary.

get_deployment_at

Get the deployment at a given index.

get_deployment_with_name

Get the deployment with a given name.

get_deployments

Get the deployments of the OPM message.

get_header

Get the header of the OPM message.

is_defined

Check if the OPM message is defined.

load

Load an OPM message from a file.

parse

Parse an OPM message from a string.

undefined

Return an undefined OPM message.

class Deployment(
self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.Deployment,
name: ostk.core.type.String,
sequence_number: ostk.core.type.Integer,
mission_time: ostk.physics.time.Duration,
date: ostk.physics.time.Instant,
position: ostk.physics.coordinate.Position,
velocity: ostk.physics.coordinate.Velocity,
mean_perigee_altitude: ostk.physics.unit.Length,
mean_apogee_altitude: ostk.physics.unit.Length,
mean_inclination: ostk.physics.unit.Angle,
mean_argument_of_perigee: ostk.physics.unit.Angle,
mean_longitude_ascending_node: ostk.physics.unit.Angle,
mean_mean_anomaly: ostk.physics.unit.Angle,
ballistic_coefficient: ostk.core.type.Real,
)

Bases: pybind11_object

The deployment of the SpaceX OPM message.

Constructor.

Parameters:

  • name (str) -- The name of the deployment.

  • sequence_number (int) -- The sequence number of the deployment.

  • mission_time (Duration) -- The mission time of the deployment.

  • date (Instant) -- The date of the deployment.

  • position (Position) -- The position of the deployment.

  • velocity (Velocity) -- The velocity of the deployment.

  • mean_perigee_altitude (Length) -- The mean perigee altitude of the deployment.

  • mean_apogee_altitude (Length) -- The mean apogee altitude of the deployment.

  • mean_inclination (Angle) -- The mean inclination of the deployment.

  • mean_argument_of_perigee (Angle) -- The mean argument of perigee of the deployment.

  • mean_longitude_ascending_node (Angle) -- The mean longitude of the ascending node of the deployment.

  • mean_mean_anomaly (Angle) -- The mean mean anomaly of the deployment.

  • ballistic_coefficient (float) -- The ballistic coefficient of the deployment.

property ballistic_coefficient

Get the ballistic coefficient of the deployment.

Type:

float

property date

Get the date of the deployment.

Type:

Instant

property mean_apogee_altitude

Get the mean apogee altitude of the deployment.

Type:

Length

property mean_argument_of_perigee

Get the mean argument of perigee of the deployment.

Type:

Angle

property mean_inclination

Get the mean inclination of the deployment.

Type:

Angle

property mean_longitude_ascending_node

Get the mean longitude of the ascending node of the deployment.

Type:

Angle

property mean_mean_anomaly

Get the mean mean anomaly of the deployment.

Type:

Angle

property mean_perigee_altitude

Get the mean perigee altitude of the deployment.

Type:

Length

property mission_time

Get the mission time of the deployment.

Type:

Duration

property name

Get the name of the deployment.

Type:

str

property position

Get the position of the deployment.

Type:

Position

property sequence_number

Get the sequence number of the deployment.

Type:

int

to_state(
self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.Deployment,
) → ostk.astrodynamics.trajectory.State

Convert the deployment to a state.

Returns:

The state of the deployment.

Return type:

state (State)

property velocity

Get the velocity of the deployment.

Type:

Velocity

class Header(
self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.Header,
generation_date: ostk.physics.time.Instant,
launch_date: ostk.physics.time.Instant,
)

Bases: pybind11_object

The header of the SpaceX OPM message.

Constructor.

Parameters:

  • generation_date (Instant) -- The date at which the OPM message was generated.

  • launch_date (Instant) -- The date at which the spacecraft was launched.

property generation_date

Get the date at which the OPM message was generated.

Returns:

The date at which the OPM message was generated.

Return type:

instant (Instant)

property launch_date

Get the date at which the spacecraft was launched.

Returns:

The date at which the spacecraft was launched.

Return type:

instant (Instant)

static dictionary(
dictionary: ostk.core.container.Dictionary,
) → ostk.astrodynamics.trajectory.orbit.message.spacex.OPM

Build an OPM message from a dictionary.

Parameters:

dictionary (dict) -- The dictionary containing the OPM message information.

Returns:

The OPM message.

Return type:

opm (OPM)

get_deployment_at(
self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM,
index: int,
) → ostk::astrodynamics::trajectory::orbit::message::spacex::OPM::Deployment

Get the deployment at a given index.

Parameters:

index (int) -- The index of the deployment.

Returns:

The deployment at the given index.

Return type:

deployment (Deployment)

get_deployment_with_name(
self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM,
name: ostk.core.type.String,
) → ostk::astrodynamics::trajectory::orbit::message::spacex::OPM::Deployment

Get the deployment with a given name.

Parameters:

name (str) -- The name of the deployment.

Returns:

The deployment with the given name.

Return type:

deployment (Deployment)

get_deployments(
self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM,
) → List[ostk::astrodynamics::trajectory::orbit::message::spacex::OPM::Deployment]

Get the deployments of the OPM message.

Returns:

The deployments of the OPM message.

Return type:

deployments (list[Deployment])

get_header(
self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM,
) → ostk::astrodynamics::trajectory::orbit::message::spacex::OPM::Header

Get the header of the OPM message.

Returns:

The header of the OPM message.

Return type:

header (Header)

is_defined(self: ostk.astrodynamics.trajectory.orbit.message.spacex.OPM) → bool

Check if the OPM message is defined.

Returns:

True if the OPM message is defined, False otherwise.

Return type:

is_defined (bool)

static load(
file: ostk.core.filesystem.File,
) → ostk.astrodynamics.trajectory.orbit.message.spacex.OPM

Load an OPM message from a file.

Parameters:

file (str) -- The path to the file containing the OPM message.

Returns:

The OPM message.

Return type:

opm (OPM)

static parse(
string: ostk.core.type.String,
) → ostk.astrodynamics.trajectory.orbit.message.spacex.OPM

Parse an OPM message from a string.

Parameters:

string (str) -- The string containing the OPM message.

Returns:

The OPM message.

Return type:

opm (OPM)

static undefined() → ostk.astrodynamics.trajectory.orbit.message.spacex.OPM

Return an undefined OPM message.

Returns:

An undefined OPM message.

Return type:

opm (OPM)

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.html index a64dca852..e2afcc076 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean

class BrouwerLyddaneMean(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
semi_major_axis: ostk.physics.unit.Length,
eccentricity: ostk.core.type.Real,
inclination: ostk.physics.unit.Angle,
raan: ostk.physics.unit.Angle,
aop: ostk.physics.unit.Angle,
mean_anomaly: ostk.physics.unit.Angle,
)

Bases: COE

Brouwer-Lyddane mean orbit elements. This is a parent class, please use the Short or Long child classes as appropriate.

Constructor.

Parameters:

  • semi_major_axis (Length) -- The semi-major axis.

  • eccentricity (float) -- The eccentricity.

  • inclination (Angle) -- The inclination.

  • raan (Angle) -- The right ascension of the ascending node.

  • aop (Angle) -- The argument of periapsis.

  • mean_anomaly (Angle) -- The mean anomaly.

Methods

cartesian

Create a COE model from Cartesian state.

compute_angular_momentum

Overloaded function.

compute_radial_distance

Compute the radial distance from the semi-latus rectum and the eccentricity.

compute_semi_latus_rectum

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

eccentric_anomaly_from_mean_anomaly

Compute the eccentric anomaly from the mean anomaly.

eccentric_anomaly_from_true_anomaly

Compute the eccentric anomaly from the true anomaly.

from_SI_vector

Create a COE model from a state vector in SI units.

get_SI_vector

Get the state vector of the COE in the specified anomaly type.

get_angular_momentum

Get the angular momentum of the COE.

get_aop

Get the argument of periapsis of the COE.

get_apoapsis_radius

Get the apoapsis radius of the COE.

get_cartesian_state

Get the Cartesian state of the BrouwerLyddaneMean model.

get_eccentric_anomaly

Get the eccentric anomaly of the BrouwerLyddaneMean model.

get_eccentricity

Get the eccentricity of the COE.

get_inclination

Get the inclination of the COE.

get_mean_anomaly

Get the mean anomaly of the BrouwerLyddaneMean model.

get_mean_motion

Get the mean motion of the COE.

get_nodal_precession_rate

Get the nodal precession of the COE.

get_orbital_period

Get the orbital period of the COE.

get_periapsis_radius

Get the periapsis radius of the COE.

get_raan

Get the right ascension of the ascending node of the COE.

get_radial_distance

Get the radial distance of the COE.

get_semi_latus_rectum

Get the semi-latus rectum of the COE.

get_semi_major_axis

Get the semi-major axis of the COE.

get_true_anomaly

Get the true anomaly of the BrouwerLyddaneMean model.

is_defined

Check if the COE is defined.

mean_anomaly_from_eccentric_anomaly

Compute the mean anomaly from the eccentric anomaly.

string_from_element

Get the string representation of an element.

to_coe

Convert the BrouwerLyddaneMean model to classical orbital elements.

true_anomaly_from_eccentric_anomaly

Compute the true anomaly from the eccentric anomaly.

true_anomaly_from_mean_anomaly

Compute the true anomaly from the mean anomaly.

undefined

Create an undefined COE model.

class AnomalyType(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
value: int,
)

Bases: pybind11_object

The type of Anomaly.

Members:

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
class Element(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
value: int,
)

Bases: pybind11_object

Classical Orbital Element enumeration.

Members:

SemiMajorAxis : Semi-Major Axis

Eccentricity : Eccentricity

Inclination : Inclination

Aop : Argument of Perigee

Raan : Right Angle of the Ascending Node

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
static cartesian(
cartesian_state: Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity],
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create a COE model from Cartesian state.

Parameters:

  • cartesian_state (CartesianState) -- The Cartesian state.

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

Returns:

The COE model.

Return type:

COE

static compute_angular_momentum(*args, **kwargs)

Overloaded function.

  1. compute_angular_momentum(semi_major_axis: ostk.core.type.Real, eccentricity: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-major axis and the eccentricity.

    Args:

    semi_major_axis (float): The semi-major axis. In meters. eccentricity (float): The eccentricity. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

  2. compute_angular_momentum(semi_latus_rectum: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-latus rectum.

    Args:

    semi_latus_rectum (float): The semi-latus rectum. In meters. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

static compute_radial_distance(
semi_latus_rectum: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
true_anomaly: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the radial distance from the semi-latus rectum and the eccentricity.

Parameters:

  • semi_latus_rectum (float) -- The semi-latus rectum. In meters.

  • eccentricity (float) -- The eccentricity.

  • true_anomaly (float) -- The true anomly. In degrees.

Returns:

The radial distance.

Return type:

Length

static compute_semi_latus_rectum(
semi_major_axis: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

Parameters:

  • semi_major_axis (float) -- The semi-major axis. In meters.

  • eccentricity (float) -- The eccentricity.

Returns:

The semi-latus rectum.

Return type:

Length

static eccentric_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The eccentric anomaly.

Return type:

Angle

static eccentric_anomaly_from_true_anomaly(
true_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the true anomaly.

Parameters:

  • true_anomaly (Angle) -- The true anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The eccentric anomaly.

Return type:

Angle

static from_SI_vector(
vector: numpy.ndarray[numpy.float64[6, 1]],
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create a COE model from a state vector in SI units.

Parameters:

  • vector (Vector6d) -- The state vector.

  • anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The COE model.

Return type:

COE

get_SI_vector(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → numpy.ndarray[numpy.float64[6, 1]]

Get the state vector of the COE in the specified anomaly type.

Parameters:

anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The state vector of the COE in the specified anomaly type.

Return type:

numpy.ndarray

get_angular_momentum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
arg0: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the angular momentum of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The angular momentum of the COE.

Return type:

Derived

get_aop(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the argument of periapsis of the COE.

Returns:

The argument of periapsis of the COE.

Return type:

Angle

get_apoapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the apoapsis radius of the COE.

Returns:

The apoapsis radius of the COE.

Return type:

Length

get_cartesian_state(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
gravitational_parameter: ostk.physics.unit.Derived,
frame: ostk.physics.coordinate.Frame,
) → Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity]

Get the Cartesian state of the BrouwerLyddaneMean model.

Parameters:

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

  • frame (str) -- The reference frame in which the state is expressed.

Returns:

The Cartesian state.

Return type:

CartesianState

get_eccentric_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the eccentric anomaly of the BrouwerLyddaneMean model.

Returns:

The eccentric anomaly.

Return type:

Angle

get_eccentricity(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.core.type.Real

Get the eccentricity of the COE.

Returns:

The eccentricity of the COE.

Return type:

float

get_inclination(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the inclination of the COE.

Returns:

The inclination of the COE.

Return type:

Angle

get_mean_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the mean anomaly of the BrouwerLyddaneMean model.

Returns:

The mean anomaly.

Return type:

Angle

get_mean_motion(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the mean motion of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The mean motion of the COE.

Return type:

Derived

get_nodal_precession_rate(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
equatorial_radius: ostk.physics.unit.Length,
j2: ostk.core.type.Real,
) → ostk.physics.unit.Derived

Get the nodal precession of the COE.

Parameters:

  • gravitational_parameter (Derived) -- The gravitational parameter of the central body.

  • equatorial_radius (Length) -- The equatorial radius of the central body.

  • j2 (float) -- The second zonal harmonic coefficient of the central body.

Returns:

The nodal precession of the COE.

Return type:

Derived

get_orbital_period(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.time.Duration

Get the orbital period of the COE.

Parameters:

gravitational_parameter (double) -- The gravitational parameter of the central body.

Returns:

The orbital period of the COE.

Return type:

Duration

get_periapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the periapsis radius of the COE.

Returns:

The periapsis radius of the COE.

Return type:

Length

get_raan(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the right ascension of the ascending node of the COE.

Returns:

The right ascension of the ascending node of the COE.

Return type:

Angle

get_radial_distance(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the radial distance of the COE.

Returns:

The radial distance of the COE.

Return type:

Length

get_semi_latus_rectum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-latus rectum of the COE.

Returns:

The semilatus rectum of the COE.

Return type:

Length

get_semi_major_axis(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-major axis of the COE.

Returns:

The semi-major axis of the COE.

Return type:

Length

get_true_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the true anomaly of the BrouwerLyddaneMean model.

Returns:

The true anomaly.

Return type:

Angle

is_defined(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → bool

Check if the COE is defined.

Returns:

True if the COE is defined, False otherwise.

Return type:

bool

static mean_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the mean anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The mean anomaly.

Return type:

Angle

static string_from_element(
element: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
) → ostk.core.type.String

Get the string representation of an element.

Parameters:

element (Element) -- The element.

Returns:

The string representation.

Return type:

str

to_coe(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Convert the BrouwerLyddaneMean model to classical orbital elements.

Returns:

The classical orbital elements.

Return type:

COE

static true_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The true anomaly.

Return type:

Angle

static true_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The true anomaly.

Return type:

Angle

static undefined() → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create an undefined COE model.

Returns:

The undefined COE model.

Return type:

COE

\ No newline at end of file + ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean

class BrouwerLyddaneMean(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
semi_major_axis: ostk.physics.unit.Length,
eccentricity: ostk.core.type.Real,
inclination: ostk.physics.unit.Angle,
raan: ostk.physics.unit.Angle,
aop: ostk.physics.unit.Angle,
mean_anomaly: ostk.physics.unit.Angle,
)

Bases: COE

Brouwer-Lyddane mean orbit elements. This is a parent class, please use the Short or Long child classes as appropriate.

Constructor.

Parameters:

  • semi_major_axis (Length) -- The semi-major axis.

  • eccentricity (float) -- The eccentricity.

  • inclination (Angle) -- The inclination.

  • raan (Angle) -- The right ascension of the ascending node.

  • aop (Angle) -- The argument of periapsis.

  • mean_anomaly (Angle) -- The mean anomaly.

Methods

cartesian

Create a COE model from Cartesian state.

compute_angular_momentum

Overloaded function.

compute_radial_distance

Compute the radial distance from the semi-latus rectum and the eccentricity.

compute_semi_latus_rectum

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

eccentric_anomaly_from_mean_anomaly

Compute the eccentric anomaly from the mean anomaly.

eccentric_anomaly_from_true_anomaly

Compute the eccentric anomaly from the true anomaly.

from_SI_vector

Create a COE model from a state vector in SI units.

get_SI_vector

Get the state vector of the COE in the specified anomaly type.

get_angular_momentum

Get the angular momentum of the COE.

get_aop

Get the argument of periapsis of the COE.

get_apoapsis_radius

Get the apoapsis radius of the COE.

get_cartesian_state

Get the Cartesian state of the BrouwerLyddaneMean model.

get_eccentric_anomaly

Get the eccentric anomaly of the BrouwerLyddaneMean model.

get_eccentricity

Get the eccentricity of the COE.

get_inclination

Get the inclination of the COE.

get_mean_anomaly

Get the mean anomaly of the BrouwerLyddaneMean model.

get_mean_motion

Get the mean motion of the COE.

get_nodal_precession_rate

Get the nodal precession of the COE.

get_orbital_period

Get the orbital period of the COE.

get_periapsis_radius

Get the periapsis radius of the COE.

get_raan

Get the right ascension of the ascending node of the COE.

get_radial_distance

Get the radial distance of the COE.

get_semi_latus_rectum

Get the semi-latus rectum of the COE.

get_semi_major_axis

Get the semi-major axis of the COE.

get_true_anomaly

Get the true anomaly of the BrouwerLyddaneMean model.

is_defined

Check if the COE is defined.

mean_anomaly_from_eccentric_anomaly

Compute the mean anomaly from the eccentric anomaly.

string_from_element

Get the string representation of an element.

to_coe

Convert the BrouwerLyddaneMean model to classical orbital elements.

true_anomaly_from_eccentric_anomaly

Compute the true anomaly from the eccentric anomaly.

true_anomaly_from_mean_anomaly

Compute the true anomaly from the mean anomaly.

undefined

Create an undefined COE model.

class AnomalyType(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
value: int,
)

Bases: pybind11_object

The type of Anomaly.

Members:

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
class Element(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
value: int,
)

Bases: pybind11_object

Classical Orbital Element enumeration.

Members:

SemiMajorAxis : Semi-Major Axis

Eccentricity : Eccentricity

Inclination : Inclination

Aop : Argument of Perigee

Raan : Right Angle of the Ascending Node

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
static cartesian(
cartesian_state: Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity],
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create a COE model from Cartesian state.

Parameters:

  • cartesian_state (CartesianState) -- The Cartesian state.

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

Returns:

The COE model.

Return type:

COE

static compute_angular_momentum(*args, **kwargs)

Overloaded function.

  1. compute_angular_momentum(semi_major_axis: ostk.core.type.Real, eccentricity: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-major axis and the eccentricity.

    Args:

    semi_major_axis (float): The semi-major axis. In meters. eccentricity (float): The eccentricity. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

  2. compute_angular_momentum(semi_latus_rectum: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-latus rectum.

    Args:

    semi_latus_rectum (float): The semi-latus rectum. In meters. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

static compute_radial_distance(
semi_latus_rectum: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
true_anomaly: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the radial distance from the semi-latus rectum and the eccentricity.

Parameters:

  • semi_latus_rectum (float) -- The semi-latus rectum. In meters.

  • eccentricity (float) -- The eccentricity.

  • true_anomaly (float) -- The true anomly. In degrees.

Returns:

The radial distance.

Return type:

Length

static compute_semi_latus_rectum(
semi_major_axis: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

Parameters:

  • semi_major_axis (float) -- The semi-major axis. In meters.

  • eccentricity (float) -- The eccentricity.

Returns:

The semi-latus rectum.

Return type:

Length

static eccentric_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The eccentric anomaly.

Return type:

Angle

static eccentric_anomaly_from_true_anomaly(
true_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the true anomaly.

Parameters:

  • true_anomaly (Angle) -- The true anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The eccentric anomaly.

Return type:

Angle

static from_SI_vector(
vector: numpy.ndarray[numpy.float64[6, 1]],
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create a COE model from a state vector in SI units.

Parameters:

  • vector (Vector6d) -- The state vector.

  • anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The COE model.

Return type:

COE

get_SI_vector(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → numpy.ndarray[numpy.float64[6, 1]]

Get the state vector of the COE in the specified anomaly type.

Parameters:

anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The state vector of the COE in the specified anomaly type.

Return type:

numpy.ndarray

get_angular_momentum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
arg0: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the angular momentum of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The angular momentum of the COE.

Return type:

Derived

get_aop(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the argument of periapsis of the COE.

Returns:

The argument of periapsis of the COE.

Return type:

Angle

get_apoapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the apoapsis radius of the COE.

Returns:

The apoapsis radius of the COE.

Return type:

Length

get_cartesian_state(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
gravitational_parameter: ostk.physics.unit.Derived,
frame: ostk.physics.coordinate.Frame,
) → Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity]

Get the Cartesian state of the BrouwerLyddaneMean model.

Parameters:

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

  • frame (str) -- The reference frame in which the state is expressed.

Returns:

The Cartesian state.

Return type:

CartesianState

get_eccentric_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the eccentric anomaly of the BrouwerLyddaneMean model.

Returns:

The eccentric anomaly.

Return type:

Angle

get_eccentricity(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.core.type.Real

Get the eccentricity of the COE.

Returns:

The eccentricity of the COE.

Return type:

float

get_inclination(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the inclination of the COE.

Returns:

The inclination of the COE.

Return type:

Angle

get_mean_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the mean anomaly of the BrouwerLyddaneMean model.

Returns:

The mean anomaly.

Return type:

Angle

get_mean_motion(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the mean motion of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The mean motion of the COE.

Return type:

Derived

get_nodal_precession_rate(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
equatorial_radius: ostk.physics.unit.Length,
j2: ostk.core.type.Real,
) → ostk.physics.unit.Derived

Get the nodal precession of the COE.

Parameters:

  • gravitational_parameter (Derived) -- The gravitational parameter of the central body.

  • equatorial_radius (Length) -- The equatorial radius of the central body.

  • j2 (float) -- The second zonal harmonic coefficient of the central body.

Returns:

The nodal precession of the COE.

Return type:

Derived

get_orbital_period(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.time.Duration

Get the orbital period of the COE.

Parameters:

gravitational_parameter (double) -- The gravitational parameter of the central body.

Returns:

The orbital period of the COE.

Return type:

Duration

get_periapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the periapsis radius of the COE.

Returns:

The periapsis radius of the COE.

Return type:

Length

get_raan(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the right ascension of the ascending node of the COE.

Returns:

The right ascension of the ascending node of the COE.

Return type:

Angle

get_radial_distance(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the radial distance of the COE.

Returns:

The radial distance of the COE.

Return type:

Length

get_semi_latus_rectum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-latus rectum of the COE.

Returns:

The semilatus rectum of the COE.

Return type:

Length

get_semi_major_axis(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-major axis of the COE.

Returns:

The semi-major axis of the COE.

Return type:

Length

get_true_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the true anomaly of the BrouwerLyddaneMean model.

Returns:

The true anomaly.

Return type:

Angle

is_defined(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → bool

Check if the COE is defined.

Returns:

True if the COE is defined, False otherwise.

Return type:

bool

static mean_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the mean anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The mean anomaly.

Return type:

Angle

static string_from_element(
element: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
) → ostk.core.type.String

Get the string representation of an element.

Parameters:

element (Element) -- The element.

Returns:

The string representation.

Return type:

str

to_coe(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Convert the BrouwerLyddaneMean model to classical orbital elements.

Returns:

The classical orbital elements.

Return type:

COE

static true_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The true anomaly.

Return type:

Angle

static true_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The true anomaly.

Return type:

Angle

static undefined() → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create an undefined COE model.

Returns:

The undefined COE model.

Return type:

COE

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.Kepler.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.Kepler.html index 7873a6152..da7291cd6 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.Kepler.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.Kepler.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.orbit.model.Kepler — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.Kepler

class Kepler(*args, **kwargs)

Bases: OrbitModel

A Kepler orbit model.

Provides the interface for orbit models.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.orbit.model.Kepler, coe: ostk::astrodynamics::trajectory::orbit::model::kepler::COE, epoch: ostk.physics.time.Instant, gravitational_parameter: ostk.physics.unit.Derived, equatorial_radius: ostk.physics.unit.Length, j2: ostk.core.type.Real, j4: ostk.core.type.Real, perturbation_type: ostk.astrodynamics.trajectory.orbit.model.Kepler.PerturbationType) -> None

    Constructor.

    Args:

    coe (COE): The classical orbital elements. epoch (Instant): The epoch. gravitational_parameter (Derived): The gravitational parameter. equatorial_radius (Length): The equatorial radius. j2 (float): The J2 coefficient. j4 (float): The J4 coefficient. perturbation_type (PerturbationType): The perturbation type.

  2. __init__(self: ostk.astrodynamics.trajectory.orbit.model.Kepler, coe: ostk::astrodynamics::trajectory::orbit::model::kepler::COE, epoch: ostk.physics.time.Instant, celestial_object: ostk.physics.environment.object.Celestial, perturbation_type: ostk.astrodynamics.trajectory.orbit.model.Kepler.PerturbationType, in_fixed_frame: bool = False) -> None

    Constructor.

    Args:

    coe (COE): The classical orbital elements. epoch (Instant): The epoch. celestial_object (Celestial): The celestial object. perturbation_type (PerturbationType): The perturbation type. in_fixed_frame (bool): If True, the state is expressed in the fixed frame, otherwise it is expressed in the inertial frame. Default is False.

Methods

as_kepler

Cast the orbit model to a Kepler model.

as_propagated

Cast the orbit model to a propagated model.

as_sgp4

Cast the orbit model to an SGP4 model.

calculate_revolution_number_at

Calculate the revolution number of the Kepler model at a given instant.

calculate_state_at

Calculate the state of the Kepler model at a given instant.

get_classical_orbital_elements

Get the classical orbital elements of the Kepler model.

get_epoch

Get the epoch of the Kepler model.

get_equatorial_radius

Get the equatorial radius of the Kepler model.

get_gravitational_parameter

Get the gravitational parameter of the Kepler model.

get_j2

Get the J2 coefficient of the Kepler model.

get_j4

Get the J4 coefficient of the Kepler model.

get_perturbation_type

Get the perturbation type of the Kepler model.

get_revolution_number_at_epoch

Get the revolution number at the epoch of the Kepler model.

is_defined

Check if the Kepler model is defined.

is_kepler

Check if the orbit model is a Kepler model.

is_propagated

Check if the orbit model is a propagated model.

is_sgp4

Check if the orbit model is an SGP4 model.

string_from_perturbation_type

Get the string representation of a PerturbationType.

class PerturbationType(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler.PerturbationType,
value: int,
)

Bases: pybind11_object

The Perturbation Type due to Oblateness

Members:

No : No perturbation

J2 : J2 perturbation

J4 : J4 perturbation

property name
as_kepler(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Kepler

Cast the orbit model to a Kepler model.

Returns:

The Kepler model.

Return type:

Kepler

as_propagated(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Propagated

Cast the orbit model to a propagated model.

Returns:

The propagated model.

Return type:

Propagated

as_sgp4(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::SGP4

Cast the orbit model to an SGP4 model.

Returns:

The SGP4 model.

Return type:

SGP4

calculate_revolution_number_at(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
instant: ostk.physics.time.Instant,
) → ostk.core.type.Integer

Calculate the revolution number of the Kepler model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The revolution number.

Return type:

int

calculate_state_at(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
instant: ostk.physics.time.Instant,
) → ostk.astrodynamics.trajectory.State

Calculate the state of the Kepler model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state.

Return type:

State

get_classical_orbital_elements(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk::astrodynamics::trajectory::orbit::model::kepler::COE

Get the classical orbital elements of the Kepler model.

Returns:

The classical orbital elements.

Return type:

COE

get_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk.physics.time.Instant

Get the epoch of the Kepler model.

Returns:

The epoch.

Return type:

Instant

get_equatorial_radius(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk.physics.unit.Length

Get the equatorial radius of the Kepler model.

Returns:

The equatorial radius.

Return type:

Length

get_gravitational_parameter(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk.physics.unit.Derived

Get the gravitational parameter of the Kepler model.

Returns:

The gravitational parameter.

Return type:

Derived

get_j2(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk.core.type.Real

Get the J2 coefficient of the Kepler model.

Returns:

The J2 coefficient.

Return type:

float

get_j4(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk.core.type.Real

Get the J4 coefficient of the Kepler model.

Returns:

The J4 coefficient.

Return type:

float

get_perturbation_type(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk.astrodynamics.trajectory.orbit.model.Kepler.PerturbationType

Get the perturbation type of the Kepler model.

Returns:

The perturbation type.

Return type:

PerturbationType

get_revolution_number_at_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk.core.type.Integer

Get the revolution number at the epoch of the Kepler model.

Returns:

The revolution number.

Return type:

int

is_defined(self: ostk.astrodynamics.trajectory.orbit.model.Kepler) → bool

Check if the Kepler model is defined.

Returns:

True if the Kepler model is defined, False otherwise.

Return type:

bool

is_kepler(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a Kepler model.

Returns:

True if the orbit model is a Kepler model, False otherwise.

Return type:

bool

is_propagated(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a propagated model.

Returns:

True if the orbit model is a propagated model, False otherwise.

Return type:

bool

is_sgp4(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is an SGP4 model.

Returns:

True if the orbit model is an SGP4 model, False otherwise.

Return type:

bool

static string_from_perturbation_type(
perturbation_type: ostk.astrodynamics.trajectory.orbit.model.Kepler.PerturbationType,
) → ostk.core.type.String

Get the string representation of a PerturbationType.

Parameters:

perturbation_type (PerturbationType) -- The perturbation type.

Returns:

The string representation.

Return type:

str

\ No newline at end of file + ostk.astrodynamics.trajectory.orbit.model.Kepler — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.Kepler

class Kepler(*args, **kwargs)

Bases: OrbitModel

A Kepler orbit model.

Provides the interface for orbit models.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.orbit.model.Kepler, coe: ostk::astrodynamics::trajectory::orbit::model::kepler::COE, epoch: ostk.physics.time.Instant, gravitational_parameter: ostk.physics.unit.Derived, equatorial_radius: ostk.physics.unit.Length, j2: ostk.core.type.Real, j4: ostk.core.type.Real, perturbation_type: ostk.astrodynamics.trajectory.orbit.model.Kepler.PerturbationType) -> None

    Constructor.

    Args:

    coe (COE): The classical orbital elements. epoch (Instant): The epoch. gravitational_parameter (Derived): The gravitational parameter. equatorial_radius (Length): The equatorial radius. j2 (float): The J2 coefficient. j4 (float): The J4 coefficient. perturbation_type (PerturbationType): The perturbation type.

  2. __init__(self: ostk.astrodynamics.trajectory.orbit.model.Kepler, coe: ostk::astrodynamics::trajectory::orbit::model::kepler::COE, epoch: ostk.physics.time.Instant, celestial_object: ostk.physics.environment.object.Celestial, perturbation_type: ostk.astrodynamics.trajectory.orbit.model.Kepler.PerturbationType, in_fixed_frame: bool = False) -> None

    Constructor.

    Args:

    coe (COE): The classical orbital elements. epoch (Instant): The epoch. celestial_object (Celestial): The celestial object. perturbation_type (PerturbationType): The perturbation type. in_fixed_frame (bool): If True, the state is expressed in the fixed frame, otherwise it is expressed in the inertial frame. Default is False.

Methods

as_kepler

Cast the orbit model to a Kepler model.

as_propagated

Cast the orbit model to a propagated model.

as_sgp4

Cast the orbit model to an SGP4 model.

calculate_revolution_number_at

Calculate the revolution number of the Kepler model at a given instant.

calculate_state_at

Calculate the state of the Kepler model at a given instant.

get_classical_orbital_elements

Get the classical orbital elements of the Kepler model.

get_epoch

Get the epoch of the Kepler model.

get_equatorial_radius

Get the equatorial radius of the Kepler model.

get_gravitational_parameter

Get the gravitational parameter of the Kepler model.

get_j2

Get the J2 coefficient of the Kepler model.

get_j4

Get the J4 coefficient of the Kepler model.

get_perturbation_type

Get the perturbation type of the Kepler model.

get_revolution_number_at_epoch

Get the revolution number at the epoch of the Kepler model.

is_defined

Check if the Kepler model is defined.

is_kepler

Check if the orbit model is a Kepler model.

is_propagated

Check if the orbit model is a propagated model.

is_sgp4

Check if the orbit model is an SGP4 model.

string_from_perturbation_type

Get the string representation of a PerturbationType.

class PerturbationType(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler.PerturbationType,
value: int,
)

Bases: pybind11_object

The Perturbation Type due to Oblateness

Members:

No : No perturbation

J2 : J2 perturbation

J4 : J4 perturbation

property name
as_kepler(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Kepler

Cast the orbit model to a Kepler model.

Returns:

The Kepler model.

Return type:

Kepler

as_propagated(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Propagated

Cast the orbit model to a propagated model.

Returns:

The propagated model.

Return type:

Propagated

as_sgp4(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::SGP4

Cast the orbit model to an SGP4 model.

Returns:

The SGP4 model.

Return type:

SGP4

calculate_revolution_number_at(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
instant: ostk.physics.time.Instant,
) → ostk.core.type.Integer

Calculate the revolution number of the Kepler model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The revolution number.

Return type:

int

calculate_state_at(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
instant: ostk.physics.time.Instant,
) → ostk.astrodynamics.trajectory.State

Calculate the state of the Kepler model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state.

Return type:

State

get_classical_orbital_elements(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk::astrodynamics::trajectory::orbit::model::kepler::COE

Get the classical orbital elements of the Kepler model.

Returns:

The classical orbital elements.

Return type:

COE

get_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk.physics.time.Instant

Get the epoch of the Kepler model.

Returns:

The epoch.

Return type:

Instant

get_equatorial_radius(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk.physics.unit.Length

Get the equatorial radius of the Kepler model.

Returns:

The equatorial radius.

Return type:

Length

get_gravitational_parameter(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk.physics.unit.Derived

Get the gravitational parameter of the Kepler model.

Returns:

The gravitational parameter.

Return type:

Derived

get_j2(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk.core.type.Real

Get the J2 coefficient of the Kepler model.

Returns:

The J2 coefficient.

Return type:

float

get_j4(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk.core.type.Real

Get the J4 coefficient of the Kepler model.

Returns:

The J4 coefficient.

Return type:

float

get_perturbation_type(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk.astrodynamics.trajectory.orbit.model.Kepler.PerturbationType

Get the perturbation type of the Kepler model.

Returns:

The perturbation type.

Return type:

PerturbationType

get_revolution_number_at_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.Kepler,
) → ostk.core.type.Integer

Get the revolution number at the epoch of the Kepler model.

Returns:

The revolution number.

Return type:

int

is_defined(self: ostk.astrodynamics.trajectory.orbit.model.Kepler) → bool

Check if the Kepler model is defined.

Returns:

True if the Kepler model is defined, False otherwise.

Return type:

bool

is_kepler(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a Kepler model.

Returns:

True if the orbit model is a Kepler model, False otherwise.

Return type:

bool

is_propagated(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a propagated model.

Returns:

True if the orbit model is a propagated model, False otherwise.

Return type:

bool

is_sgp4(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is an SGP4 model.

Returns:

True if the orbit model is an SGP4 model, False otherwise.

Return type:

bool

static string_from_perturbation_type(
perturbation_type: ostk.astrodynamics.trajectory.orbit.model.Kepler.PerturbationType,
) → ostk.core.type.String

Get the string representation of a PerturbationType.

Parameters:

perturbation_type (PerturbationType) -- The perturbation type.

Returns:

The string representation.

Return type:

str

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.Propagated.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.Propagated.html index 360d42a79..881aca109 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.Propagated.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.Propagated.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.orbit.model.Propagated — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.Propagated

class Propagated(*args, **kwargs)

Bases: OrbitModel

A Propagated orbit model.

Provides the interface for orbit models.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.orbit.model.Propagated, propagator: ostk::astrodynamics::trajectory::Propagator, state: ostk.astrodynamics.trajectory.State, initial_revolution_number: ostk.core.type.Integer = 1) -> None

    Constructor.

    Args:

    propagator (Propagator): The propagator. state (State): The initial state. initial_revolution_number (int, optional): The initial revolution number. Defaults to 1.

  2. __init__(self: ostk.astrodynamics.trajectory.orbit.model.Propagated, propagator: ostk::astrodynamics::trajectory::Propagator, state_array: List[ostk.astrodynamics.trajectory.State], initial_revolution_number: ostk.core.type.Integer = 1) -> None

    Constructor.

    Args:

    propagator (Propagator): The propagator. state_array (list[State]): The initial state array. initial_revolution_number (int, optional): The initial revolution number. Defaults to 1.

Methods

access_cached_state_array

Access the cached state array of the Propagated model.

access_propagator

Access the propagator of the Propagated model.

as_kepler

Cast the orbit model to a Kepler model.

as_propagated

Cast the orbit model to a propagated model.

as_sgp4

Cast the orbit model to an SGP4 model.

calculate_revolution_number_at

Calculate the revolution number of the Propagated model at a given instant.

calculate_state_at

Calculate the state of the Propagated model at a given instant.

calculate_states_at

Calculate the states of the Propagated model at given instants.

get_epoch

Get the epoch of the Propagated model.

get_revolution_number_at_epoch

Get the revolution number at the epoch of the Propagated model.

is_defined

Check if the Propagated model is defined.

is_kepler

Check if the orbit model is a Kepler model.

is_propagated

Check if the orbit model is a propagated model.

is_sgp4

Check if the orbit model is an SGP4 model.

set_cached_state_array

Set the cached state array of the Propagated model.

access_cached_state_array(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
) → List[ostk.astrodynamics.trajectory.State]

Access the cached state array of the Propagated model.

Returns:

The cached state array.

Return type:

list[State]

access_propagator(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
) → ostk::astrodynamics::trajectory::Propagator

Access the propagator of the Propagated model.

Returns:

The propagator.

Return type:

Propagator

as_kepler(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Kepler

Cast the orbit model to a Kepler model.

Returns:

The Kepler model.

Return type:

Kepler

as_propagated(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Propagated

Cast the orbit model to a propagated model.

Returns:

The propagated model.

Return type:

Propagated

as_sgp4(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::SGP4

Cast the orbit model to an SGP4 model.

Returns:

The SGP4 model.

Return type:

SGP4

calculate_revolution_number_at(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
instant: ostk.physics.time.Instant,
) → ostk.core.type.Integer

Calculate the revolution number of the Propagated model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The revolution number.

Return type:

int

calculate_state_at(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
instant: ostk.physics.time.Instant,
) → ostk.astrodynamics.trajectory.State

Calculate the state of the Propagated model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state.

Return type:

State

calculate_states_at(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
instants: List[ostk.physics.time.Instant],
) → List[ostk.astrodynamics.trajectory.State]

Calculate the states of the Propagated model at given instants.

Parameters:

instants (list[Instant]) -- The instants.

Returns:

The states.

Return type:

list[State]

get_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
) → ostk.physics.time.Instant

Get the epoch of the Propagated model.

Returns:

The epoch.

Return type:

Instant

get_revolution_number_at_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
) → ostk.core.type.Integer

Get the revolution number at the epoch of the Propagated model.

Returns:

The revolution number.

Return type:

int

is_defined(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
) → bool

Check if the Propagated model is defined.

Returns:

True if the Propagated model is defined, False otherwise.

Return type:

bool

is_kepler(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a Kepler model.

Returns:

True if the orbit model is a Kepler model, False otherwise.

Return type:

bool

is_propagated(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a propagated model.

Returns:

True if the orbit model is a propagated model, False otherwise.

Return type:

bool

is_sgp4(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is an SGP4 model.

Returns:

True if the orbit model is an SGP4 model, False otherwise.

Return type:

bool

set_cached_state_array(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
state_array: List[ostk.astrodynamics.trajectory.State],
) → None

Set the cached state array of the Propagated model.

Parameters:

state_array (list[State]) -- The state array.

\ No newline at end of file + ostk.astrodynamics.trajectory.orbit.model.Propagated — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.Propagated

class Propagated(*args, **kwargs)

Bases: OrbitModel

A Propagated orbit model.

Provides the interface for orbit models.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.orbit.model.Propagated, propagator: ostk::astrodynamics::trajectory::Propagator, state: ostk.astrodynamics.trajectory.State, initial_revolution_number: ostk.core.type.Integer = 1) -> None

    Constructor.

    Args:

    propagator (Propagator): The propagator. state (State): The initial state. initial_revolution_number (int, optional): The initial revolution number. Defaults to 1.

  2. __init__(self: ostk.astrodynamics.trajectory.orbit.model.Propagated, propagator: ostk::astrodynamics::trajectory::Propagator, state_array: List[ostk.astrodynamics.trajectory.State], initial_revolution_number: ostk.core.type.Integer = 1) -> None

    Constructor.

    Args:

    propagator (Propagator): The propagator. state_array (list[State]): The initial state array. initial_revolution_number (int, optional): The initial revolution number. Defaults to 1.

Methods

access_cached_state_array

Access the cached state array of the Propagated model.

access_propagator

Access the propagator of the Propagated model.

as_kepler

Cast the orbit model to a Kepler model.

as_propagated

Cast the orbit model to a propagated model.

as_sgp4

Cast the orbit model to an SGP4 model.

calculate_revolution_number_at

Calculate the revolution number of the Propagated model at a given instant.

calculate_state_at

Calculate the state of the Propagated model at a given instant.

calculate_states_at

Calculate the states of the Propagated model at given instants.

get_epoch

Get the epoch of the Propagated model.

get_revolution_number_at_epoch

Get the revolution number at the epoch of the Propagated model.

is_defined

Check if the Propagated model is defined.

is_kepler

Check if the orbit model is a Kepler model.

is_propagated

Check if the orbit model is a propagated model.

is_sgp4

Check if the orbit model is an SGP4 model.

set_cached_state_array

Set the cached state array of the Propagated model.

access_cached_state_array(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
) → List[ostk.astrodynamics.trajectory.State]

Access the cached state array of the Propagated model.

Returns:

The cached state array.

Return type:

list[State]

access_propagator(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
) → ostk::astrodynamics::trajectory::Propagator

Access the propagator of the Propagated model.

Returns:

The propagator.

Return type:

Propagator

as_kepler(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Kepler

Cast the orbit model to a Kepler model.

Returns:

The Kepler model.

Return type:

Kepler

as_propagated(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Propagated

Cast the orbit model to a propagated model.

Returns:

The propagated model.

Return type:

Propagated

as_sgp4(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::SGP4

Cast the orbit model to an SGP4 model.

Returns:

The SGP4 model.

Return type:

SGP4

calculate_revolution_number_at(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
instant: ostk.physics.time.Instant,
) → ostk.core.type.Integer

Calculate the revolution number of the Propagated model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The revolution number.

Return type:

int

calculate_state_at(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
instant: ostk.physics.time.Instant,
) → ostk.astrodynamics.trajectory.State

Calculate the state of the Propagated model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state.

Return type:

State

calculate_states_at(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
instants: List[ostk.physics.time.Instant],
) → List[ostk.astrodynamics.trajectory.State]

Calculate the states of the Propagated model at given instants.

Parameters:

instants (list[Instant]) -- The instants.

Returns:

The states.

Return type:

list[State]

get_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
) → ostk.physics.time.Instant

Get the epoch of the Propagated model.

Returns:

The epoch.

Return type:

Instant

get_revolution_number_at_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
) → ostk.core.type.Integer

Get the revolution number at the epoch of the Propagated model.

Returns:

The revolution number.

Return type:

int

is_defined(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
) → bool

Check if the Propagated model is defined.

Returns:

True if the Propagated model is defined, False otherwise.

Return type:

bool

is_kepler(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a Kepler model.

Returns:

True if the orbit model is a Kepler model, False otherwise.

Return type:

bool

is_propagated(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a propagated model.

Returns:

True if the orbit model is a propagated model, False otherwise.

Return type:

bool

is_sgp4(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is an SGP4 model.

Returns:

True if the orbit model is an SGP4 model, False otherwise.

Return type:

bool

set_cached_state_array(
self: ostk.astrodynamics.trajectory.orbit.model.Propagated,
state_array: List[ostk.astrodynamics.trajectory.State],
) → None

Set the cached state array of the Propagated model.

Parameters:

state_array (list[State]) -- The state array.

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.SGP4.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.SGP4.html index 6ac61c684..3bc0fed66 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.SGP4.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.SGP4.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.orbit.model.SGP4 — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.SGP4

class SGP4(
self: ostk.astrodynamics.trajectory.orbit.model.SGP4,
tle: ostk::astrodynamics::trajectory::orbit::model::sgp4::TLE,
)

Bases: OrbitModel

A SGP4 model.

Provides the interface for orbit models.

Constructor.

Parameters:

tle (TLE) -- The TLE.

Methods

as_kepler

Cast the orbit model to a Kepler model.

as_propagated

Cast the orbit model to a propagated model.

as_sgp4

Cast the orbit model to an SGP4 model.

calculate_revolution_number_at

Calculate the revolution number of the SGP4 model at a given instant.

calculate_state_at

Calculate the state of the SGP4 model at a given instant.

get_epoch

Get the epoch of the SGP4 model.

get_revolution_number_at_epoch

Get the revolution number at the epoch of the SGP4 model.

get_tle

Get the TLE of the SGP4 model.

is_defined

Check if the SGP4 model is defined.

is_kepler

Check if the orbit model is a Kepler model.

is_propagated

Check if the orbit model is a propagated model.

is_sgp4

Check if the orbit model is an SGP4 model.

as_kepler(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Kepler

Cast the orbit model to a Kepler model.

Returns:

The Kepler model.

Return type:

Kepler

as_propagated(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Propagated

Cast the orbit model to a propagated model.

Returns:

The propagated model.

Return type:

Propagated

as_sgp4(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::SGP4

Cast the orbit model to an SGP4 model.

Returns:

The SGP4 model.

Return type:

SGP4

calculate_revolution_number_at(
self: ostk.astrodynamics.trajectory.orbit.model.SGP4,
instant: ostk.physics.time.Instant,
) → ostk.core.type.Integer

Calculate the revolution number of the SGP4 model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The revolution number.

Return type:

int

calculate_state_at(
self: ostk.astrodynamics.trajectory.orbit.model.SGP4,
instant: ostk.physics.time.Instant,
) → ostk.astrodynamics.trajectory.State

Calculate the state of the SGP4 model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state.

Return type:

State

get_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.SGP4,
) → ostk.physics.time.Instant

Get the epoch of the SGP4 model.

Returns:

The epoch.

Return type:

Instant

get_revolution_number_at_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.SGP4,
) → ostk.core.type.Integer

Get the revolution number at the epoch of the SGP4 model.

Returns:

The revolution number.

Return type:

int

get_tle(
self: ostk.astrodynamics.trajectory.orbit.model.SGP4,
) → ostk::astrodynamics::trajectory::orbit::model::sgp4::TLE

Get the TLE of the SGP4 model.

Returns:

The TLE.

Return type:

TLE

is_defined(self: ostk.astrodynamics.trajectory.orbit.model.SGP4) → bool

Check if the SGP4 model is defined.

Returns:

True if the SGP4 model is defined, False otherwise.

Return type:

bool

is_kepler(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a Kepler model.

Returns:

True if the orbit model is a Kepler model, False otherwise.

Return type:

bool

is_propagated(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a propagated model.

Returns:

True if the orbit model is a propagated model, False otherwise.

Return type:

bool

is_sgp4(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is an SGP4 model.

Returns:

True if the orbit model is an SGP4 model, False otherwise.

Return type:

bool

\ No newline at end of file + ostk.astrodynamics.trajectory.orbit.model.SGP4 — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.SGP4

class SGP4(
self: ostk.astrodynamics.trajectory.orbit.model.SGP4,
tle: ostk::astrodynamics::trajectory::orbit::model::sgp4::TLE,
)

Bases: OrbitModel

A SGP4 model.

Provides the interface for orbit models.

Constructor.

Parameters:

tle (TLE) -- The TLE.

Methods

as_kepler

Cast the orbit model to a Kepler model.

as_propagated

Cast the orbit model to a propagated model.

as_sgp4

Cast the orbit model to an SGP4 model.

calculate_revolution_number_at

Calculate the revolution number of the SGP4 model at a given instant.

calculate_state_at

Calculate the state of the SGP4 model at a given instant.

get_epoch

Get the epoch of the SGP4 model.

get_revolution_number_at_epoch

Get the revolution number at the epoch of the SGP4 model.

get_tle

Get the TLE of the SGP4 model.

is_defined

Check if the SGP4 model is defined.

is_kepler

Check if the orbit model is a Kepler model.

is_propagated

Check if the orbit model is a propagated model.

is_sgp4

Check if the orbit model is an SGP4 model.

as_kepler(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Kepler

Cast the orbit model to a Kepler model.

Returns:

The Kepler model.

Return type:

Kepler

as_propagated(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Propagated

Cast the orbit model to a propagated model.

Returns:

The propagated model.

Return type:

Propagated

as_sgp4(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::SGP4

Cast the orbit model to an SGP4 model.

Returns:

The SGP4 model.

Return type:

SGP4

calculate_revolution_number_at(
self: ostk.astrodynamics.trajectory.orbit.model.SGP4,
instant: ostk.physics.time.Instant,
) → ostk.core.type.Integer

Calculate the revolution number of the SGP4 model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The revolution number.

Return type:

int

calculate_state_at(
self: ostk.astrodynamics.trajectory.orbit.model.SGP4,
instant: ostk.physics.time.Instant,
) → ostk.astrodynamics.trajectory.State

Calculate the state of the SGP4 model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state.

Return type:

State

get_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.SGP4,
) → ostk.physics.time.Instant

Get the epoch of the SGP4 model.

Returns:

The epoch.

Return type:

Instant

get_revolution_number_at_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.SGP4,
) → ostk.core.type.Integer

Get the revolution number at the epoch of the SGP4 model.

Returns:

The revolution number.

Return type:

int

get_tle(
self: ostk.astrodynamics.trajectory.orbit.model.SGP4,
) → ostk::astrodynamics::trajectory::orbit::model::sgp4::TLE

Get the TLE of the SGP4 model.

Returns:

The TLE.

Return type:

TLE

is_defined(self: ostk.astrodynamics.trajectory.orbit.model.SGP4) → bool

Check if the SGP4 model is defined.

Returns:

True if the SGP4 model is defined, False otherwise.

Return type:

bool

is_kepler(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a Kepler model.

Returns:

True if the orbit model is a Kepler model, False otherwise.

Return type:

bool

is_propagated(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a propagated model.

Returns:

True if the orbit model is a propagated model, False otherwise.

Return type:

bool

is_sgp4(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is an SGP4 model.

Returns:

True if the orbit model is an SGP4 model, False otherwise.

Return type:

bool

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.Tabulated.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.Tabulated.html index 7be071327..628046632 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.Tabulated.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.Tabulated.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.orbit.model.Tabulated — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.Tabulated

class Tabulated(self: ostk.astrodynamics.trajectory.orbit.model.Tabulated, states: List[ostk.astrodynamics.trajectory.State], initial_revolution_number: ostk.core.type.Integer, interpolation_type: ostk.mathematics.curve_fitting.Interpolator.Type = <Type.Linear: 2>)

Bases: OrbitModel

Tabulated orbit model.

Constructor.

Parameters:

  • states (list[State]) -- The states.

  • initial_revolution_number (int) -- The initial revolution number.

  • interpolation_type (Interpolator.Type, optional) -- The interpolation type.

Methods

as_kepler

Cast the orbit model to a Kepler model.

as_propagated

Cast the orbit model to a propagated model.

as_sgp4

Cast the orbit model to an SGP4 model.

calculate_revolution_number_at

Calculate the revolution number of the Tabulated model at a given instant.

calculate_state_at

Calculate the state of the Tabulated model at a given instant.

calculate_states_at

Calculate the states of the Tabulated model at given instants.

get_epoch

Get the epoch of the Tabulated model.

get_interpolation_type

Get the interpolation type of the Tabulated model.

get_interval

Get the interval of the Tabulated model.

get_revolution_number_at_epoch

Get the revolution number at the epoch of the Tabulated model.

is_defined

Check if the Tabulated model is defined.

is_kepler

Check if the orbit model is a Kepler model.

is_propagated

Check if the orbit model is a propagated model.

is_sgp4

Check if the orbit model is an SGP4 model.

as_kepler(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Kepler

Cast the orbit model to a Kepler model.

Returns:

The Kepler model.

Return type:

Kepler

as_propagated(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Propagated

Cast the orbit model to a propagated model.

Returns:

The propagated model.

Return type:

Propagated

as_sgp4(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::SGP4

Cast the orbit model to an SGP4 model.

Returns:

The SGP4 model.

Return type:

SGP4

calculate_revolution_number_at(
self: ostk.astrodynamics.trajectory.orbit.model.Tabulated,
instant: ostk.physics.time.Instant,
) → ostk.core.type.Integer

Calculate the revolution number of the Tabulated model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The revolution number.

Return type:

int

calculate_state_at(
self: ostk.astrodynamics.trajectory.orbit.model.Tabulated,
instant: ostk.physics.time.Instant,
) → ostk.astrodynamics.trajectory.State

Calculate the state of the Tabulated model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state.

Return type:

State

calculate_states_at(
self: ostk.astrodynamics.trajectory.orbit.model.Tabulated,
instants: List[ostk.physics.time.Instant],
) → List[ostk.astrodynamics.trajectory.State]

Calculate the states of the Tabulated model at given instants.

Parameters:

instants (list[Instant]) -- The instants.

Returns:

The states.

Return type:

list[State]

get_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.Tabulated,
) → ostk.physics.time.Instant

Get the epoch of the Tabulated model.

Returns:

The epoch.

Return type:

Instant

get_interpolation_type(
self: ostk.astrodynamics.trajectory.orbit.model.Tabulated,
) → ostk.mathematics.curve_fitting.Interpolator.Type

Get the interpolation type of the Tabulated model.

Returns:

The interpolation type.

Return type:

Interpolator.Type

get_interval(
self: ostk.astrodynamics.trajectory.orbit.model.Tabulated,
) → ostk.physics.time.Interval

Get the interval of the Tabulated model.

Returns:

The interval.

Return type:

Interval

get_revolution_number_at_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.Tabulated,
) → ostk.core.type.Integer

Get the revolution number at the epoch of the Tabulated model.

Returns:

The revolution number.

Return type:

int

is_defined(self: ostk.astrodynamics.trajectory.orbit.model.Tabulated) → bool

Check if the Tabulated model is defined.

Returns:

True if the Tabulated model is defined, False otherwise.

Return type:

bool

is_kepler(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a Kepler model.

Returns:

True if the orbit model is a Kepler model, False otherwise.

Return type:

bool

is_propagated(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a propagated model.

Returns:

True if the orbit model is a propagated model, False otherwise.

Return type:

bool

is_sgp4(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is an SGP4 model.

Returns:

True if the orbit model is an SGP4 model, False otherwise.

Return type:

bool

\ No newline at end of file + ostk.astrodynamics.trajectory.orbit.model.Tabulated — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.Tabulated

class Tabulated(self: ostk.astrodynamics.trajectory.orbit.model.Tabulated, states: List[ostk.astrodynamics.trajectory.State], initial_revolution_number: ostk.core.type.Integer, interpolation_type: ostk.mathematics.curve_fitting.Interpolator.Type = <Type.Linear: 2>)

Bases: OrbitModel

Tabulated orbit model.

Constructor.

Parameters:

  • states (list[State]) -- The states.

  • initial_revolution_number (int) -- The initial revolution number.

  • interpolation_type (Interpolator.Type, optional) -- The interpolation type.

Methods

as_kepler

Cast the orbit model to a Kepler model.

as_propagated

Cast the orbit model to a propagated model.

as_sgp4

Cast the orbit model to an SGP4 model.

calculate_revolution_number_at

Calculate the revolution number of the Tabulated model at a given instant.

calculate_state_at

Calculate the state of the Tabulated model at a given instant.

calculate_states_at

Calculate the states of the Tabulated model at given instants.

get_epoch

Get the epoch of the Tabulated model.

get_interpolation_type

Get the interpolation type of the Tabulated model.

get_interval

Get the interval of the Tabulated model.

get_revolution_number_at_epoch

Get the revolution number at the epoch of the Tabulated model.

is_defined

Check if the Tabulated model is defined.

is_kepler

Check if the orbit model is a Kepler model.

is_propagated

Check if the orbit model is a propagated model.

is_sgp4

Check if the orbit model is an SGP4 model.

as_kepler(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Kepler

Cast the orbit model to a Kepler model.

Returns:

The Kepler model.

Return type:

Kepler

as_propagated(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::Propagated

Cast the orbit model to a propagated model.

Returns:

The propagated model.

Return type:

Propagated

as_sgp4(
self: ostk.astrodynamics.trajectory.orbit.OrbitModel,
) → ostk::astrodynamics::trajectory::orbit::model::SGP4

Cast the orbit model to an SGP4 model.

Returns:

The SGP4 model.

Return type:

SGP4

calculate_revolution_number_at(
self: ostk.astrodynamics.trajectory.orbit.model.Tabulated,
instant: ostk.physics.time.Instant,
) → ostk.core.type.Integer

Calculate the revolution number of the Tabulated model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The revolution number.

Return type:

int

calculate_state_at(
self: ostk.astrodynamics.trajectory.orbit.model.Tabulated,
instant: ostk.physics.time.Instant,
) → ostk.astrodynamics.trajectory.State

Calculate the state of the Tabulated model at a given instant.

Parameters:

instant (Instant) -- The instant.

Returns:

The state.

Return type:

State

calculate_states_at(
self: ostk.astrodynamics.trajectory.orbit.model.Tabulated,
instants: List[ostk.physics.time.Instant],
) → List[ostk.astrodynamics.trajectory.State]

Calculate the states of the Tabulated model at given instants.

Parameters:

instants (list[Instant]) -- The instants.

Returns:

The states.

Return type:

list[State]

get_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.Tabulated,
) → ostk.physics.time.Instant

Get the epoch of the Tabulated model.

Returns:

The epoch.

Return type:

Instant

get_interpolation_type(
self: ostk.astrodynamics.trajectory.orbit.model.Tabulated,
) → ostk.mathematics.curve_fitting.Interpolator.Type

Get the interpolation type of the Tabulated model.

Returns:

The interpolation type.

Return type:

Interpolator.Type

get_interval(
self: ostk.astrodynamics.trajectory.orbit.model.Tabulated,
) → ostk.physics.time.Interval

Get the interval of the Tabulated model.

Returns:

The interval.

Return type:

Interval

get_revolution_number_at_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.Tabulated,
) → ostk.core.type.Integer

Get the revolution number at the epoch of the Tabulated model.

Returns:

The revolution number.

Return type:

int

is_defined(self: ostk.astrodynamics.trajectory.orbit.model.Tabulated) → bool

Check if the Tabulated model is defined.

Returns:

True if the Tabulated model is defined, False otherwise.

Return type:

bool

is_kepler(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a Kepler model.

Returns:

True if the orbit model is a Kepler model, False otherwise.

Return type:

bool

is_propagated(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is a propagated model.

Returns:

True if the orbit model is a propagated model, False otherwise.

Return type:

bool

is_sgp4(self: ostk.astrodynamics.trajectory.orbit.OrbitModel) → bool

Check if the orbit model is an SGP4 model.

Returns:

True if the orbit model is an SGP4 model, False otherwise.

Return type:

bool

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.html index 41b1ef3bf..225010f18 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong

class BrouwerLyddaneMeanLong(
self: ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong,
semi_major_axis: ostk.physics.unit.Length,
eccentricity: ostk.core.type.Real,
inclination: ostk.physics.unit.Angle,
raan: ostk.physics.unit.Angle,
aop: ostk.physics.unit.Angle,
mean_anomaly: ostk.physics.unit.Angle,
)

Bases: BrouwerLyddaneMean

Brouwer-Lyddane Mean (Long) orbit elements. Short periodic variations and secular variations are averaged.

Constructor.

Parameters:

  • semi_major_axis (Length) -- The semi-major axis.

  • eccentricity (float) -- The eccentricity.

  • inclination (Angle) -- The inclination.

  • raan (Angle) -- The right ascension of the ascending node.

  • aop (Angle) -- The argument of periapsis.

  • mean_anomaly (Angle) -- The mean anomaly.

Methods

COE

Create a BrouwerLyddaneMeanLong model from classical orbital elements.

cartesian

Create a BrouwerLyddaneMeanLong model from Cartesian state.

compute_angular_momentum

Overloaded function.

compute_radial_distance

Compute the radial distance from the semi-latus rectum and the eccentricity.

compute_semi_latus_rectum

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

eccentric_anomaly_from_mean_anomaly

Compute the eccentric anomaly from the mean anomaly.

eccentric_anomaly_from_true_anomaly

Compute the eccentric anomaly from the true anomaly.

from_SI_vector

Create a COE model from a state vector in SI units.

get_SI_vector

Get the state vector of the COE in the specified anomaly type.

get_angular_momentum

Get the angular momentum of the COE.

get_aop

Get the argument of periapsis of the COE.

get_apoapsis_radius

Get the apoapsis radius of the COE.

get_cartesian_state

Get the Cartesian state of the BrouwerLyddaneMean model.

get_eccentric_anomaly

Get the eccentric anomaly of the BrouwerLyddaneMean model.

get_eccentricity

Get the eccentricity of the COE.

get_inclination

Get the inclination of the COE.

get_mean_anomaly

Get the mean anomaly of the BrouwerLyddaneMean model.

get_mean_motion

Get the mean motion of the COE.

get_nodal_precession_rate

Get the nodal precession of the COE.

get_orbital_period

Get the orbital period of the COE.

get_periapsis_radius

Get the periapsis radius of the COE.

get_raan

Get the right ascension of the ascending node of the COE.

get_radial_distance

Get the radial distance of the COE.

get_semi_latus_rectum

Get the semi-latus rectum of the COE.

get_semi_major_axis

Get the semi-major axis of the COE.

get_true_anomaly

Get the true anomaly of the BrouwerLyddaneMean model.

is_defined

Check if the COE is defined.

mean_anomaly_from_eccentric_anomaly

Compute the mean anomaly from the eccentric anomaly.

string_from_element

Get the string representation of an element.

to_coe

Convert the BrouwerLyddaneMeanLong model to classical orbital elements.

true_anomaly_from_eccentric_anomaly

Compute the true anomaly from the eccentric anomaly.

true_anomaly_from_mean_anomaly

Compute the true anomaly from the mean anomaly.

undefined

Create an undefined BrouwerLyddaneMeanLong model.

class AnomalyType(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
value: int,
)

Bases: pybind11_object

The type of Anomaly.

Members:

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
static COE(
coe: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong

Create a BrouwerLyddaneMeanLong model from classical orbital elements.

Parameters:

coe (COE) -- The classical orbital elements.

Returns:

The BrouwerLyddaneMeanLong model.

Return type:

BrouwerLyddaneMeanLong

class Element(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
value: int,
)

Bases: pybind11_object

Classical Orbital Element enumeration.

Members:

SemiMajorAxis : Semi-Major Axis

Eccentricity : Eccentricity

Inclination : Inclination

Aop : Argument of Perigee

Raan : Right Angle of the Ascending Node

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
static cartesian(
cartesian_state: Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity],
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong

Create a BrouwerLyddaneMeanLong model from Cartesian state.

Parameters:

  • cartesian_state (CartesianState) -- The Cartesian state.

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

Returns:

The BrouwerLyddaneMeanLong model.

Return type:

BrouwerLyddaneMeanLong

static compute_angular_momentum(*args, **kwargs)

Overloaded function.

  1. compute_angular_momentum(semi_major_axis: ostk.core.type.Real, eccentricity: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-major axis and the eccentricity.

    Args:

    semi_major_axis (float): The semi-major axis. In meters. eccentricity (float): The eccentricity. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

  2. compute_angular_momentum(semi_latus_rectum: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-latus rectum.

    Args:

    semi_latus_rectum (float): The semi-latus rectum. In meters. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

static compute_radial_distance(
semi_latus_rectum: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
true_anomaly: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the radial distance from the semi-latus rectum and the eccentricity.

Parameters:

  • semi_latus_rectum (float) -- The semi-latus rectum. In meters.

  • eccentricity (float) -- The eccentricity.

  • true_anomaly (float) -- The true anomly. In degrees.

Returns:

The radial distance.

Return type:

Length

static compute_semi_latus_rectum(
semi_major_axis: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

Parameters:

  • semi_major_axis (float) -- The semi-major axis. In meters.

  • eccentricity (float) -- The eccentricity.

Returns:

The semi-latus rectum.

Return type:

Length

static eccentric_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The eccentric anomaly.

Return type:

Angle

static eccentric_anomaly_from_true_anomaly(
true_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the true anomaly.

Parameters:

  • true_anomaly (Angle) -- The true anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The eccentric anomaly.

Return type:

Angle

static from_SI_vector(
vector: numpy.ndarray[numpy.float64[6, 1]],
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create a COE model from a state vector in SI units.

Parameters:

  • vector (Vector6d) -- The state vector.

  • anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The COE model.

Return type:

COE

get_SI_vector(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → numpy.ndarray[numpy.float64[6, 1]]

Get the state vector of the COE in the specified anomaly type.

Parameters:

anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The state vector of the COE in the specified anomaly type.

Return type:

numpy.ndarray

get_angular_momentum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
arg0: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the angular momentum of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The angular momentum of the COE.

Return type:

Derived

get_aop(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the argument of periapsis of the COE.

Returns:

The argument of periapsis of the COE.

Return type:

Angle

get_apoapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the apoapsis radius of the COE.

Returns:

The apoapsis radius of the COE.

Return type:

Length

get_cartesian_state(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
gravitational_parameter: ostk.physics.unit.Derived,
frame: ostk.physics.coordinate.Frame,
) → Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity]

Get the Cartesian state of the BrouwerLyddaneMean model.

Parameters:

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

  • frame (str) -- The reference frame in which the state is expressed.

Returns:

The Cartesian state.

Return type:

CartesianState

get_eccentric_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the eccentric anomaly of the BrouwerLyddaneMean model.

Returns:

The eccentric anomaly.

Return type:

Angle

get_eccentricity(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.core.type.Real

Get the eccentricity of the COE.

Returns:

The eccentricity of the COE.

Return type:

float

get_inclination(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the inclination of the COE.

Returns:

The inclination of the COE.

Return type:

Angle

get_mean_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the mean anomaly of the BrouwerLyddaneMean model.

Returns:

The mean anomaly.

Return type:

Angle

get_mean_motion(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the mean motion of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The mean motion of the COE.

Return type:

Derived

get_nodal_precession_rate(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
equatorial_radius: ostk.physics.unit.Length,
j2: ostk.core.type.Real,
) → ostk.physics.unit.Derived

Get the nodal precession of the COE.

Parameters:

  • gravitational_parameter (Derived) -- The gravitational parameter of the central body.

  • equatorial_radius (Length) -- The equatorial radius of the central body.

  • j2 (float) -- The second zonal harmonic coefficient of the central body.

Returns:

The nodal precession of the COE.

Return type:

Derived

get_orbital_period(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.time.Duration

Get the orbital period of the COE.

Parameters:

gravitational_parameter (double) -- The gravitational parameter of the central body.

Returns:

The orbital period of the COE.

Return type:

Duration

get_periapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the periapsis radius of the COE.

Returns:

The periapsis radius of the COE.

Return type:

Length

get_raan(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the right ascension of the ascending node of the COE.

Returns:

The right ascension of the ascending node of the COE.

Return type:

Angle

get_radial_distance(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the radial distance of the COE.

Returns:

The radial distance of the COE.

Return type:

Length

get_semi_latus_rectum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-latus rectum of the COE.

Returns:

The semilatus rectum of the COE.

Return type:

Length

get_semi_major_axis(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-major axis of the COE.

Returns:

The semi-major axis of the COE.

Return type:

Length

get_true_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the true anomaly of the BrouwerLyddaneMean model.

Returns:

The true anomaly.

Return type:

Angle

is_defined(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → bool

Check if the COE is defined.

Returns:

True if the COE is defined, False otherwise.

Return type:

bool

static mean_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the mean anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The mean anomaly.

Return type:

Angle

static string_from_element(
element: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
) → ostk.core.type.String

Get the string representation of an element.

Parameters:

element (Element) -- The element.

Returns:

The string representation.

Return type:

str

to_coe(
self: ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Convert the BrouwerLyddaneMeanLong model to classical orbital elements.

Returns:

The classical orbital elements.

Return type:

COE

static true_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The true anomaly.

Return type:

Angle

static true_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The true anomaly.

Return type:

Angle

static undefined() → ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong

Create an undefined BrouwerLyddaneMeanLong model.

Returns:

The undefined BrouwerLyddaneMeanLong model.

Return type:

BrouwerLyddaneMeanLong

\ No newline at end of file + ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong

class BrouwerLyddaneMeanLong(
self: ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong,
semi_major_axis: ostk.physics.unit.Length,
eccentricity: ostk.core.type.Real,
inclination: ostk.physics.unit.Angle,
raan: ostk.physics.unit.Angle,
aop: ostk.physics.unit.Angle,
mean_anomaly: ostk.physics.unit.Angle,
)

Bases: BrouwerLyddaneMean

Brouwer-Lyddane Mean (Long) orbit elements. Short periodic variations and secular variations are averaged.

Constructor.

Parameters:

  • semi_major_axis (Length) -- The semi-major axis.

  • eccentricity (float) -- The eccentricity.

  • inclination (Angle) -- The inclination.

  • raan (Angle) -- The right ascension of the ascending node.

  • aop (Angle) -- The argument of periapsis.

  • mean_anomaly (Angle) -- The mean anomaly.

Methods

COE

Create a BrouwerLyddaneMeanLong model from classical orbital elements.

cartesian

Create a BrouwerLyddaneMeanLong model from Cartesian state.

compute_angular_momentum

Overloaded function.

compute_radial_distance

Compute the radial distance from the semi-latus rectum and the eccentricity.

compute_semi_latus_rectum

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

eccentric_anomaly_from_mean_anomaly

Compute the eccentric anomaly from the mean anomaly.

eccentric_anomaly_from_true_anomaly

Compute the eccentric anomaly from the true anomaly.

from_SI_vector

Create a COE model from a state vector in SI units.

get_SI_vector

Get the state vector of the COE in the specified anomaly type.

get_angular_momentum

Get the angular momentum of the COE.

get_aop

Get the argument of periapsis of the COE.

get_apoapsis_radius

Get the apoapsis radius of the COE.

get_cartesian_state

Get the Cartesian state of the BrouwerLyddaneMean model.

get_eccentric_anomaly

Get the eccentric anomaly of the BrouwerLyddaneMean model.

get_eccentricity

Get the eccentricity of the COE.

get_inclination

Get the inclination of the COE.

get_mean_anomaly

Get the mean anomaly of the BrouwerLyddaneMean model.

get_mean_motion

Get the mean motion of the COE.

get_nodal_precession_rate

Get the nodal precession of the COE.

get_orbital_period

Get the orbital period of the COE.

get_periapsis_radius

Get the periapsis radius of the COE.

get_raan

Get the right ascension of the ascending node of the COE.

get_radial_distance

Get the radial distance of the COE.

get_semi_latus_rectum

Get the semi-latus rectum of the COE.

get_semi_major_axis

Get the semi-major axis of the COE.

get_true_anomaly

Get the true anomaly of the BrouwerLyddaneMean model.

is_defined

Check if the COE is defined.

mean_anomaly_from_eccentric_anomaly

Compute the mean anomaly from the eccentric anomaly.

string_from_element

Get the string representation of an element.

to_coe

Convert the BrouwerLyddaneMeanLong model to classical orbital elements.

true_anomaly_from_eccentric_anomaly

Compute the true anomaly from the eccentric anomaly.

true_anomaly_from_mean_anomaly

Compute the true anomaly from the mean anomaly.

undefined

Create an undefined BrouwerLyddaneMeanLong model.

class AnomalyType(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
value: int,
)

Bases: pybind11_object

The type of Anomaly.

Members:

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
static COE(
coe: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong

Create a BrouwerLyddaneMeanLong model from classical orbital elements.

Parameters:

coe (COE) -- The classical orbital elements.

Returns:

The BrouwerLyddaneMeanLong model.

Return type:

BrouwerLyddaneMeanLong

class Element(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
value: int,
)

Bases: pybind11_object

Classical Orbital Element enumeration.

Members:

SemiMajorAxis : Semi-Major Axis

Eccentricity : Eccentricity

Inclination : Inclination

Aop : Argument of Perigee

Raan : Right Angle of the Ascending Node

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
static cartesian(
cartesian_state: Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity],
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong

Create a BrouwerLyddaneMeanLong model from Cartesian state.

Parameters:

  • cartesian_state (CartesianState) -- The Cartesian state.

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

Returns:

The BrouwerLyddaneMeanLong model.

Return type:

BrouwerLyddaneMeanLong

static compute_angular_momentum(*args, **kwargs)

Overloaded function.

  1. compute_angular_momentum(semi_major_axis: ostk.core.type.Real, eccentricity: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-major axis and the eccentricity.

    Args:

    semi_major_axis (float): The semi-major axis. In meters. eccentricity (float): The eccentricity. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

  2. compute_angular_momentum(semi_latus_rectum: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-latus rectum.

    Args:

    semi_latus_rectum (float): The semi-latus rectum. In meters. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

static compute_radial_distance(
semi_latus_rectum: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
true_anomaly: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the radial distance from the semi-latus rectum and the eccentricity.

Parameters:

  • semi_latus_rectum (float) -- The semi-latus rectum. In meters.

  • eccentricity (float) -- The eccentricity.

  • true_anomaly (float) -- The true anomly. In degrees.

Returns:

The radial distance.

Return type:

Length

static compute_semi_latus_rectum(
semi_major_axis: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

Parameters:

  • semi_major_axis (float) -- The semi-major axis. In meters.

  • eccentricity (float) -- The eccentricity.

Returns:

The semi-latus rectum.

Return type:

Length

static eccentric_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The eccentric anomaly.

Return type:

Angle

static eccentric_anomaly_from_true_anomaly(
true_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the true anomaly.

Parameters:

  • true_anomaly (Angle) -- The true anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The eccentric anomaly.

Return type:

Angle

static from_SI_vector(
vector: numpy.ndarray[numpy.float64[6, 1]],
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create a COE model from a state vector in SI units.

Parameters:

  • vector (Vector6d) -- The state vector.

  • anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The COE model.

Return type:

COE

get_SI_vector(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → numpy.ndarray[numpy.float64[6, 1]]

Get the state vector of the COE in the specified anomaly type.

Parameters:

anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The state vector of the COE in the specified anomaly type.

Return type:

numpy.ndarray

get_angular_momentum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
arg0: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the angular momentum of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The angular momentum of the COE.

Return type:

Derived

get_aop(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the argument of periapsis of the COE.

Returns:

The argument of periapsis of the COE.

Return type:

Angle

get_apoapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the apoapsis radius of the COE.

Returns:

The apoapsis radius of the COE.

Return type:

Length

get_cartesian_state(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
gravitational_parameter: ostk.physics.unit.Derived,
frame: ostk.physics.coordinate.Frame,
) → Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity]

Get the Cartesian state of the BrouwerLyddaneMean model.

Parameters:

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

  • frame (str) -- The reference frame in which the state is expressed.

Returns:

The Cartesian state.

Return type:

CartesianState

get_eccentric_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the eccentric anomaly of the BrouwerLyddaneMean model.

Returns:

The eccentric anomaly.

Return type:

Angle

get_eccentricity(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.core.type.Real

Get the eccentricity of the COE.

Returns:

The eccentricity of the COE.

Return type:

float

get_inclination(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the inclination of the COE.

Returns:

The inclination of the COE.

Return type:

Angle

get_mean_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the mean anomaly of the BrouwerLyddaneMean model.

Returns:

The mean anomaly.

Return type:

Angle

get_mean_motion(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the mean motion of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The mean motion of the COE.

Return type:

Derived

get_nodal_precession_rate(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
equatorial_radius: ostk.physics.unit.Length,
j2: ostk.core.type.Real,
) → ostk.physics.unit.Derived

Get the nodal precession of the COE.

Parameters:

  • gravitational_parameter (Derived) -- The gravitational parameter of the central body.

  • equatorial_radius (Length) -- The equatorial radius of the central body.

  • j2 (float) -- The second zonal harmonic coefficient of the central body.

Returns:

The nodal precession of the COE.

Return type:

Derived

get_orbital_period(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.time.Duration

Get the orbital period of the COE.

Parameters:

gravitational_parameter (double) -- The gravitational parameter of the central body.

Returns:

The orbital period of the COE.

Return type:

Duration

get_periapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the periapsis radius of the COE.

Returns:

The periapsis radius of the COE.

Return type:

Length

get_raan(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the right ascension of the ascending node of the COE.

Returns:

The right ascension of the ascending node of the COE.

Return type:

Angle

get_radial_distance(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the radial distance of the COE.

Returns:

The radial distance of the COE.

Return type:

Length

get_semi_latus_rectum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-latus rectum of the COE.

Returns:

The semilatus rectum of the COE.

Return type:

Length

get_semi_major_axis(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-major axis of the COE.

Returns:

The semi-major axis of the COE.

Return type:

Length

get_true_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the true anomaly of the BrouwerLyddaneMean model.

Returns:

The true anomaly.

Return type:

Angle

is_defined(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → bool

Check if the COE is defined.

Returns:

True if the COE is defined, False otherwise.

Return type:

bool

static mean_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the mean anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The mean anomaly.

Return type:

Angle

static string_from_element(
element: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
) → ostk.core.type.String

Get the string representation of an element.

Parameters:

element (Element) -- The element.

Returns:

The string representation.

Return type:

str

to_coe(
self: ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Convert the BrouwerLyddaneMeanLong model to classical orbital elements.

Returns:

The classical orbital elements.

Return type:

COE

static true_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The true anomaly.

Return type:

Angle

static true_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The true anomaly.

Return type:

Angle

static undefined() → ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong

Create an undefined BrouwerLyddaneMeanLong model.

Returns:

The undefined BrouwerLyddaneMeanLong model.

Return type:

BrouwerLyddaneMeanLong

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.html index 611f763d7..db986ae3d 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort

class BrouwerLyddaneMeanShort(
self: ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort,
semi_major_axis: ostk.physics.unit.Length,
eccentricity: ostk.core.type.Real,
inclination: ostk.physics.unit.Angle,
raan: ostk.physics.unit.Angle,
aop: ostk.physics.unit.Angle,
mean_anomaly: ostk.physics.unit.Angle,
)

Bases: BrouwerLyddaneMean

Brouwer-Lyddane Mean (Short) orbit elements. Short periodic variations are averaged.

Constructor.

Parameters:

  • semi_major_axis (Length) -- The semi-major axis.

  • eccentricity (float) -- The eccentricity.

  • inclination (Angle) -- The inclination.

  • raan (Angle) -- The right ascension of the ascending node.

  • aop (Angle) -- The argument of periapsis.

  • mean_anomaly (Angle) -- The mean anomaly.

Methods

COE

Create a BrouwerLyddaneMeanShort model from classical orbital elements.

cartesian

Create a BrouwerLyddaneMeanShort model from Cartesian state.

compute_angular_momentum

Overloaded function.

compute_radial_distance

Compute the radial distance from the semi-latus rectum and the eccentricity.

compute_semi_latus_rectum

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

eccentric_anomaly_from_mean_anomaly

Compute the eccentric anomaly from the mean anomaly.

eccentric_anomaly_from_true_anomaly

Compute the eccentric anomaly from the true anomaly.

from_SI_vector

Create a COE model from a state vector in SI units.

get_SI_vector

Get the state vector of the COE in the specified anomaly type.

get_angular_momentum

Get the angular momentum of the COE.

get_aop

Get the argument of periapsis of the COE.

get_apoapsis_radius

Get the apoapsis radius of the COE.

get_cartesian_state

Get the Cartesian state of the BrouwerLyddaneMean model.

get_eccentric_anomaly

Get the eccentric anomaly of the BrouwerLyddaneMean model.

get_eccentricity

Get the eccentricity of the COE.

get_inclination

Get the inclination of the COE.

get_mean_anomaly

Get the mean anomaly of the BrouwerLyddaneMean model.

get_mean_motion

Get the mean motion of the COE.

get_nodal_precession_rate

Get the nodal precession of the COE.

get_orbital_period

Get the orbital period of the COE.

get_periapsis_radius

Get the periapsis radius of the COE.

get_raan

Get the right ascension of the ascending node of the COE.

get_radial_distance

Get the radial distance of the COE.

get_semi_latus_rectum

Get the semi-latus rectum of the COE.

get_semi_major_axis

Get the semi-major axis of the COE.

get_true_anomaly

Get the true anomaly of the BrouwerLyddaneMean model.

is_defined

Check if the COE is defined.

mean_anomaly_from_eccentric_anomaly

Compute the mean anomaly from the eccentric anomaly.

string_from_element

Get the string representation of an element.

to_coe

Convert the BrouwerLyddaneMeanShort model to classical orbital elements.

true_anomaly_from_eccentric_anomaly

Compute the true anomaly from the eccentric anomaly.

true_anomaly_from_mean_anomaly

Compute the true anomaly from the mean anomaly.

undefined

Create an undefined BrouwerLyddaneMeanShort model.

class AnomalyType(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
value: int,
)

Bases: pybind11_object

The type of Anomaly.

Members:

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
static COE(
coe: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort

Create a BrouwerLyddaneMeanShort model from classical orbital elements.

Parameters:

coe (COE) -- The classical orbital elements.

Returns:

The BrouwerLyddaneMeanShort model.

Return type:

BrouwerLyddaneMeanShort

class Element(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
value: int,
)

Bases: pybind11_object

Classical Orbital Element enumeration.

Members:

SemiMajorAxis : Semi-Major Axis

Eccentricity : Eccentricity

Inclination : Inclination

Aop : Argument of Perigee

Raan : Right Angle of the Ascending Node

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
static cartesian(
cartesian_state: Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity],
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort

Create a BrouwerLyddaneMeanShort model from Cartesian state.

Parameters:

  • cartesian_state (CartesianState) -- The Cartesian state.

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

Returns:

The BrouwerLyddaneMeanShort model.

Return type:

BrouwerLyddaneMeanShort

static compute_angular_momentum(*args, **kwargs)

Overloaded function.

  1. compute_angular_momentum(semi_major_axis: ostk.core.type.Real, eccentricity: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-major axis and the eccentricity.

    Args:

    semi_major_axis (float): The semi-major axis. In meters. eccentricity (float): The eccentricity. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

  2. compute_angular_momentum(semi_latus_rectum: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-latus rectum.

    Args:

    semi_latus_rectum (float): The semi-latus rectum. In meters. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

static compute_radial_distance(
semi_latus_rectum: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
true_anomaly: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the radial distance from the semi-latus rectum and the eccentricity.

Parameters:

  • semi_latus_rectum (float) -- The semi-latus rectum. In meters.

  • eccentricity (float) -- The eccentricity.

  • true_anomaly (float) -- The true anomly. In degrees.

Returns:

The radial distance.

Return type:

Length

static compute_semi_latus_rectum(
semi_major_axis: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

Parameters:

  • semi_major_axis (float) -- The semi-major axis. In meters.

  • eccentricity (float) -- The eccentricity.

Returns:

The semi-latus rectum.

Return type:

Length

static eccentric_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The eccentric anomaly.

Return type:

Angle

static eccentric_anomaly_from_true_anomaly(
true_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the true anomaly.

Parameters:

  • true_anomaly (Angle) -- The true anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The eccentric anomaly.

Return type:

Angle

static from_SI_vector(
vector: numpy.ndarray[numpy.float64[6, 1]],
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create a COE model from a state vector in SI units.

Parameters:

  • vector (Vector6d) -- The state vector.

  • anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The COE model.

Return type:

COE

get_SI_vector(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → numpy.ndarray[numpy.float64[6, 1]]

Get the state vector of the COE in the specified anomaly type.

Parameters:

anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The state vector of the COE in the specified anomaly type.

Return type:

numpy.ndarray

get_angular_momentum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
arg0: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the angular momentum of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The angular momentum of the COE.

Return type:

Derived

get_aop(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the argument of periapsis of the COE.

Returns:

The argument of periapsis of the COE.

Return type:

Angle

get_apoapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the apoapsis radius of the COE.

Returns:

The apoapsis radius of the COE.

Return type:

Length

get_cartesian_state(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
gravitational_parameter: ostk.physics.unit.Derived,
frame: ostk.physics.coordinate.Frame,
) → Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity]

Get the Cartesian state of the BrouwerLyddaneMean model.

Parameters:

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

  • frame (str) -- The reference frame in which the state is expressed.

Returns:

The Cartesian state.

Return type:

CartesianState

get_eccentric_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the eccentric anomaly of the BrouwerLyddaneMean model.

Returns:

The eccentric anomaly.

Return type:

Angle

get_eccentricity(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.core.type.Real

Get the eccentricity of the COE.

Returns:

The eccentricity of the COE.

Return type:

float

get_inclination(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the inclination of the COE.

Returns:

The inclination of the COE.

Return type:

Angle

get_mean_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the mean anomaly of the BrouwerLyddaneMean model.

Returns:

The mean anomaly.

Return type:

Angle

get_mean_motion(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the mean motion of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The mean motion of the COE.

Return type:

Derived

get_nodal_precession_rate(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
equatorial_radius: ostk.physics.unit.Length,
j2: ostk.core.type.Real,
) → ostk.physics.unit.Derived

Get the nodal precession of the COE.

Parameters:

  • gravitational_parameter (Derived) -- The gravitational parameter of the central body.

  • equatorial_radius (Length) -- The equatorial radius of the central body.

  • j2 (float) -- The second zonal harmonic coefficient of the central body.

Returns:

The nodal precession of the COE.

Return type:

Derived

get_orbital_period(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.time.Duration

Get the orbital period of the COE.

Parameters:

gravitational_parameter (double) -- The gravitational parameter of the central body.

Returns:

The orbital period of the COE.

Return type:

Duration

get_periapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the periapsis radius of the COE.

Returns:

The periapsis radius of the COE.

Return type:

Length

get_raan(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the right ascension of the ascending node of the COE.

Returns:

The right ascension of the ascending node of the COE.

Return type:

Angle

get_radial_distance(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the radial distance of the COE.

Returns:

The radial distance of the COE.

Return type:

Length

get_semi_latus_rectum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-latus rectum of the COE.

Returns:

The semilatus rectum of the COE.

Return type:

Length

get_semi_major_axis(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-major axis of the COE.

Returns:

The semi-major axis of the COE.

Return type:

Length

get_true_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the true anomaly of the BrouwerLyddaneMean model.

Returns:

The true anomaly.

Return type:

Angle

is_defined(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → bool

Check if the COE is defined.

Returns:

True if the COE is defined, False otherwise.

Return type:

bool

static mean_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the mean anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The mean anomaly.

Return type:

Angle

static string_from_element(
element: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
) → ostk.core.type.String

Get the string representation of an element.

Parameters:

element (Element) -- The element.

Returns:

The string representation.

Return type:

str

to_coe(
self: ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Convert the BrouwerLyddaneMeanShort model to classical orbital elements.

Returns:

The classical orbital elements.

Return type:

COE

static true_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The true anomaly.

Return type:

Angle

static true_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The true anomaly.

Return type:

Angle

static undefined() → ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort

Create an undefined BrouwerLyddaneMeanShort model.

Returns:

The undefined BrouwerLyddaneMeanShort model.

Return type:

BrouwerLyddaneMeanShort

\ No newline at end of file + ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort

class BrouwerLyddaneMeanShort(
self: ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort,
semi_major_axis: ostk.physics.unit.Length,
eccentricity: ostk.core.type.Real,
inclination: ostk.physics.unit.Angle,
raan: ostk.physics.unit.Angle,
aop: ostk.physics.unit.Angle,
mean_anomaly: ostk.physics.unit.Angle,
)

Bases: BrouwerLyddaneMean

Brouwer-Lyddane Mean (Short) orbit elements. Short periodic variations are averaged.

Constructor.

Parameters:

  • semi_major_axis (Length) -- The semi-major axis.

  • eccentricity (float) -- The eccentricity.

  • inclination (Angle) -- The inclination.

  • raan (Angle) -- The right ascension of the ascending node.

  • aop (Angle) -- The argument of periapsis.

  • mean_anomaly (Angle) -- The mean anomaly.

Methods

COE

Create a BrouwerLyddaneMeanShort model from classical orbital elements.

cartesian

Create a BrouwerLyddaneMeanShort model from Cartesian state.

compute_angular_momentum

Overloaded function.

compute_radial_distance

Compute the radial distance from the semi-latus rectum and the eccentricity.

compute_semi_latus_rectum

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

eccentric_anomaly_from_mean_anomaly

Compute the eccentric anomaly from the mean anomaly.

eccentric_anomaly_from_true_anomaly

Compute the eccentric anomaly from the true anomaly.

from_SI_vector

Create a COE model from a state vector in SI units.

get_SI_vector

Get the state vector of the COE in the specified anomaly type.

get_angular_momentum

Get the angular momentum of the COE.

get_aop

Get the argument of periapsis of the COE.

get_apoapsis_radius

Get the apoapsis radius of the COE.

get_cartesian_state

Get the Cartesian state of the BrouwerLyddaneMean model.

get_eccentric_anomaly

Get the eccentric anomaly of the BrouwerLyddaneMean model.

get_eccentricity

Get the eccentricity of the COE.

get_inclination

Get the inclination of the COE.

get_mean_anomaly

Get the mean anomaly of the BrouwerLyddaneMean model.

get_mean_motion

Get the mean motion of the COE.

get_nodal_precession_rate

Get the nodal precession of the COE.

get_orbital_period

Get the orbital period of the COE.

get_periapsis_radius

Get the periapsis radius of the COE.

get_raan

Get the right ascension of the ascending node of the COE.

get_radial_distance

Get the radial distance of the COE.

get_semi_latus_rectum

Get the semi-latus rectum of the COE.

get_semi_major_axis

Get the semi-major axis of the COE.

get_true_anomaly

Get the true anomaly of the BrouwerLyddaneMean model.

is_defined

Check if the COE is defined.

mean_anomaly_from_eccentric_anomaly

Compute the mean anomaly from the eccentric anomaly.

string_from_element

Get the string representation of an element.

to_coe

Convert the BrouwerLyddaneMeanShort model to classical orbital elements.

true_anomaly_from_eccentric_anomaly

Compute the true anomaly from the eccentric anomaly.

true_anomaly_from_mean_anomaly

Compute the true anomaly from the mean anomaly.

undefined

Create an undefined BrouwerLyddaneMeanShort model.

class AnomalyType(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
value: int,
)

Bases: pybind11_object

The type of Anomaly.

Members:

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
static COE(
coe: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort

Create a BrouwerLyddaneMeanShort model from classical orbital elements.

Parameters:

coe (COE) -- The classical orbital elements.

Returns:

The BrouwerLyddaneMeanShort model.

Return type:

BrouwerLyddaneMeanShort

class Element(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
value: int,
)

Bases: pybind11_object

Classical Orbital Element enumeration.

Members:

SemiMajorAxis : Semi-Major Axis

Eccentricity : Eccentricity

Inclination : Inclination

Aop : Argument of Perigee

Raan : Right Angle of the Ascending Node

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
static cartesian(
cartesian_state: Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity],
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort

Create a BrouwerLyddaneMeanShort model from Cartesian state.

Parameters:

  • cartesian_state (CartesianState) -- The Cartesian state.

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

Returns:

The BrouwerLyddaneMeanShort model.

Return type:

BrouwerLyddaneMeanShort

static compute_angular_momentum(*args, **kwargs)

Overloaded function.

  1. compute_angular_momentum(semi_major_axis: ostk.core.type.Real, eccentricity: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-major axis and the eccentricity.

    Args:

    semi_major_axis (float): The semi-major axis. In meters. eccentricity (float): The eccentricity. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

  2. compute_angular_momentum(semi_latus_rectum: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-latus rectum.

    Args:

    semi_latus_rectum (float): The semi-latus rectum. In meters. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

static compute_radial_distance(
semi_latus_rectum: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
true_anomaly: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the radial distance from the semi-latus rectum and the eccentricity.

Parameters:

  • semi_latus_rectum (float) -- The semi-latus rectum. In meters.

  • eccentricity (float) -- The eccentricity.

  • true_anomaly (float) -- The true anomly. In degrees.

Returns:

The radial distance.

Return type:

Length

static compute_semi_latus_rectum(
semi_major_axis: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

Parameters:

  • semi_major_axis (float) -- The semi-major axis. In meters.

  • eccentricity (float) -- The eccentricity.

Returns:

The semi-latus rectum.

Return type:

Length

static eccentric_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The eccentric anomaly.

Return type:

Angle

static eccentric_anomaly_from_true_anomaly(
true_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the true anomaly.

Parameters:

  • true_anomaly (Angle) -- The true anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The eccentric anomaly.

Return type:

Angle

static from_SI_vector(
vector: numpy.ndarray[numpy.float64[6, 1]],
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create a COE model from a state vector in SI units.

Parameters:

  • vector (Vector6d) -- The state vector.

  • anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The COE model.

Return type:

COE

get_SI_vector(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → numpy.ndarray[numpy.float64[6, 1]]

Get the state vector of the COE in the specified anomaly type.

Parameters:

anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The state vector of the COE in the specified anomaly type.

Return type:

numpy.ndarray

get_angular_momentum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
arg0: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the angular momentum of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The angular momentum of the COE.

Return type:

Derived

get_aop(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the argument of periapsis of the COE.

Returns:

The argument of periapsis of the COE.

Return type:

Angle

get_apoapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the apoapsis radius of the COE.

Returns:

The apoapsis radius of the COE.

Return type:

Length

get_cartesian_state(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
gravitational_parameter: ostk.physics.unit.Derived,
frame: ostk.physics.coordinate.Frame,
) → Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity]

Get the Cartesian state of the BrouwerLyddaneMean model.

Parameters:

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

  • frame (str) -- The reference frame in which the state is expressed.

Returns:

The Cartesian state.

Return type:

CartesianState

get_eccentric_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the eccentric anomaly of the BrouwerLyddaneMean model.

Returns:

The eccentric anomaly.

Return type:

Angle

get_eccentricity(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.core.type.Real

Get the eccentricity of the COE.

Returns:

The eccentricity of the COE.

Return type:

float

get_inclination(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the inclination of the COE.

Returns:

The inclination of the COE.

Return type:

Angle

get_mean_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the mean anomaly of the BrouwerLyddaneMean model.

Returns:

The mean anomaly.

Return type:

Angle

get_mean_motion(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the mean motion of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The mean motion of the COE.

Return type:

Derived

get_nodal_precession_rate(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
equatorial_radius: ostk.physics.unit.Length,
j2: ostk.core.type.Real,
) → ostk.physics.unit.Derived

Get the nodal precession of the COE.

Parameters:

  • gravitational_parameter (Derived) -- The gravitational parameter of the central body.

  • equatorial_radius (Length) -- The equatorial radius of the central body.

  • j2 (float) -- The second zonal harmonic coefficient of the central body.

Returns:

The nodal precession of the COE.

Return type:

Derived

get_orbital_period(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.time.Duration

Get the orbital period of the COE.

Parameters:

gravitational_parameter (double) -- The gravitational parameter of the central body.

Returns:

The orbital period of the COE.

Return type:

Duration

get_periapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the periapsis radius of the COE.

Returns:

The periapsis radius of the COE.

Return type:

Length

get_raan(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the right ascension of the ascending node of the COE.

Returns:

The right ascension of the ascending node of the COE.

Return type:

Angle

get_radial_distance(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the radial distance of the COE.

Returns:

The radial distance of the COE.

Return type:

Length

get_semi_latus_rectum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-latus rectum of the COE.

Returns:

The semilatus rectum of the COE.

Return type:

Length

get_semi_major_axis(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-major axis of the COE.

Returns:

The semi-major axis of the COE.

Return type:

Length

get_true_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean,
) → ostk.physics.unit.Angle

Get the true anomaly of the BrouwerLyddaneMean model.

Returns:

The true anomaly.

Return type:

Angle

is_defined(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → bool

Check if the COE is defined.

Returns:

True if the COE is defined, False otherwise.

Return type:

bool

static mean_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the mean anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The mean anomaly.

Return type:

Angle

static string_from_element(
element: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
) → ostk.core.type.String

Get the string representation of an element.

Parameters:

element (Element) -- The element.

Returns:

The string representation.

Return type:

str

to_coe(
self: ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Convert the BrouwerLyddaneMeanShort model to classical orbital elements.

Returns:

The classical orbital elements.

Return type:

COE

static true_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The true anomaly.

Return type:

Angle

static true_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The true anomaly.

Return type:

Angle

static undefined() → ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort

Create an undefined BrouwerLyddaneMeanShort model.

Returns:

The undefined BrouwerLyddaneMeanShort model.

Return type:

BrouwerLyddaneMeanShort

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ostk.astrodynamics.trajectory.orbit.model.kepler.COE

class COE(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
semi_major_axis: ostk.physics.unit.Length,
eccentricity: ostk.core.type.Real,
inclination: ostk.physics.unit.Angle,
raan: ostk.physics.unit.Angle,
aop: ostk.physics.unit.Angle,
true_anomaly: ostk.physics.unit.Angle,
)

Bases: pybind11_object

Classical orbital elements.

Provides the classical orbital elements used to describe the orbit of a body around another.

\[\begin{split}\begin{aligned} a & = \text{semi-major axis} \\ e & = \text{eccentricity} \\ i & = \text{inclination} \\ \Omega & = \text{right ascension of the ascending node} \\ \omega & = \text{argument of periapsis} \\ \nu & = \text{true anomaly} \\ M & = \text{mean anomaly} \\ E & = \text{eccentric anomaly} \\ r_p & = \text{periapsis radius} \\ r_a & = \text{apoapsis radius} \end{aligned}\end{split}\]

Constructor.

Parameters:

  • semi_major_axis (Length) -- The semi-major axis.

  • eccentricity (float) -- The eccentricity.

  • inclination (Angle) -- The inclination.

  • raan (Angle) -- The right ascension of the ascending node.

  • aop (Angle) -- The argument of periapsis.

  • true_anomaly (Angle) -- The true anomaly.

Methods

cartesian

Create a COE model from Cartesian state.

compute_angular_momentum

Overloaded function.

compute_radial_distance

Compute the radial distance from the semi-latus rectum and the eccentricity.

compute_semi_latus_rectum

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

eccentric_anomaly_from_mean_anomaly

Compute the eccentric anomaly from the mean anomaly.

eccentric_anomaly_from_true_anomaly

Compute the eccentric anomaly from the true anomaly.

from_SI_vector

Create a COE model from a state vector in SI units.

get_SI_vector

Get the state vector of the COE in the specified anomaly type.

get_angular_momentum

Get the angular momentum of the COE.

get_aop

Get the argument of periapsis of the COE.

get_apoapsis_radius

Get the apoapsis radius of the COE.

get_cartesian_state

Get the Cartesian state of the COE.

get_eccentric_anomaly

Get the eccentric anomaly of the COE.

get_eccentricity

Get the eccentricity of the COE.

get_inclination

Get the inclination of the COE.

get_mean_anomaly

Get the mean anomaly of the COE.

get_mean_motion

Get the mean motion of the COE.

get_nodal_precession_rate

Get the nodal precession of the COE.

get_orbital_period

Get the orbital period of the COE.

get_periapsis_radius

Get the periapsis radius of the COE.

get_raan

Get the right ascension of the ascending node of the COE.

get_radial_distance

Get the radial distance of the COE.

get_semi_latus_rectum

Get the semi-latus rectum of the COE.

get_semi_major_axis

Get the semi-major axis of the COE.

get_true_anomaly

Get the true anomaly of the COE.

is_defined

Check if the COE is defined.

mean_anomaly_from_eccentric_anomaly

Compute the mean anomaly from the eccentric anomaly.

string_from_element

Get the string representation of an element.

true_anomaly_from_eccentric_anomaly

Compute the true anomaly from the eccentric anomaly.

true_anomaly_from_mean_anomaly

Compute the true anomaly from the mean anomaly.

undefined

Create an undefined COE model.

class AnomalyType(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
value: int,
)

Bases: pybind11_object

The type of Anomaly.

Members:

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
class Element(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
value: int,
)

Bases: pybind11_object

Classical Orbital Element enumeration.

Members:

SemiMajorAxis : Semi-Major Axis

Eccentricity : Eccentricity

Inclination : Inclination

Aop : Argument of Perigee

Raan : Right Angle of the Ascending Node

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
static cartesian(
cartesian_state: Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity],
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create a COE model from Cartesian state.

Parameters:

  • cartesian_state (CartesianState) -- The Cartesian state.

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

Returns:

The COE model.

Return type:

COE

static compute_angular_momentum(*args, **kwargs)

Overloaded function.

  1. compute_angular_momentum(semi_major_axis: ostk.core.type.Real, eccentricity: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-major axis and the eccentricity.

    Args:

    semi_major_axis (float): The semi-major axis. In meters. eccentricity (float): The eccentricity. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

  2. compute_angular_momentum(semi_latus_rectum: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-latus rectum.

    Args:

    semi_latus_rectum (float): The semi-latus rectum. In meters. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

static compute_radial_distance(
semi_latus_rectum: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
true_anomaly: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the radial distance from the semi-latus rectum and the eccentricity.

Parameters:

  • semi_latus_rectum (float) -- The semi-latus rectum. In meters.

  • eccentricity (float) -- The eccentricity.

  • true_anomaly (float) -- The true anomly. In degrees.

Returns:

The radial distance.

Return type:

Length

static compute_semi_latus_rectum(
semi_major_axis: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

Parameters:

  • semi_major_axis (float) -- The semi-major axis. In meters.

  • eccentricity (float) -- The eccentricity.

Returns:

The semi-latus rectum.

Return type:

Length

static eccentric_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The eccentric anomaly.

Return type:

Angle

static eccentric_anomaly_from_true_anomaly(
true_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the true anomaly.

Parameters:

  • true_anomaly (Angle) -- The true anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The eccentric anomaly.

Return type:

Angle

static from_SI_vector(
vector: numpy.ndarray[numpy.float64[6, 1]],
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create a COE model from a state vector in SI units.

Parameters:

  • vector (Vector6d) -- The state vector.

  • anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The COE model.

Return type:

COE

get_SI_vector(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → numpy.ndarray[numpy.float64[6, 1]]

Get the state vector of the COE in the specified anomaly type.

Parameters:

anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The state vector of the COE in the specified anomaly type.

Return type:

numpy.ndarray

get_angular_momentum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
arg0: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the angular momentum of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The angular momentum of the COE.

Return type:

Derived

get_aop(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the argument of periapsis of the COE.

Returns:

The argument of periapsis of the COE.

Return type:

Angle

get_apoapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the apoapsis radius of the COE.

Returns:

The apoapsis radius of the COE.

Return type:

Length

get_cartesian_state(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
frame: ostk.physics.coordinate.Frame,
) → Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity]

Get the Cartesian state of the COE.

Parameters:

  • gravitational_parameter (double) -- The gravitational parameter of the central body.

  • frame (Frame) -- The reference frame in which to express the Cartesian state.

Returns:

The Cartesian state of the COE.

Return type:

CartesianState

get_eccentric_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the eccentric anomaly of the COE.

Returns:

The eccentric anomaly of the COE.

Return type:

Angle

get_eccentricity(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.core.type.Real

Get the eccentricity of the COE.

Returns:

The eccentricity of the COE.

Return type:

float

get_inclination(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the inclination of the COE.

Returns:

The inclination of the COE.

Return type:

Angle

get_mean_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the mean anomaly of the COE.

Returns:

The mean anomaly of the COE.

Return type:

Angle

get_mean_motion(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the mean motion of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The mean motion of the COE.

Return type:

Derived

get_nodal_precession_rate(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
equatorial_radius: ostk.physics.unit.Length,
j2: ostk.core.type.Real,
) → ostk.physics.unit.Derived

Get the nodal precession of the COE.

Parameters:

  • gravitational_parameter (Derived) -- The gravitational parameter of the central body.

  • equatorial_radius (Length) -- The equatorial radius of the central body.

  • j2 (float) -- The second zonal harmonic coefficient of the central body.

Returns:

The nodal precession of the COE.

Return type:

Derived

get_orbital_period(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.time.Duration

Get the orbital period of the COE.

Parameters:

gravitational_parameter (double) -- The gravitational parameter of the central body.

Returns:

The orbital period of the COE.

Return type:

Duration

get_periapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the periapsis radius of the COE.

Returns:

The periapsis radius of the COE.

Return type:

Length

get_raan(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the right ascension of the ascending node of the COE.

Returns:

The right ascension of the ascending node of the COE.

Return type:

Angle

get_radial_distance(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the radial distance of the COE.

Returns:

The radial distance of the COE.

Return type:

Length

get_semi_latus_rectum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-latus rectum of the COE.

Returns:

The semilatus rectum of the COE.

Return type:

Length

get_semi_major_axis(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-major axis of the COE.

Returns:

The semi-major axis of the COE.

Return type:

Length

get_true_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the true anomaly of the COE.

Returns:

The true anomaly of the COE.

Return type:

Angle

is_defined(self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE) → bool

Check if the COE is defined.

Returns:

True if the COE is defined, False otherwise.

Return type:

bool

static mean_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the mean anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The mean anomaly.

Return type:

Angle

static string_from_element(
element: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
) → ostk.core.type.String

Get the string representation of an element.

Parameters:

element (Element) -- The element.

Returns:

The string representation.

Return type:

str

static true_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The true anomaly.

Return type:

Angle

static true_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The true anomaly.

Return type:

Angle

static undefined() → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create an undefined COE model.

Returns:

The undefined COE model.

Return type:

COE

\ No newline at end of file + ostk.astrodynamics.trajectory.orbit.model.kepler.COE — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.kepler.COE

class COE(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
semi_major_axis: ostk.physics.unit.Length,
eccentricity: ostk.core.type.Real,
inclination: ostk.physics.unit.Angle,
raan: ostk.physics.unit.Angle,
aop: ostk.physics.unit.Angle,
true_anomaly: ostk.physics.unit.Angle,
)

Bases: pybind11_object

Classical orbital elements.

Provides the classical orbital elements used to describe the orbit of a body around another.

\[\begin{split}\begin{aligned} a & = \text{semi-major axis} \\ e & = \text{eccentricity} \\ i & = \text{inclination} \\ \Omega & = \text{right ascension of the ascending node} \\ \omega & = \text{argument of periapsis} \\ \nu & = \text{true anomaly} \\ M & = \text{mean anomaly} \\ E & = \text{eccentric anomaly} \\ r_p & = \text{periapsis radius} \\ r_a & = \text{apoapsis radius} \end{aligned}\end{split}\]

Constructor.

Parameters:

  • semi_major_axis (Length) -- The semi-major axis.

  • eccentricity (float) -- The eccentricity.

  • inclination (Angle) -- The inclination.

  • raan (Angle) -- The right ascension of the ascending node.

  • aop (Angle) -- The argument of periapsis.

  • true_anomaly (Angle) -- The true anomaly.

Methods

cartesian

Create a COE model from Cartesian state.

compute_angular_momentum

Overloaded function.

compute_radial_distance

Compute the radial distance from the semi-latus rectum and the eccentricity.

compute_semi_latus_rectum

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

eccentric_anomaly_from_mean_anomaly

Compute the eccentric anomaly from the mean anomaly.

eccentric_anomaly_from_true_anomaly

Compute the eccentric anomaly from the true anomaly.

from_SI_vector

Create a COE model from a state vector in SI units.

get_SI_vector

Get the state vector of the COE in the specified anomaly type.

get_angular_momentum

Get the angular momentum of the COE.

get_aop

Get the argument of periapsis of the COE.

get_apoapsis_radius

Get the apoapsis radius of the COE.

get_cartesian_state

Get the Cartesian state of the COE.

get_eccentric_anomaly

Get the eccentric anomaly of the COE.

get_eccentricity

Get the eccentricity of the COE.

get_inclination

Get the inclination of the COE.

get_mean_anomaly

Get the mean anomaly of the COE.

get_mean_motion

Get the mean motion of the COE.

get_nodal_precession_rate

Get the nodal precession of the COE.

get_orbital_period

Get the orbital period of the COE.

get_periapsis_radius

Get the periapsis radius of the COE.

get_raan

Get the right ascension of the ascending node of the COE.

get_radial_distance

Get the radial distance of the COE.

get_semi_latus_rectum

Get the semi-latus rectum of the COE.

get_semi_major_axis

Get the semi-major axis of the COE.

get_true_anomaly

Get the true anomaly of the COE.

is_defined

Check if the COE is defined.

mean_anomaly_from_eccentric_anomaly

Compute the mean anomaly from the eccentric anomaly.

string_from_element

Get the string representation of an element.

true_anomaly_from_eccentric_anomaly

Compute the true anomaly from the eccentric anomaly.

true_anomaly_from_mean_anomaly

Compute the true anomaly from the mean anomaly.

undefined

Create an undefined COE model.

class AnomalyType(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
value: int,
)

Bases: pybind11_object

The type of Anomaly.

Members:

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
class Element(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
value: int,
)

Bases: pybind11_object

Classical Orbital Element enumeration.

Members:

SemiMajorAxis : Semi-Major Axis

Eccentricity : Eccentricity

Inclination : Inclination

Aop : Argument of Perigee

Raan : Right Angle of the Ascending Node

TrueAnomaly : True Anomaly

MeanAnomaly : Mean Anomaly

EccentricAnomaly : Eccentric Anomaly

property name
static cartesian(
cartesian_state: Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity],
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create a COE model from Cartesian state.

Parameters:

  • cartesian_state (CartesianState) -- The Cartesian state.

  • gravitational_parameter (float) -- The gravitational parameter of the central body.

Returns:

The COE model.

Return type:

COE

static compute_angular_momentum(*args, **kwargs)

Overloaded function.

  1. compute_angular_momentum(semi_major_axis: ostk.core.type.Real, eccentricity: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-major axis and the eccentricity.

    Args:

    semi_major_axis (float): The semi-major axis. In meters. eccentricity (float): The eccentricity. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

  2. compute_angular_momentum(semi_latus_rectum: ostk.core.type.Real, gravitational_parameter: ostk.physics.unit.Derived) -> ostk.core.type.Real

    Compute the angular momentum from the semi-latus rectum.

    Args:

    semi_latus_rectum (float): The semi-latus rectum. In meters. gravitational_parameter (Derived): The gravitational parameter of the central body.

    Returns:

    Derived: The angular momentum.

static compute_radial_distance(
semi_latus_rectum: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
true_anomaly: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the radial distance from the semi-latus rectum and the eccentricity.

Parameters:

  • semi_latus_rectum (float) -- The semi-latus rectum. In meters.

  • eccentricity (float) -- The eccentricity.

  • true_anomaly (float) -- The true anomly. In degrees.

Returns:

The radial distance.

Return type:

Length

static compute_semi_latus_rectum(
semi_major_axis: ostk.core.type.Real,
eccentricity: ostk.core.type.Real,
) → ostk.core.type.Real

Compute the semi-latus rectum from the semi-major axis and the eccentricity.

Parameters:

  • semi_major_axis (float) -- The semi-major axis. In meters.

  • eccentricity (float) -- The eccentricity.

Returns:

The semi-latus rectum.

Return type:

Length

static eccentric_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The eccentric anomaly.

Return type:

Angle

static eccentric_anomaly_from_true_anomaly(
true_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the eccentric anomaly from the true anomaly.

Parameters:

  • true_anomaly (Angle) -- The true anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The eccentric anomaly.

Return type:

Angle

static from_SI_vector(
vector: numpy.ndarray[numpy.float64[6, 1]],
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create a COE model from a state vector in SI units.

Parameters:

  • vector (Vector6d) -- The state vector.

  • anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The COE model.

Return type:

COE

get_SI_vector(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
anomaly_type: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType,
) → numpy.ndarray[numpy.float64[6, 1]]

Get the state vector of the COE in the specified anomaly type.

Parameters:

anomaly_type (AnomalyType) -- The type of anomaly.

Returns:

The state vector of the COE in the specified anomaly type.

Return type:

numpy.ndarray

get_angular_momentum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
arg0: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the angular momentum of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The angular momentum of the COE.

Return type:

Derived

get_aop(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the argument of periapsis of the COE.

Returns:

The argument of periapsis of the COE.

Return type:

Angle

get_apoapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the apoapsis radius of the COE.

Returns:

The apoapsis radius of the COE.

Return type:

Length

get_cartesian_state(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
frame: ostk.physics.coordinate.Frame,
) → Tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity]

Get the Cartesian state of the COE.

Parameters:

  • gravitational_parameter (double) -- The gravitational parameter of the central body.

  • frame (Frame) -- The reference frame in which to express the Cartesian state.

Returns:

The Cartesian state of the COE.

Return type:

CartesianState

get_eccentric_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the eccentric anomaly of the COE.

Returns:

The eccentric anomaly of the COE.

Return type:

Angle

get_eccentricity(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.core.type.Real

Get the eccentricity of the COE.

Returns:

The eccentricity of the COE.

Return type:

float

get_inclination(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the inclination of the COE.

Returns:

The inclination of the COE.

Return type:

Angle

get_mean_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the mean anomaly of the COE.

Returns:

The mean anomaly of the COE.

Return type:

Angle

get_mean_motion(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.unit.Derived

Get the mean motion of the COE.

Parameters:

gravitational_parameter (Derived) -- The gravitational parameter of the central body.

Returns:

The mean motion of the COE.

Return type:

Derived

get_nodal_precession_rate(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
equatorial_radius: ostk.physics.unit.Length,
j2: ostk.core.type.Real,
) → ostk.physics.unit.Derived

Get the nodal precession of the COE.

Parameters:

  • gravitational_parameter (Derived) -- The gravitational parameter of the central body.

  • equatorial_radius (Length) -- The equatorial radius of the central body.

  • j2 (float) -- The second zonal harmonic coefficient of the central body.

Returns:

The nodal precession of the COE.

Return type:

Derived

get_orbital_period(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
gravitational_parameter: ostk.physics.unit.Derived,
) → ostk.physics.time.Duration

Get the orbital period of the COE.

Parameters:

gravitational_parameter (double) -- The gravitational parameter of the central body.

Returns:

The orbital period of the COE.

Return type:

Duration

get_periapsis_radius(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the periapsis radius of the COE.

Returns:

The periapsis radius of the COE.

Return type:

Length

get_raan(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the right ascension of the ascending node of the COE.

Returns:

The right ascension of the ascending node of the COE.

Return type:

Angle

get_radial_distance(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the radial distance of the COE.

Returns:

The radial distance of the COE.

Return type:

Length

get_semi_latus_rectum(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-latus rectum of the COE.

Returns:

The semilatus rectum of the COE.

Return type:

Length

get_semi_major_axis(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Length

Get the semi-major axis of the COE.

Returns:

The semi-major axis of the COE.

Return type:

Length

get_true_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE,
) → ostk.physics.unit.Angle

Get the true anomaly of the COE.

Returns:

The true anomaly of the COE.

Return type:

Angle

is_defined(self: ostk.astrodynamics.trajectory.orbit.model.kepler.COE) → bool

Check if the COE is defined.

Returns:

True if the COE is defined, False otherwise.

Return type:

bool

static mean_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the mean anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The mean anomaly.

Return type:

Angle

static string_from_element(
element: ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element,
) → ostk.core.type.String

Get the string representation of an element.

Parameters:

element (Element) -- The element.

Returns:

The string representation.

Return type:

str

static true_anomaly_from_eccentric_anomaly(
eccentric_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the eccentric anomaly.

Parameters:

  • eccentric_anomaly (Angle) -- The eccentric anomaly.

  • eccentricity (float) -- The eccentricity.

Returns:

The true anomaly.

Return type:

Angle

static true_anomaly_from_mean_anomaly(
mean_anomaly: ostk.physics.unit.Angle,
eccentricity: ostk.core.type.Real,
tolerance: ostk.core.type.Real,
) → ostk.physics.unit.Angle

Compute the true anomaly from the mean anomaly.

Parameters:

  • mean_anomaly (Angle) -- The mean anomaly.

  • eccentricity (float) -- The eccentricity.

  • tolerance (float) -- The tolerance of the root solver.

Returns:

The true anomaly.

Return type:

Angle

static undefined() → ostk.astrodynamics.trajectory.orbit.model.kepler.COE

Create an undefined COE model.

Returns:

The undefined COE model.

Return type:

COE

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE.html index 52fbca08f..009d6088e 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE

class TLE(*args, **kwargs)

Bases: pybind11_object

A Two-Line Element set (TLE).

A TLE is a data format encoding a list of orbital elements of an Earth-orbiting object for a given point in time

Reference:

https://en.wikipedia.org/wiki/Two-line_element_set

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE, first_line: ostk.core.type.String, second_line: ostk.core.type.String) -> None

    Constructor.

    Args:

    first_line (str): The first line of the TLE. second_line (str): The second line of the TLE.

  2. __init__(self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE, satellite_name: ostk.core.type.String, first_line: ostk.core.type.String, second_line: ostk.core.type.String) -> None

    Constructor.

    Args:

    satellite_name (str): The name of the satellite. first_line (str): The first line of the TLE. second_line (str): The second line of the TLE.

Methods

can_parse

Check if a TLE can be parsed from two strings.

construct

Overloaded function.

generate_checksum

Generate the checksum of a string.

get_aop

Get the argument of perigee.

get_b_star_drag_term

Get the B* drag term.

get_classification

Get the classification.

get_eccentricity

Get the eccentricity.

get_element_set_number

Get the element set number.

get_ephemeris_type

Get the ephemeris type.

get_epoch

Get the epoch.

get_first_line

Get the first line of the TLE.

get_first_line_checksum

Get the checksum of the first line.

get_inclination

Get the inclination.

get_international_designator

Get the international designator.

get_mean_anomaly

Get the mean anomaly.

get_mean_motion

Get the mean motion.

get_mean_motion_first_time_derivative_divided_by_two

Get the mean motion first time derivative divided by two.

get_mean_motion_second_time_derivative_divided_by_six

Get the mean motion second time derivative divided by six.

get_raan

Get the right ascension of the ascending node.

get_revolution_number_at_epoch

Get the revolution number at epoch.

get_satellite_name

Get the name of the satellite.

get_satellite_number

Get the satellite number.

get_second_line

Get the second line of the TLE.

get_second_line_checksum

Get the checksum of the second line.

is_defined

Check if the TLE object is defined.

load

Load a TLE from a file.

parse

Parse a TLE from a string.

set_epoch

Set the epoch.

set_revolution_number_at_epoch

Set the revolution number at epoch.

set_satellite_number

Set the satellite number.

undefined

Create an undefined TLE object.

static can_parse(
first_line: ostk.core.type.String,
second_line: ostk.core.type.String,
) → bool

Check if a TLE can be parsed from two strings.

Parameters:

  • first_line (str) -- The first line of the TLE.

  • second_line (str) -- The second line of the TLE.

Returns:

True if the TLE can be parsed, False otherwise.

Return type:

bool

static construct(*args, **kwargs)

Overloaded function.

  1. construct(satellite_name: ostk.core.type.String, satellite_number: ostk.core.type.Integer, classification: ostk.core.type.String, international_designator: ostk.core.type.String, epoch: ostk.physics.time.Instant, mean_motion_first_time_derivative_divided_by_two: ostk.core.type.Real, mean_motion_second_time_derivative_divided_by_six: ostk.core.type.Real, b_star_drag_term: ostk.core.type.Real, ephemeris_type: ostk.core.type.Integer, element_set_number: ostk.core.type.Integer, inclination: ostk.physics.unit.Angle, raan: ostk.physics.unit.Angle, eccentricity: ostk.core.type.Real, aop: ostk.physics.unit.Angle, mean_anomaly: ostk.physics.unit.Angle, mean_motion: ostk.physics.unit.Derived, revolution_number_at_epoch: ostk.core.type.Integer) -> ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE

    Construct a TLE.

    Args:

    satellite_name (str): The name of the satellite. satellite_number (int): The satellite number. classification (str): The classification. international_designator (str): The international designator. epoch (Instant): The epoch. mean_motion_first_time_derivative_divided_by_two (float): The mean motion first time derivative divided by two. mean_motion_second_time_derivative_divided_by_six (float): The mean motion second time derivative divided by six. b_star_drag_term (float): The B* drag term. ephemeris_type (int): The ephemeris type. element_set_number (int): The element set number. inclination (Angle): The inclination. raan (Angle): The right ascension of the ascending node. eccentricity (float): The eccentricity. aop (Angle): The argument of perigee. mean_anomaly (Angle): The mean anomaly. mean_motion (float): The mean motion. revolution_number_at_epoch (int): The revolution number at epoch.

    Returns:

    TLE: The constructed TLE.

  2. construct(satellite_number: ostk.core.type.Integer, classification: ostk.core.type.String, international_designator: ostk.core.type.String, epoch: ostk.physics.time.Instant, mean_motion_first_time_derivative_divided_by_two: ostk.core.type.Real, mean_motion_second_time_derivative_divided_by_six: ostk.core.type.Real, b_star_drag_term: ostk.core.type.Real, ephemeris_type: ostk.core.type.Integer, element_set_number: ostk.core.type.Integer, inclination: ostk.physics.unit.Angle, raan: ostk.physics.unit.Angle, eccentricity: ostk.core.type.Real, aop: ostk.physics.unit.Angle, mean_anomaly: ostk.physics.unit.Angle, mean_motion: ostk.physics.unit.Derived, revolution_number_at_epoch: ostk.core.type.Integer) -> ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE

    Construct a TLE.

    Args:

    satellite_number (int): The satellite number. classification (str): The classification. international_designator (str): The international designator. epoch (Instant): The epoch. mean_motion_first_time_derivative_divided_by_two (float): The mean motion first time derivative divided by two. mean_motion_second_time_derivative_divided_by_six (float): The mean motion second time derivative divided by six. b_star_drag_term (float): The B* drag term. ephemeris_type (int): The ephemeris type. element_set_number (int): The element set number. inclination (Angle): The inclination. raan (Angle): The right ascension of the ascending node. eccentricity (float): The eccentricity. aop (Angle): The argument of perigee. mean_anomaly (Angle): The mean anomaly. mean_motion (float): The mean motion. revolution_number_at_epoch (int): The revolution number at epoch.

    Returns:

    TLE: The constructed TLE.

static generate_checksum(string: ostk.core.type.String) → ostk.core.type.Integer

Generate the checksum of a string.

Parameters:

string (str) -- The string.

Returns:

The checksum.

Return type:

int

get_aop(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.physics.unit.Angle

Get the argument of perigee.

Returns:

The argument of perigee.

Return type:

Angle

get_b_star_drag_term(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Real

Get the B* drag term.

Returns:

The B* drag term.

Return type:

float

get_classification(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.String

Get the classification.

Returns:

The classification.

Return type:

str

get_eccentricity(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Real

Get the eccentricity.

Returns:

The eccentricity.

Return type:

float

get_element_set_number(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Integer

Get the element set number.

Returns:

The element set number.

Return type:

int

get_ephemeris_type(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Integer

Get the ephemeris type.

Returns:

The ephemeris type.

Return type:

int

get_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.physics.time.Instant

Get the epoch.

Returns:

The epoch.

Return type:

Instant

get_first_line(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.String

Get the first line of the TLE.

Returns:

The first line of the TLE.

Return type:

str

get_first_line_checksum(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Integer

Get the checksum of the first line.

Returns:

The checksum of the first line.

Return type:

int

get_inclination(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.physics.unit.Angle

Get the inclination.

Returns:

The inclination.

Return type:

Angle

get_international_designator(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.String

Get the international designator.

Returns:

The international designator.

Return type:

str

get_mean_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.physics.unit.Angle

Get the mean anomaly.

Returns:

The mean anomaly.

Return type:

Angle

get_mean_motion(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.physics.unit.Derived

Get the mean motion.

Returns:

The mean motion.

Return type:

float

get_mean_motion_first_time_derivative_divided_by_two(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Real

Get the mean motion first time derivative divided by two.

Returns:

The mean motion first time derivative divided by two.

Return type:

float

get_mean_motion_second_time_derivative_divided_by_six(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Real

Get the mean motion second time derivative divided by six.

Returns:

The mean motion second time derivative divided by six.

Return type:

float

get_raan(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.physics.unit.Angle

Get the right ascension of the ascending node.

Returns:

The right ascension of the ascending node.

Return type:

Angle

get_revolution_number_at_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Integer

Get the revolution number at epoch.

Returns:

The revolution number at epoch.

Return type:

int

get_satellite_name(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.String

Get the name of the satellite.

Returns:

The name of the satellite.

Return type:

str

get_satellite_number(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Integer

Get the satellite number.

Returns:

The satellite number.

Return type:

int

get_second_line(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.String

Get the second line of the TLE.

Returns:

The second line of the TLE.

Return type:

str

get_second_line_checksum(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Integer

Get the checksum of the second line.

Returns:

The checksum of the second line.

Return type:

int

is_defined(self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE) → bool

Check if the TLE object is defined.

Returns:

True if the TLE object is defined, False otherwise.

Return type:

bool

static load(
file: ostk.core.filesystem.File,
) → ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE

Load a TLE from a file.

Parameters:

file (str) -- The path to the file.

Returns:

The loaded TLE.

Return type:

TLE

static parse(
string: ostk.core.type.String,
) → ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE

Parse a TLE from a string.

Parameters:

string (str) -- The string to parse.

Returns:

The parsed TLE.

Return type:

TLE

set_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
epoch: ostk.physics.time.Instant,
) → None

Set the epoch.

Parameters:

epoch (Instant) -- The epoch.

set_revolution_number_at_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
revolution_number: ostk.core.type.Integer,
) → None

Set the revolution number at epoch.

Parameters:

revolution_number (int) -- The revolution number at epoch.

set_satellite_number(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
satellite_number: ostk.core.type.Integer,
) → None

Set the satellite number.

Parameters:

satellite_number (int) -- The satellite number.

static undefined() → ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE

Create an undefined TLE object.

Returns:

The undefined TLE object.

Return type:

TLE

\ No newline at end of file + ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE

class TLE(*args, **kwargs)

Bases: pybind11_object

A Two-Line Element set (TLE).

A TLE is a data format encoding a list of orbital elements of an Earth-orbiting object for a given point in time

Reference:

https://en.wikipedia.org/wiki/Two-line_element_set

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE, first_line: ostk.core.type.String, second_line: ostk.core.type.String) -> None

    Constructor.

    Args:

    first_line (str): The first line of the TLE. second_line (str): The second line of the TLE.

  2. __init__(self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE, satellite_name: ostk.core.type.String, first_line: ostk.core.type.String, second_line: ostk.core.type.String) -> None

    Constructor.

    Args:

    satellite_name (str): The name of the satellite. first_line (str): The first line of the TLE. second_line (str): The second line of the TLE.

Methods

can_parse

Check if a TLE can be parsed from two strings.

construct

Overloaded function.

generate_checksum

Generate the checksum of a string.

get_aop

Get the argument of perigee.

get_b_star_drag_term

Get the B* drag term.

get_classification

Get the classification.

get_eccentricity

Get the eccentricity.

get_element_set_number

Get the element set number.

get_ephemeris_type

Get the ephemeris type.

get_epoch

Get the epoch.

get_first_line

Get the first line of the TLE.

get_first_line_checksum

Get the checksum of the first line.

get_inclination

Get the inclination.

get_international_designator

Get the international designator.

get_mean_anomaly

Get the mean anomaly.

get_mean_motion

Get the mean motion.

get_mean_motion_first_time_derivative_divided_by_two

Get the mean motion first time derivative divided by two.

get_mean_motion_second_time_derivative_divided_by_six

Get the mean motion second time derivative divided by six.

get_raan

Get the right ascension of the ascending node.

get_revolution_number_at_epoch

Get the revolution number at epoch.

get_satellite_name

Get the name of the satellite.

get_satellite_number

Get the satellite number.

get_second_line

Get the second line of the TLE.

get_second_line_checksum

Get the checksum of the second line.

is_defined

Check if the TLE object is defined.

load

Load a TLE from a file.

parse

Parse a TLE from a string.

set_epoch

Set the epoch.

set_revolution_number_at_epoch

Set the revolution number at epoch.

set_satellite_number

Set the satellite number.

undefined

Create an undefined TLE object.

static can_parse(
first_line: ostk.core.type.String,
second_line: ostk.core.type.String,
) → bool

Check if a TLE can be parsed from two strings.

Parameters:

  • first_line (str) -- The first line of the TLE.

  • second_line (str) -- The second line of the TLE.

Returns:

True if the TLE can be parsed, False otherwise.

Return type:

bool

static construct(*args, **kwargs)

Overloaded function.

  1. construct(satellite_name: ostk.core.type.String, satellite_number: ostk.core.type.Integer, classification: ostk.core.type.String, international_designator: ostk.core.type.String, epoch: ostk.physics.time.Instant, mean_motion_first_time_derivative_divided_by_two: ostk.core.type.Real, mean_motion_second_time_derivative_divided_by_six: ostk.core.type.Real, b_star_drag_term: ostk.core.type.Real, ephemeris_type: ostk.core.type.Integer, element_set_number: ostk.core.type.Integer, inclination: ostk.physics.unit.Angle, raan: ostk.physics.unit.Angle, eccentricity: ostk.core.type.Real, aop: ostk.physics.unit.Angle, mean_anomaly: ostk.physics.unit.Angle, mean_motion: ostk.physics.unit.Derived, revolution_number_at_epoch: ostk.core.type.Integer) -> ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE

    Construct a TLE.

    Args:

    satellite_name (str): The name of the satellite. satellite_number (int): The satellite number. classification (str): The classification. international_designator (str): The international designator. epoch (Instant): The epoch. mean_motion_first_time_derivative_divided_by_two (float): The mean motion first time derivative divided by two. mean_motion_second_time_derivative_divided_by_six (float): The mean motion second time derivative divided by six. b_star_drag_term (float): The B* drag term. ephemeris_type (int): The ephemeris type. element_set_number (int): The element set number. inclination (Angle): The inclination. raan (Angle): The right ascension of the ascending node. eccentricity (float): The eccentricity. aop (Angle): The argument of perigee. mean_anomaly (Angle): The mean anomaly. mean_motion (float): The mean motion. revolution_number_at_epoch (int): The revolution number at epoch.

    Returns:

    TLE: The constructed TLE.

  2. construct(satellite_number: ostk.core.type.Integer, classification: ostk.core.type.String, international_designator: ostk.core.type.String, epoch: ostk.physics.time.Instant, mean_motion_first_time_derivative_divided_by_two: ostk.core.type.Real, mean_motion_second_time_derivative_divided_by_six: ostk.core.type.Real, b_star_drag_term: ostk.core.type.Real, ephemeris_type: ostk.core.type.Integer, element_set_number: ostk.core.type.Integer, inclination: ostk.physics.unit.Angle, raan: ostk.physics.unit.Angle, eccentricity: ostk.core.type.Real, aop: ostk.physics.unit.Angle, mean_anomaly: ostk.physics.unit.Angle, mean_motion: ostk.physics.unit.Derived, revolution_number_at_epoch: ostk.core.type.Integer) -> ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE

    Construct a TLE.

    Args:

    satellite_number (int): The satellite number. classification (str): The classification. international_designator (str): The international designator. epoch (Instant): The epoch. mean_motion_first_time_derivative_divided_by_two (float): The mean motion first time derivative divided by two. mean_motion_second_time_derivative_divided_by_six (float): The mean motion second time derivative divided by six. b_star_drag_term (float): The B* drag term. ephemeris_type (int): The ephemeris type. element_set_number (int): The element set number. inclination (Angle): The inclination. raan (Angle): The right ascension of the ascending node. eccentricity (float): The eccentricity. aop (Angle): The argument of perigee. mean_anomaly (Angle): The mean anomaly. mean_motion (float): The mean motion. revolution_number_at_epoch (int): The revolution number at epoch.

    Returns:

    TLE: The constructed TLE.

static generate_checksum(string: ostk.core.type.String) → ostk.core.type.Integer

Generate the checksum of a string.

Parameters:

string (str) -- The string.

Returns:

The checksum.

Return type:

int

get_aop(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.physics.unit.Angle

Get the argument of perigee.

Returns:

The argument of perigee.

Return type:

Angle

get_b_star_drag_term(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Real

Get the B* drag term.

Returns:

The B* drag term.

Return type:

float

get_classification(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.String

Get the classification.

Returns:

The classification.

Return type:

str

get_eccentricity(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Real

Get the eccentricity.

Returns:

The eccentricity.

Return type:

float

get_element_set_number(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Integer

Get the element set number.

Returns:

The element set number.

Return type:

int

get_ephemeris_type(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Integer

Get the ephemeris type.

Returns:

The ephemeris type.

Return type:

int

get_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.physics.time.Instant

Get the epoch.

Returns:

The epoch.

Return type:

Instant

get_first_line(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.String

Get the first line of the TLE.

Returns:

The first line of the TLE.

Return type:

str

get_first_line_checksum(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Integer

Get the checksum of the first line.

Returns:

The checksum of the first line.

Return type:

int

get_inclination(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.physics.unit.Angle

Get the inclination.

Returns:

The inclination.

Return type:

Angle

get_international_designator(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.String

Get the international designator.

Returns:

The international designator.

Return type:

str

get_mean_anomaly(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.physics.unit.Angle

Get the mean anomaly.

Returns:

The mean anomaly.

Return type:

Angle

get_mean_motion(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.physics.unit.Derived

Get the mean motion.

Returns:

The mean motion.

Return type:

float

get_mean_motion_first_time_derivative_divided_by_two(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Real

Get the mean motion first time derivative divided by two.

Returns:

The mean motion first time derivative divided by two.

Return type:

float

get_mean_motion_second_time_derivative_divided_by_six(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Real

Get the mean motion second time derivative divided by six.

Returns:

The mean motion second time derivative divided by six.

Return type:

float

get_raan(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.physics.unit.Angle

Get the right ascension of the ascending node.

Returns:

The right ascension of the ascending node.

Return type:

Angle

get_revolution_number_at_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Integer

Get the revolution number at epoch.

Returns:

The revolution number at epoch.

Return type:

int

get_satellite_name(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.String

Get the name of the satellite.

Returns:

The name of the satellite.

Return type:

str

get_satellite_number(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Integer

Get the satellite number.

Returns:

The satellite number.

Return type:

int

get_second_line(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.String

Get the second line of the TLE.

Returns:

The second line of the TLE.

Return type:

str

get_second_line_checksum(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
) → ostk.core.type.Integer

Get the checksum of the second line.

Returns:

The checksum of the second line.

Return type:

int

is_defined(self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE) → bool

Check if the TLE object is defined.

Returns:

True if the TLE object is defined, False otherwise.

Return type:

bool

static load(
file: ostk.core.filesystem.File,
) → ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE

Load a TLE from a file.

Parameters:

file (str) -- The path to the file.

Returns:

The loaded TLE.

Return type:

TLE

static parse(
string: ostk.core.type.String,
) → ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE

Parse a TLE from a string.

Parameters:

string (str) -- The string to parse.

Returns:

The parsed TLE.

Return type:

TLE

set_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
epoch: ostk.physics.time.Instant,
) → None

Set the epoch.

Parameters:

epoch (Instant) -- The epoch.

set_revolution_number_at_epoch(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
revolution_number: ostk.core.type.Integer,
) → None

Set the revolution number at epoch.

Parameters:

revolution_number (int) -- The revolution number at epoch.

set_satellite_number(
self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE,
satellite_number: ostk.core.type.Integer,
) → None

Set the satellite number.

Parameters:

satellite_number (int) -- The satellite number.

static undefined() → ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE

Create an undefined TLE object.

Returns:

The undefined TLE object.

Return type:

TLE

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.CoordinateSubset.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.CoordinateSubset.html index a54bd5b32..2f3e1a660 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.CoordinateSubset.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.CoordinateSubset.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.state.CoordinateSubset — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.state.CoordinateSubset

class CoordinateSubset(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
name: ostk.core.type.String,
size: int,
)

Bases: pybind11_object

State coordinate subset. It contains information related to a particular group of coordinates. It does not contain the coordinate values.

Constructor.

Parameters:

  • name (str) -- The name of the coordinate subset.

  • size (int) -- The size of the coordinate subset.

Methods

add

Add the coordinates of another state to the coordinates of this state.

drag_coefficient

Get the drag coefficient coordinate subset.

get_id

Get the identifier of the coordinate subset.

get_name

Get the name of the coordinate subset.

get_size

Get the size of the coordinate subset.

in_frame

Convert the coordinates of this state from one frame to another.

mass

Get the mass coordinate subset.

subtract

Subtract the coordinates of another state from the coordinates of this state.

surface_area

Get the surface area coordinate subset.

add(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Add the coordinates of another state to the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The sum of the coordinates.

Return type:

numpy.ndarray

static drag_coefficient() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the drag coefficient coordinate subset.

Returns:

The drag coefficient coordinate subset.

Return type:

CoordinateSubset

get_id(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the identifier of the coordinate subset.

Returns:

The identifier of the coordinate subset.

Return type:

str

get_name(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the name of the coordinate subset.

Returns:

The name of the coordinate subset.

Return type:

str

get_size(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → int

Get the size of the coordinate subset.

Returns:

The size of the coordinate subset.

Return type:

int

in_frame(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
from_frame: ostk.physics.coordinate.Frame,
to_frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Convert the coordinates of this state from one frame to another.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • from_frame (Frame) -- The reference frame of the input coordinates.

  • to_frame (Frame) -- The reference frame of the output coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The coordinates in the output frame.

Return type:

numpy.ndarray

static mass() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the mass coordinate subset.

Returns:

The mass coordinate subset.

Return type:

CoordinateSubset

subtract(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Subtract the coordinates of another state from the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The difference of the coordinates.

Return type:

numpy.ndarray

static surface_area() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the surface area coordinate subset.

Returns:

The surface area coordinate subset.

Return type:

CoordinateSubset

\ No newline at end of file + ostk.astrodynamics.trajectory.state.CoordinateSubset — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.state.CoordinateSubset

class CoordinateSubset(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
name: ostk.core.type.String,
size: int,
)

Bases: pybind11_object

State coordinate subset. It contains information related to a particular group of coordinates. It does not contain the coordinate values.

Constructor.

Parameters:

  • name (str) -- The name of the coordinate subset.

  • size (int) -- The size of the coordinate subset.

Methods

add

Add the coordinates of another state to the coordinates of this state.

drag_coefficient

Get the drag coefficient coordinate subset.

get_id

Get the identifier of the coordinate subset.

get_name

Get the name of the coordinate subset.

get_size

Get the size of the coordinate subset.

in_frame

Convert the coordinates of this state from one frame to another.

mass

Get the mass coordinate subset.

subtract

Subtract the coordinates of another state from the coordinates of this state.

surface_area

Get the surface area coordinate subset.

add(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Add the coordinates of another state to the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The sum of the coordinates.

Return type:

numpy.ndarray

static drag_coefficient() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the drag coefficient coordinate subset.

Returns:

The drag coefficient coordinate subset.

Return type:

CoordinateSubset

get_id(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the identifier of the coordinate subset.

Returns:

The identifier of the coordinate subset.

Return type:

str

get_name(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the name of the coordinate subset.

Returns:

The name of the coordinate subset.

Return type:

str

get_size(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → int

Get the size of the coordinate subset.

Returns:

The size of the coordinate subset.

Return type:

int

in_frame(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
from_frame: ostk.physics.coordinate.Frame,
to_frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Convert the coordinates of this state from one frame to another.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • from_frame (Frame) -- The reference frame of the input coordinates.

  • to_frame (Frame) -- The reference frame of the output coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The coordinates in the output frame.

Return type:

numpy.ndarray

static mass() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the mass coordinate subset.

Returns:

The mass coordinate subset.

Return type:

CoordinateSubset

subtract(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Subtract the coordinates of another state from the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The difference of the coordinates.

Return type:

numpy.ndarray

static surface_area() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the surface area coordinate subset.

Returns:

The surface area coordinate subset.

Return type:

CoordinateSubset

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity.html index 6dd1a63db..010656082 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity

class AngularVelocity(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity,
attitude_quaternion: ostk::astrodynamics::trajectory::state::coordinatesubset::AttitudeQuaternion,
name: ostk.core.type.String,
)

Bases: CoordinateSubset

Angular velocity coordinate subset.

Defined with respect to a reference frame and a Attitude quaternion.

Constructor.

Parameters:

  • attitude_quaternion (AttitudeQuaternion) -- The Attitude quaternion.

  • name (str) -- The name of the subset.

Methods

add

Add the coordinates of another state to the coordinates of this state.

default

Get the default Angular velocity subset.

drag_coefficient

Get the drag coefficient coordinate subset.

get_id

Get the identifier of the coordinate subset.

get_name

Get the name of the coordinate subset.

get_size

Get the size of the coordinate subset.

in_frame

Convert a Angular velocity from one reference frame to another.

mass

Get the mass coordinate subset.

subtract

Subtract the coordinates of another state from the coordinates of this state.

surface_area

Get the surface area coordinate subset.

add(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Add the coordinates of another state to the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The sum of the coordinates.

Return type:

numpy.ndarray

static default() → ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity

Get the default Angular velocity subset.

Returns:

The default Angular velocity subset.

Return type:

AngularVelocity

static drag_coefficient() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the drag coefficient coordinate subset.

Returns:

The drag coefficient coordinate subset.

Return type:

CoordinateSubset

get_id(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the identifier of the coordinate subset.

Returns:

The identifier of the coordinate subset.

Return type:

str

get_name(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the name of the coordinate subset.

Returns:

The name of the coordinate subset.

Return type:

str

get_size(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → int

Get the size of the coordinate subset.

Returns:

The size of the coordinate subset.

Return type:

int

in_frame(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
from_frame: ostk.physics.coordinate.Frame,
to_frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Convert a Angular velocity from one reference frame to another.

Parameters:

  • instant (Instant) -- The instant of the conversion.

  • coordinates (numpy.ndarray) -- The Angular velocity to convert.

  • from_frame (str) -- The reference frame of the input Angular velocity.

  • to_frame (str) -- The reference frame of the output Angular velocity.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The Angular velocity in the output reference frame.

Return type:

numpy.ndarray

static mass() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the mass coordinate subset.

Returns:

The mass coordinate subset.

Return type:

CoordinateSubset

subtract(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Subtract the coordinates of another state from the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The difference of the coordinates.

Return type:

numpy.ndarray

static surface_area() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the surface area coordinate subset.

Returns:

The surface area coordinate subset.

Return type:

CoordinateSubset

\ No newline at end of file + ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity

class AngularVelocity(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity,
attitude_quaternion: ostk::astrodynamics::trajectory::state::coordinatesubset::AttitudeQuaternion,
name: ostk.core.type.String,
)

Bases: CoordinateSubset

Angular velocity coordinate subset.

Defined with respect to a reference frame and a Attitude quaternion.

Constructor.

Parameters:

  • attitude_quaternion (AttitudeQuaternion) -- The Attitude quaternion.

  • name (str) -- The name of the subset.

Methods

add

Add the coordinates of another state to the coordinates of this state.

default

Get the default Angular velocity subset.

drag_coefficient

Get the drag coefficient coordinate subset.

get_id

Get the identifier of the coordinate subset.

get_name

Get the name of the coordinate subset.

get_size

Get the size of the coordinate subset.

in_frame

Convert a Angular velocity from one reference frame to another.

mass

Get the mass coordinate subset.

subtract

Subtract the coordinates of another state from the coordinates of this state.

surface_area

Get the surface area coordinate subset.

add(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Add the coordinates of another state to the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The sum of the coordinates.

Return type:

numpy.ndarray

static default() → ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity

Get the default Angular velocity subset.

Returns:

The default Angular velocity subset.

Return type:

AngularVelocity

static drag_coefficient() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the drag coefficient coordinate subset.

Returns:

The drag coefficient coordinate subset.

Return type:

CoordinateSubset

get_id(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the identifier of the coordinate subset.

Returns:

The identifier of the coordinate subset.

Return type:

str

get_name(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the name of the coordinate subset.

Returns:

The name of the coordinate subset.

Return type:

str

get_size(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → int

Get the size of the coordinate subset.

Returns:

The size of the coordinate subset.

Return type:

int

in_frame(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
from_frame: ostk.physics.coordinate.Frame,
to_frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Convert a Angular velocity from one reference frame to another.

Parameters:

  • instant (Instant) -- The instant of the conversion.

  • coordinates (numpy.ndarray) -- The Angular velocity to convert.

  • from_frame (str) -- The reference frame of the input Angular velocity.

  • to_frame (str) -- The reference frame of the output Angular velocity.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The Angular velocity in the output reference frame.

Return type:

numpy.ndarray

static mass() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the mass coordinate subset.

Returns:

The mass coordinate subset.

Return type:

CoordinateSubset

subtract(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Subtract the coordinates of another state from the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The difference of the coordinates.

Return type:

numpy.ndarray

static surface_area() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the surface area coordinate subset.

Returns:

The surface area coordinate subset.

Return type:

CoordinateSubset

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion.html index e2d3b9522..4c6649af0 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion

class AttitudeQuaternion(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion,
name: ostk.core.type.String,
)

Bases: CoordinateSubset

Attitude quaternion coordinate subset.

Defined with respect to a reference frame.

Constructor.

Parameters:

name (str) -- The name of the subset.

Methods

add

Add the coordinates of another state to the coordinates of this state.

default

Get the default Attitude quaternion subset.

drag_coefficient

Get the drag coefficient coordinate subset.

get_id

Get the identifier of the coordinate subset.

get_name

Get the name of the coordinate subset.

get_size

Get the size of the coordinate subset.

in_frame

Convert a Attitude quaternion from one reference frame to another.

mass

Get the mass coordinate subset.

subtract

Subtract the coordinates of another state from the coordinates of this state.

surface_area

Get the surface area coordinate subset.

add(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Add the coordinates of another state to the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The sum of the coordinates.

Return type:

numpy.ndarray

static default() → ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion

Get the default Attitude quaternion subset.

Returns:

The default Attitude quaternion subset.

Return type:

AttitudeQuaternion

static drag_coefficient() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the drag coefficient coordinate subset.

Returns:

The drag coefficient coordinate subset.

Return type:

CoordinateSubset

get_id(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the identifier of the coordinate subset.

Returns:

The identifier of the coordinate subset.

Return type:

str

get_name(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the name of the coordinate subset.

Returns:

The name of the coordinate subset.

Return type:

str

get_size(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → int

Get the size of the coordinate subset.

Returns:

The size of the coordinate subset.

Return type:

int

in_frame(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
from_frame: ostk.physics.coordinate.Frame,
to_frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Convert a Attitude quaternion from one reference frame to another.

Parameters:

  • instant (Instant) -- The instant of the conversion.

  • coordinates (numpy.ndarray) -- The Attitude quaternion to convert.

  • from_frame (str) -- The reference frame of the input Attitude quaternion.

  • to_frame (str) -- The reference frame of the output Attitude quaternion.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The Attitude quaternion in the output reference frame.

Return type:

numpy.ndarray

static mass() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the mass coordinate subset.

Returns:

The mass coordinate subset.

Return type:

CoordinateSubset

subtract(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Subtract the coordinates of another state from the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The difference of the coordinates.

Return type:

numpy.ndarray

static surface_area() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the surface area coordinate subset.

Returns:

The surface area coordinate subset.

Return type:

CoordinateSubset

\ No newline at end of file + ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion

class AttitudeQuaternion(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion,
name: ostk.core.type.String,
)

Bases: CoordinateSubset

Attitude quaternion coordinate subset.

Defined with respect to a reference frame.

Constructor.

Parameters:

name (str) -- The name of the subset.

Methods

add

Add the coordinates of another state to the coordinates of this state.

default

Get the default Attitude quaternion subset.

drag_coefficient

Get the drag coefficient coordinate subset.

get_id

Get the identifier of the coordinate subset.

get_name

Get the name of the coordinate subset.

get_size

Get the size of the coordinate subset.

in_frame

Convert a Attitude quaternion from one reference frame to another.

mass

Get the mass coordinate subset.

subtract

Subtract the coordinates of another state from the coordinates of this state.

surface_area

Get the surface area coordinate subset.

add(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Add the coordinates of another state to the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The sum of the coordinates.

Return type:

numpy.ndarray

static default() → ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion

Get the default Attitude quaternion subset.

Returns:

The default Attitude quaternion subset.

Return type:

AttitudeQuaternion

static drag_coefficient() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the drag coefficient coordinate subset.

Returns:

The drag coefficient coordinate subset.

Return type:

CoordinateSubset

get_id(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the identifier of the coordinate subset.

Returns:

The identifier of the coordinate subset.

Return type:

str

get_name(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the name of the coordinate subset.

Returns:

The name of the coordinate subset.

Return type:

str

get_size(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → int

Get the size of the coordinate subset.

Returns:

The size of the coordinate subset.

Return type:

int

in_frame(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
from_frame: ostk.physics.coordinate.Frame,
to_frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Convert a Attitude quaternion from one reference frame to another.

Parameters:

  • instant (Instant) -- The instant of the conversion.

  • coordinates (numpy.ndarray) -- The Attitude quaternion to convert.

  • from_frame (str) -- The reference frame of the input Attitude quaternion.

  • to_frame (str) -- The reference frame of the output Attitude quaternion.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The Attitude quaternion in the output reference frame.

Return type:

numpy.ndarray

static mass() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the mass coordinate subset.

Returns:

The mass coordinate subset.

Return type:

CoordinateSubset

subtract(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Subtract the coordinates of another state from the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The difference of the coordinates.

Return type:

numpy.ndarray

static surface_area() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the surface area coordinate subset.

Returns:

The surface area coordinate subset.

Return type:

CoordinateSubset

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition.html index a94f00afe..70551c57b 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition

class CartesianPosition(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition,
name: ostk.core.type.String,
)

Bases: CoordinateSubset

Cartesian position coordinate subset.

Defined with respect to a reference frame.

Constructor.

Parameters:

name (str) -- The name of the subset.

Methods

add

Add the coordinates of another state to the coordinates of this state.

default

Get the default Cartesian position subset.

drag_coefficient

Get the drag coefficient coordinate subset.

get_id

Get the identifier of the coordinate subset.

get_name

Get the name of the coordinate subset.

get_size

Get the size of the coordinate subset.

in_frame

Convert a Cartesian position from one reference frame to another.

mass

Get the mass coordinate subset.

subtract

Subtract the coordinates of another state from the coordinates of this state.

surface_area

Get the surface area coordinate subset.

add(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Add the coordinates of another state to the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The sum of the coordinates.

Return type:

numpy.ndarray

static default() → ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition

Get the default Cartesian position subset.

Returns:

The default Cartesian position subset.

Return type:

CartesianPosition

static drag_coefficient() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the drag coefficient coordinate subset.

Returns:

The drag coefficient coordinate subset.

Return type:

CoordinateSubset

get_id(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the identifier of the coordinate subset.

Returns:

The identifier of the coordinate subset.

Return type:

str

get_name(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the name of the coordinate subset.

Returns:

The name of the coordinate subset.

Return type:

str

get_size(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → int

Get the size of the coordinate subset.

Returns:

The size of the coordinate subset.

Return type:

int

in_frame(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
from_frame: ostk.physics.coordinate.Frame,
to_frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Convert a Cartesian position from one reference frame to another.

Parameters:

  • instant (Instant) -- The instant of the conversion.

  • coordinates (numpy.ndarray) -- The Cartesian position to convert.

  • from_frame (str) -- The reference frame of the input Cartesian position.

  • to_frame (str) -- The reference frame of the output Cartesian position.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The Cartesian position in the output reference frame.

Return type:

numpy.ndarray

static mass() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the mass coordinate subset.

Returns:

The mass coordinate subset.

Return type:

CoordinateSubset

subtract(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Subtract the coordinates of another state from the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The difference of the coordinates.

Return type:

numpy.ndarray

static surface_area() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the surface area coordinate subset.

Returns:

The surface area coordinate subset.

Return type:

CoordinateSubset

\ No newline at end of file + ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition

class CartesianPosition(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition,
name: ostk.core.type.String,
)

Bases: CoordinateSubset

Cartesian position coordinate subset.

Defined with respect to a reference frame.

Constructor.

Parameters:

name (str) -- The name of the subset.

Methods

add

Add the coordinates of another state to the coordinates of this state.

default

Get the default Cartesian position subset.

drag_coefficient

Get the drag coefficient coordinate subset.

get_id

Get the identifier of the coordinate subset.

get_name

Get the name of the coordinate subset.

get_size

Get the size of the coordinate subset.

in_frame

Convert a Cartesian position from one reference frame to another.

mass

Get the mass coordinate subset.

subtract

Subtract the coordinates of another state from the coordinates of this state.

surface_area

Get the surface area coordinate subset.

add(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Add the coordinates of another state to the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The sum of the coordinates.

Return type:

numpy.ndarray

static default() → ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition

Get the default Cartesian position subset.

Returns:

The default Cartesian position subset.

Return type:

CartesianPosition

static drag_coefficient() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the drag coefficient coordinate subset.

Returns:

The drag coefficient coordinate subset.

Return type:

CoordinateSubset

get_id(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the identifier of the coordinate subset.

Returns:

The identifier of the coordinate subset.

Return type:

str

get_name(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the name of the coordinate subset.

Returns:

The name of the coordinate subset.

Return type:

str

get_size(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → int

Get the size of the coordinate subset.

Returns:

The size of the coordinate subset.

Return type:

int

in_frame(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
from_frame: ostk.physics.coordinate.Frame,
to_frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Convert a Cartesian position from one reference frame to another.

Parameters:

  • instant (Instant) -- The instant of the conversion.

  • coordinates (numpy.ndarray) -- The Cartesian position to convert.

  • from_frame (str) -- The reference frame of the input Cartesian position.

  • to_frame (str) -- The reference frame of the output Cartesian position.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The Cartesian position in the output reference frame.

Return type:

numpy.ndarray

static mass() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the mass coordinate subset.

Returns:

The mass coordinate subset.

Return type:

CoordinateSubset

subtract(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Subtract the coordinates of another state from the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The difference of the coordinates.

Return type:

numpy.ndarray

static surface_area() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the surface area coordinate subset.

Returns:

The surface area coordinate subset.

Return type:

CoordinateSubset

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity.html index 274dc284e..f2b595813 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity

class CartesianVelocity(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity,
cartesian_position: ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition,
name: ostk.core.type.String,
)

Bases: CoordinateSubset

Cartesian velocity coordinate subset.

Defined with respect to a reference frame and a Cartesian position.

Constructor.

Parameters:

  • cartesian_position (CartesianPosition) -- The Cartesian position.

  • name (str) -- The name of the subset.

Methods

add

Add the coordinates of another state to the coordinates of this state.

default

Get the default Cartesian velocity subset.

drag_coefficient

Get the drag coefficient coordinate subset.

get_id

Get the identifier of the coordinate subset.

get_name

Get the name of the coordinate subset.

get_size

Get the size of the coordinate subset.

in_frame

Convert a Cartesian velocity from one reference frame to another.

mass

Get the mass coordinate subset.

subtract

Subtract the coordinates of another state from the coordinates of this state.

surface_area

Get the surface area coordinate subset.

add(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Add the coordinates of another state to the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The sum of the coordinates.

Return type:

numpy.ndarray

static default() → ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity

Get the default Cartesian velocity subset.

Returns:

The default Cartesian velocity subset.

Return type:

CartesianVelocity

static drag_coefficient() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the drag coefficient coordinate subset.

Returns:

The drag coefficient coordinate subset.

Return type:

CoordinateSubset

get_id(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the identifier of the coordinate subset.

Returns:

The identifier of the coordinate subset.

Return type:

str

get_name(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the name of the coordinate subset.

Returns:

The name of the coordinate subset.

Return type:

str

get_size(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → int

Get the size of the coordinate subset.

Returns:

The size of the coordinate subset.

Return type:

int

in_frame(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
from_frame: ostk.physics.coordinate.Frame,
to_frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Convert a Cartesian velocity from one reference frame to another.

Parameters:

  • instant (Instant) -- The instant of the conversion.

  • coordinates (numpy.ndarray) -- The Cartesian velocity to convert.

  • from_frame (str) -- The reference frame of the input Cartesian velocity.

  • to_frame (str) -- The reference frame of the output Cartesian velocity.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The Cartesian velocity in the output reference frame.

Return type:

numpy.ndarray

static mass() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the mass coordinate subset.

Returns:

The mass coordinate subset.

Return type:

CoordinateSubset

subtract(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Subtract the coordinates of another state from the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The difference of the coordinates.

Return type:

numpy.ndarray

static surface_area() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the surface area coordinate subset.

Returns:

The surface area coordinate subset.

Return type:

CoordinateSubset

\ No newline at end of file + ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity

class CartesianVelocity(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity,
cartesian_position: ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition,
name: ostk.core.type.String,
)

Bases: CoordinateSubset

Cartesian velocity coordinate subset.

Defined with respect to a reference frame and a Cartesian position.

Constructor.

Parameters:

  • cartesian_position (CartesianPosition) -- The Cartesian position.

  • name (str) -- The name of the subset.

Methods

add

Add the coordinates of another state to the coordinates of this state.

default

Get the default Cartesian velocity subset.

drag_coefficient

Get the drag coefficient coordinate subset.

get_id

Get the identifier of the coordinate subset.

get_name

Get the name of the coordinate subset.

get_size

Get the size of the coordinate subset.

in_frame

Convert a Cartesian velocity from one reference frame to another.

mass

Get the mass coordinate subset.

subtract

Subtract the coordinates of another state from the coordinates of this state.

surface_area

Get the surface area coordinate subset.

add(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Add the coordinates of another state to the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The sum of the coordinates.

Return type:

numpy.ndarray

static default() → ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity

Get the default Cartesian velocity subset.

Returns:

The default Cartesian velocity subset.

Return type:

CartesianVelocity

static drag_coefficient() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the drag coefficient coordinate subset.

Returns:

The drag coefficient coordinate subset.

Return type:

CoordinateSubset

get_id(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the identifier of the coordinate subset.

Returns:

The identifier of the coordinate subset.

Return type:

str

get_name(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → ostk.core.type.String

Get the name of the coordinate subset.

Returns:

The name of the coordinate subset.

Return type:

str

get_size(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
) → int

Get the size of the coordinate subset.

Returns:

The size of the coordinate subset.

Return type:

int

in_frame(
self: ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
from_frame: ostk.physics.coordinate.Frame,
to_frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Convert a Cartesian velocity from one reference frame to another.

Parameters:

  • instant (Instant) -- The instant of the conversion.

  • coordinates (numpy.ndarray) -- The Cartesian velocity to convert.

  • from_frame (str) -- The reference frame of the input Cartesian velocity.

  • to_frame (str) -- The reference frame of the output Cartesian velocity.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The Cartesian velocity in the output reference frame.

Return type:

numpy.ndarray

static mass() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the mass coordinate subset.

Returns:

The mass coordinate subset.

Return type:

CoordinateSubset

subtract(
self: ostk.astrodynamics.trajectory.state.CoordinateSubset,
instant: ostk.physics.time.Instant,
coordinates: numpy.ndarray[numpy.float64[m, 1]],
another_coordinates: numpy.ndarray[numpy.float64[m, 1]],
frame: ostk.physics.coordinate.Frame,
coordinate_broker: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → numpy.ndarray[numpy.float64[m, 1]]

Subtract the coordinates of another state from the coordinates of this state.

Parameters:

  • instant (Instant) -- The instant of the state.

  • coordinates (numpy.ndarray) -- The coordinates of this state.

  • another_coordinates (numpy.ndarray) -- The coordinates of the other state.

  • frame (Frame) -- The reference frame of the coordinates.

  • coordinate_broker (CoordinateBroker) -- The coordinate broker.

Returns:

The difference of the coordinates.

Return type:

numpy.ndarray

static surface_area() → ostk.astrodynamics.trajectory.state.CoordinateSubset

Get the surface area coordinate subset.

Returns:

The surface area coordinate subset.

Return type:

CoordinateSubset

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.utilities.compute_aer.html b/_build/html/_autosummary/ostk.astrodynamics.utilities.compute_aer.html index ee3760655..54b573410 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.utilities.compute_aer.html +++ b/_build/html/_autosummary/ostk.astrodynamics.utilities.compute_aer.html @@ -1 +1 @@ - ostk.astrodynamics.utilities.compute_aer — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.utilities.compute_aer

compute_aer(
instant: Instant,
from_position: Position,
to_position: Position,
environment: Environment,
) → tuple[float, float, float]

Return [azimuth (degrees), elevation (degrees), range (meters)] from Instant and Positions (observer, target).

\ No newline at end of file + ostk.astrodynamics.utilities.compute_aer — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.utilities.compute_aer

compute_aer(
instant: Instant,
from_position: Position,
to_position: Position,
environment: Environment,
) → tuple[float, float, float]

Return [azimuth (degrees), elevation (degrees), range (meters)] from Instant and Positions (observer, target).

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.utilities.compute_time_lla_aer_state.html b/_build/html/_autosummary/ostk.astrodynamics.utilities.compute_time_lla_aer_state.html index bc47c16be..4e5a0f816 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.utilities.compute_time_lla_aer_state.html +++ b/_build/html/_autosummary/ostk.astrodynamics.utilities.compute_time_lla_aer_state.html @@ -1 +1 @@ - ostk.astrodynamics.utilities.compute_time_lla_aer_state — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.utilities.compute_time_lla_aer_state

compute_time_lla_aer_state(
state: State,
from_position: Position,
environment: Environment,
) → tuple[Instant, float, float, float, float, float, float]

Return [instant, latitude, longitude, altitude, azimuth, elevation, range] from State and observer Position.

\ No newline at end of file + ostk.astrodynamics.utilities.compute_time_lla_aer_state — Open Space Toolkit Astrodynamics Skip to content
\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.utilities.compute_trajectory_geometry.html b/_build/html/_autosummary/ostk.astrodynamics.utilities.compute_trajectory_geometry.html index b2175d47f..e67a8d45b 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.utilities.compute_trajectory_geometry.html +++ b/_build/html/_autosummary/ostk.astrodynamics.utilities.compute_trajectory_geometry.html @@ -1 +1 @@ - ostk.astrodynamics.utilities.compute_trajectory_geometry — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.utilities.compute_trajectory_geometry

compute_trajectory_geometry(
trajectory: Trajectory,
interval: Interval,
) → list[tuple[float, float, float]]

Return [latitude (degrees), longitude (degrees), altitude (meters)] values along a Trajectory during Interval.

\ No newline at end of file + ostk.astrodynamics.utilities.compute_trajectory_geometry — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.utilities.compute_trajectory_geometry

compute_trajectory_geometry(
trajectory: Trajectory,
interval: Interval,
) → list[tuple[float, float, float]]

Return [latitude (degrees), longitude (degrees), altitude (meters)] values along a Trajectory during Interval.

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.utilities.lla_from_position.html b/_build/html/_autosummary/ostk.astrodynamics.utilities.lla_from_position.html index d75a0d385..110b210e1 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.utilities.lla_from_position.html +++ b/_build/html/_autosummary/ostk.astrodynamics.utilities.lla_from_position.html @@ -1 +1 @@ - ostk.astrodynamics.utilities.lla_from_position — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.utilities.lla_from_position

lla_from_position(
position: Position,
instant: Instant | None = None,
) → LLA

Return LLA from position and instant.

\ No newline at end of file + ostk.astrodynamics.utilities.lla_from_position — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.utilities.lla_from_position

lla_from_position(
position: Position,
instant: Instant | None = None,
) → LLA

Return LLA from position and instant.

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.utilities.position_from_lla.html b/_build/html/_autosummary/ostk.astrodynamics.utilities.position_from_lla.html index e59f98ff9..09e6086c0 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.utilities.position_from_lla.html +++ b/_build/html/_autosummary/ostk.astrodynamics.utilities.position_from_lla.html @@ -1 +1 @@ - ostk.astrodynamics.utilities.position_from_lla — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.utilities.position_from_lla

position_from_lla(
lla: LLA,
) → Position

Return position from lla.

\ No newline at end of file + ostk.astrodynamics.utilities.position_from_lla — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.utilities.position_from_lla

position_from_lla(
lla: LLA,
) → Position

Return position from lla.

\ No newline at end of file diff --git a/_build/html/_autosummary/ostk.astrodynamics.viewer.Viewer.html b/_build/html/_autosummary/ostk.astrodynamics.viewer.Viewer.html index 8ee1d09b8..8d8b99fc6 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.viewer.Viewer.html +++ b/_build/html/_autosummary/ostk.astrodynamics.viewer.Viewer.html @@ -1 +1 @@ - ostk.astrodynamics.viewer.Viewer — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.viewer.Viewer

class Viewer(
interval: Interval,
cesium_token: str | None = None,
width: str = '1500px',
height: str = '800px',
)

Bases: object

Methods

add_line

Add line to Viewer.

add_profile

Add Profile to Viewer.

add_target

Add target to Viewer.

render

Render Viewer as HTML string.

Attributes

interval

add_profile(
profile: Profile,
step: Duration,
show_orbital_track: bool = False,
cesium_asset_id: int | None = None,
sensors: list[Sensor] | None = None,
show_xyz_axes: bool = False,
) → None

Add Profile to Viewer.

Parameters:

  • profile (Profile) -- Profile to be added.

  • step (Duration) -- Step between two consecutive states.

  • show_orbital_track (bool, optional) -- Whether to show the orbital track. Defaults to False.

  • cesium_asset_id (int, optional) -- The Cesium asset ID. Defaults to None.

  • sensors (list[Sensor], optional) -- Sensors to be added to the asset. Defaults to None.

  • show_xyz_axes (bool, optional) -- Whether to show the XYZ axes. Defaults to False.

add_target(
position: Position,
size: int | None = None,
color: str | None = None,
) → None

Add target to Viewer.

Parameters:

  • position (Position) -- Target position.

  • size (int, optional) -- Target size. Defaults to None.

  • color (str, optional) -- Target color. Defaults to None.

add_line(
positions: list[Position],
size: int | None = None,
color: str | None = None,
) → None

Add line to Viewer.

Parameters:

  • positions (list[Position]) -- Line positions.

  • size (int, optional) -- Line size. Defaults to None.

  • color (str, optional) -- Line color. Defaults to None.

render() → str

Render Viewer as HTML string.

Returns:

Rendered HTML string.

Return type:

str

\ No newline at end of file + ostk.astrodynamics.viewer.Viewer — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.viewer.Viewer

class Viewer(
interval: Interval,
cesium_token: str | None = None,
width: str = '1500px',
height: str = '800px',
)

Bases: object

Methods

add_line

Add line to Viewer.

add_profile

Add Profile to Viewer.

add_target

Add target to Viewer.

render

Render Viewer as HTML string.

Attributes

interval

add_profile(
profile: Profile,
step: Duration,
show_orbital_track: bool = False,
cesium_asset_id: int | None = None,
sensors: list[Sensor] | None = None,
show_xyz_axes: bool = False,
) → None

Add Profile to Viewer.

Parameters:

  • profile (Profile) -- Profile to be added.

  • step (Duration) -- Step between two consecutive states.

  • show_orbital_track (bool, optional) -- Whether to show the orbital track. Defaults to False.

  • cesium_asset_id (int, optional) -- The Cesium asset ID. Defaults to None.

  • sensors (list[Sensor], optional) -- Sensors to be added to the asset. Defaults to None.

  • show_xyz_axes (bool, optional) -- Whether to show the XYZ axes. Defaults to False.

add_target(
position: Position,
size: int | None = None,
color: str | None = None,
) → None

Add target to Viewer.

Parameters:

  • position (Position) -- Target position.

  • size (int, optional) -- Target size. Defaults to None.

  • color (str, optional) -- Target color. Defaults to None.

add_line(
positions: list[Position],
size: int | None = None,
color: str | None = None,
) → None

Add line to Viewer.

Parameters:

  • positions (list[Position]) -- Line positions.

  • size (int, optional) -- Line size. Defaults to None.

  • color (str, optional) -- Line color. Defaults to None.

render() → str

Render Viewer as HTML string.

Returns:

Rendered HTML string.

Return type:

str

\ No newline at end of file diff --git a/_build/html/_images/0dcaf71eae73f82ba16dadc6633b510fc12755a25213d93c591e7f7775dea9f4.svg b/_build/html/_images/251d0b9a31af6b6720287c14f538774fae13bcc2acd660f63ac617340e6f43ec.svg similarity index 99% rename from _build/html/_images/0dcaf71eae73f82ba16dadc6633b510fc12755a25213d93c591e7f7775dea9f4.svg rename to _build/html/_images/251d0b9a31af6b6720287c14f538774fae13bcc2acd660f63ac617340e6f43ec.svg index f47f7f497..97bf164d2 100644 --- a/_build/html/_images/0dcaf71eae73f82ba16dadc6633b510fc12755a25213d93c591e7f7775dea9f4.svg +++ b/_build/html/_images/251d0b9a31af6b6720287c14f538774fae13bcc2acd660f63ac617340e6f43ec.svg @@ -1 +1 @@ - \ No newline at end of file + \ No newline at end of file diff --git a/_build/jupyter_execute/772229b5152bc471f04e4c34e117cbc3aaf22fbf33e10496b9f4e4883bc8f1ea.svg b/_build/html/_images/347ce6263d6bdb7d60f3f9bf82f1b29df474c9e16f49d3241a1c47b87f2af987.svg similarity index 99% rename from _build/jupyter_execute/772229b5152bc471f04e4c34e117cbc3aaf22fbf33e10496b9f4e4883bc8f1ea.svg rename to _build/html/_images/347ce6263d6bdb7d60f3f9bf82f1b29df474c9e16f49d3241a1c47b87f2af987.svg index 65eeb08bd..83b0009a7 100644 --- a/_build/jupyter_execute/772229b5152bc471f04e4c34e117cbc3aaf22fbf33e10496b9f4e4883bc8f1ea.svg +++ b/_build/html/_images/347ce6263d6bdb7d60f3f9bf82f1b29df474c9e16f49d3241a1c47b87f2af987.svg @@ -1 +1 @@ -trace 1 \ No newline at end of file +trace 1 \ No newline at end of file diff --git a/_build/jupyter_execute/863f32555d46e0ec3ee1c652d70476f92e56fcaa31c2cce0711d8647024f40c5.svg b/_build/html/_images/5fce014f9c456b4d705e907725aafee04842a5a3b0743d26eea6ac2f4fcb75fb.svg similarity index 99% rename from _build/jupyter_execute/863f32555d46e0ec3ee1c652d70476f92e56fcaa31c2cce0711d8647024f40c5.svg rename to _build/html/_images/5fce014f9c456b4d705e907725aafee04842a5a3b0743d26eea6ac2f4fcb75fb.svg index 1357ea445..57646fc6c 100644 --- a/_build/jupyter_execute/863f32555d46e0ec3ee1c652d70476f92e56fcaa31c2cce0711d8647024f40c5.svg +++ b/_build/html/_images/5fce014f9c456b4d705e907725aafee04842a5a3b0743d26eea6ac2f4fcb75fb.svg @@ -1 +1 @@ - \ No newline at end of file + \ No newline at end of file diff --git a/_build/html/_images/5ba32a05a93323cebf5f94c970cfce12cf861bb3106333e092648883f21158f4.svg b/_build/html/_images/993f9d05ea20ffa811776076ca2dec165f4131564382df41d841bf624ea0f9de.svg similarity index 99% rename from _build/html/_images/5ba32a05a93323cebf5f94c970cfce12cf861bb3106333e092648883f21158f4.svg rename to _build/html/_images/993f9d05ea20ffa811776076ca2dec165f4131564382df41d841bf624ea0f9de.svg index ca3ca817b..6a9a568e7 100644 --- a/_build/html/_images/5ba32a05a93323cebf5f94c970cfce12cf861bb3106333e092648883f21158f4.svg +++ b/_build/html/_images/993f9d05ea20ffa811776076ca2dec165f4131564382df41d841bf624ea0f9de.svg @@ -1 +1 @@ - \ No newline at end of file + \ No newline at end of file diff --git a/_build/html/_images/d578584f85e6a5a5245b581dc521d9f955ac98d1e6a1a90bd3c1eaffde43f943.svg b/_build/html/_images/c09ff20d60d705a86280b5ec46c7cafd06658f5752af67451ed84e96eb1f4504.svg similarity index 99% rename from _build/html/_images/d578584f85e6a5a5245b581dc521d9f955ac98d1e6a1a90bd3c1eaffde43f943.svg rename to _build/html/_images/c09ff20d60d705a86280b5ec46c7cafd06658f5752af67451ed84e96eb1f4504.svg index 339a3cff6..c23e3a536 100644 --- a/_build/html/_images/d578584f85e6a5a5245b581dc521d9f955ac98d1e6a1a90bd3c1eaffde43f943.svg +++ b/_build/html/_images/c09ff20d60d705a86280b5ec46c7cafd06658f5752af67451ed84e96eb1f4504.svg @@ -1 +1 @@ - \ No newline at end of file + \ No newline at end of file diff --git a/_build/html/_notebooks/Area Coverage.html b/_build/html/_notebooks/Area Coverage.html index ee2121645..8318f1ae5 100644 --- a/_build/html/_notebooks/Area Coverage.html +++ b/_build/html/_notebooks/Area Coverage.html @@ -428,7 +428,7 @@ ) figure.show("svg") -
../_images/0dcaf71eae73f82ba16dadc6633b510fc12755a25213d93c591e7f7775dea9f4.svg

3D plot:

data = []
+
../_images/251d0b9a31af6b6720287c14f538774fae13bcc2acd660f63ac617340e6f43ec.svg

3D plot:

data = []
 
 # Satellite Ground Track
 
@@ -511,4 +511,4 @@
 )
 
 figure.show("svg")
-
../_images/863f32555d46e0ec3ee1c652d70476f92e56fcaa31c2cce0711d8647024f40c5.svg
\ No newline at end of file +
../_images/5fce014f9c456b4d705e907725aafee04842a5a3b0743d26eea6ac2f4fcb75fb.svg
\ No newline at end of file diff --git a/_build/html/_notebooks/Custom Window Generation.html b/_build/html/_notebooks/Custom Window Generation.html index 7650bc445..05ffe36de 100644 --- a/_build/html/_notebooks/Custom Window Generation.html +++ b/_build/html/_notebooks/Custom Window Generation.html @@ -160,4 +160,4 @@ mode="markers+lines", ) figure.show("svg") -
../_images/772229b5152bc471f04e4c34e117cbc3aaf22fbf33e10496b9f4e4883bc8f1ea.svg
\ No newline at end of file +
../_images/347ce6263d6bdb7d60f3f9bf82f1b29df474c9e16f49d3241a1c47b87f2af987.svg
\ No newline at end of file diff --git a/_build/html/_notebooks/Sensor Modeling.html b/_build/html/_notebooks/Sensor Modeling.html index e787d8cc9..8f1799f62 100644 --- a/_build/html/_notebooks/Sensor Modeling.html +++ b/_build/html/_notebooks/Sensor Modeling.html @@ -305,7 +305,7 @@ ) figure.show("svg") -
../_images/5ba32a05a93323cebf5f94c970cfce12cf861bb3106333e092648883f21158f4.svg

3D plot:

data = []
+
../_images/993f9d05ea20ffa811776076ca2dec165f4131564382df41d841bf624ea0f9de.svg

3D plot:

data = []
 
 data.append(
     go.Scattergeo(
@@ -352,7 +352,7 @@
 )
 
 figure.show("svg")
-
../_images/d578584f85e6a5a5245b581dc521d9f955ac98d1e6a1a90bd3c1eaffde43f943.svg

Satellite body frame orientation plot:

def earth_data(earth):
+
../_images/c09ff20d60d705a86280b5ec46c7cafd06658f5752af67451ed84e96eb1f4504.svg

Satellite body frame orientation plot:

def earth_data(earth):
     theta = np.linspace(0, 2 * np.pi, 30)
     phi = np.linspace(0, np.pi, 30)
 
diff --git a/_build/html/_notebooks/Station-keeping Sequence.html b/_build/html/_notebooks/Station-keeping Sequence.html
index 3366ccba5..c933227a4 100644
--- a/_build/html/_notebooks/Station-keeping Sequence.html	
+++ b/_build/html/_notebooks/Station-keeping Sequence.html	
@@ -127,7 +127,7 @@
 )
 
sol = sequence.solve(state, 2)
 states = sol.get_states()
-
[2024-05-08 15:29:37.894356] [0x00007f018897c280] [debug]   Solving Segment:
+
[2024-05-15 16:57:14.851844] [0x00007f6743286280] [debug]   Solving Segment:
 -- Segment -----------------------------------------------------------------------------------------
     Name:                                    Coast                                    
     Type:                                    Coast                                    
@@ -148,7 +148,7 @@
     Integration relative tolerance:          9.9999999999999998e-13                   
     Integration absolute tolerance:          9.9999999999999998e-13                   
 ----------------------------------------------------------------------------------------------------
-
[2024-05-08 15:29:38.658581] [0x00007f018897c280] [debug]   
+
[2024-05-15 16:57:15.623754] [0x00007f6743286280] [debug]   
 -- Segment Solution --------------------------------------------------------------------------------
     Name:                                    Coast - Mean SMA crossing - coast - 0    
     Condition satisfied:                     True                                     
@@ -159,7 +159,7 @@
 ----------------------------------------------------------------------------------------------------
 
 
-[2024-05-08 15:29:38.658777] [0x00007f018897c280] [debug]   Solving Segment:
+[2024-05-15 16:57:15.623954] [0x00007f6743286280] [debug]   Solving Segment:
 -- Segment -----------------------------------------------------------------------------------------
     Name:                                    Maneuver                                 
     Type:                                    Maneuver                                 
@@ -204,7 +204,7 @@
     Integration relative tolerance:          9.9999999999999998e-13                   
     Integration absolute tolerance:          9.9999999999999998e-13                   
 ----------------------------------------------------------------------------------------------------
-
[2024-05-08 15:29:39.570278] [0x00007f018897c280] [debug]   
+
[2024-05-15 16:57:16.546301] [0x00007f6743286280] [debug]   
 -- Segment Solution --------------------------------------------------------------------------------
     Name:                                    Maneuver - Mean SMA crossing - thrust - 0 
     Condition satisfied:                     True                                     
@@ -218,7 +218,7 @@
 ----------------------------------------------------------------------------------------------------
 
 
-[2024-05-08 15:29:39.570514] [0x00007f018897c280] [debug]   Solving Segment:
+[2024-05-15 16:57:16.546532] [0x00007f6743286280] [debug]   Solving Segment:
 -- Segment -----------------------------------------------------------------------------------------
     Name:                                    Coast                                    
     Type:                                    Coast                                    
@@ -239,7 +239,7 @@
     Integration relative tolerance:          9.9999999999999998e-13                   
     Integration absolute tolerance:          9.9999999999999998e-13                   
 ----------------------------------------------------------------------------------------------------
-
[2024-05-08 15:29:42.626245] [0x00007f018897c280] [debug]   
+
[2024-05-15 16:57:19.648189] [0x00007f6743286280] [debug]   
 -- Segment Solution --------------------------------------------------------------------------------
     Name:                                    Coast - Mean SMA crossing - coast - 1    
     Condition satisfied:                     True                                     
@@ -250,7 +250,7 @@
 ----------------------------------------------------------------------------------------------------
 
 
-[2024-05-08 15:29:42.626818] [0x00007f018897c280] [debug]   Solving Segment:
+[2024-05-15 16:57:19.648770] [0x00007f6743286280] [debug]   Solving Segment:
 -- Segment -----------------------------------------------------------------------------------------
     Name:                                    Maneuver                                 
     Type:                                    Maneuver                                 
@@ -295,7 +295,7 @@
     Integration relative tolerance:          9.9999999999999998e-13                   
     Integration absolute tolerance:          9.9999999999999998e-13                   
 ----------------------------------------------------------------------------------------------------
-
[2024-05-08 15:29:43.544916] [0x00007f018897c280] [debug]   
+
[2024-05-15 16:57:20.585195] [0x00007f6743286280] [debug]   
 -- Segment Solution --------------------------------------------------------------------------------
     Name:                                    Maneuver - Mean SMA crossing - thrust - 1 
     Condition satisfied:                     True                                     
@@ -306,8 +306,7 @@
     Initial mass:                            109.98712414601253 [kg]                  
     Final mass:                              109.97436777064368 [kg]                  
     Total mass consumed:                     0.012756375368851991 [kg]                
-------------------------------------------------------
-
----------------------------------------------
+----------------------------------------------------------------------------------------------------
 
model = Tabulated(states, 0, Tabulated.InterpolationType.BarycentricRational)
 
---------------------------------------------------------------------------
 AttributeError                            Traceback (most recent call last)
diff --git a/_build/html/_notebooks/Visualize Satellite Trajectory (Cesium).html b/_build/html/_notebooks/Visualize Satellite Trajectory (Cesium).html
index eefa0574a..39cfbfdde 100644
--- a/_build/html/_notebooks/Visualize Satellite Trajectory (Cesium).html	
+++ b/_build/html/_notebooks/Visualize Satellite Trajectory (Cesium).html	
@@ -2,8 +2,8 @@
 
 !{sys.executable} -m pip install git+https://github.com/open-space-collective/cesiumpy.git#egg=cesiumpy
 
Collecting cesiumpy
-  Cloning https://github.com/open-space-collective/cesiumpy.git to /tmp/pip-install-zye6o7x2/cesiumpy_21e431fb96a54654b143be4dd8c2d905
-  Running command git clone --filter=blob:none --quiet https://github.com/open-space-collective/cesiumpy.git /tmp/pip-install-zye6o7x2/cesiumpy_21e431fb96a54654b143be4dd8c2d905
+  Cloning https://github.com/open-space-collective/cesiumpy.git to /tmp/pip-install-gu01cwfr/cesiumpy_e50c8e43a91944649036bb06e931a235
+  Running command git clone --filter=blob:none --quiet https://github.com/open-space-collective/cesiumpy.git /tmp/pip-install-gu01cwfr/cesiumpy_e50c8e43a91944649036bb06e931a235
 
  Resolved https://github.com/open-space-collective/cesiumpy.git to commit d72945ab0816cd459c5083c817fa94c0b563c46a
   Running command git submodule update --init --recursive -q
 
  Preparing metadata (setup.py) ... ?25l-
@@ -11,7 +11,7 @@
 ?25hRequirement already satisfied: six in /usr/local/lib/python3.11/site-packages (from cesiumpy) (1.16.0)
 Requirement already satisfied: traitlets in /usr/local/lib/python3.11/site-packages (from cesiumpy) (5.14.3)
 Requirement already satisfied: geopy>=1.11.0 in /usr/local/lib/python3.11/site-packages (from cesiumpy) (2.4.1)
-
Requirement already satisfied: geographiclib<3,>=1.52 in /usr/local/lib/python3.11/site-packages (from geopy>=1.11.0->cesiumpy) (2.0)
+Requirement already satisfied: geographiclib<3,>=1.52 in /usr/local/lib/python3.11/site-packages (from geopy>=1.11.0->cesiumpy) (2.0)
 
WARNING: Running pip as the 'root' user can result in broken permissions and conflicting behaviour with the system package manager. It is recommended to use a virtual environment instead: https://pip.pypa.io/warnings/venv
 
 
import os
@@ -66,4 +66,4 @@
     ],
 )
 
viewer
-
\ No newline at end of file +
\ No newline at end of file diff --git a/_build/html/searchindex.js b/_build/html/searchindex.js index fa05c02c3..639e8d323 100644 --- a/_build/html/searchindex.js +++ b/_build/html/searchindex.js @@ -1 +1 @@ -Search.setIndex({"alltitles": {"Access": [[111, "access"], [111, "id1"]], "Access Computation": [[111, "access-computation"]], "Alternatives": [[196, "alternatives"]], "Altitude + Eccentricity Station-keeping Sequence": [[125, "altitude-eccentricity-station-keeping-sequence"]], "Area Coverage": [[112, "area-coverage"]], "Area Target": [[112, "area-target"]], "Benchmark": [[196, "benchmark"]], "Beta angle condition": [[115, "beta-angle-condition"]], "Build": [[196, "build"]], "C++": [[196, "c"]], "C++ API Documentation": [[128, "c-api-documentation"]], "Class list": [[195, "class-list"]], "Class ostk::astrodynamics::Access": [[129, "class-ostk-astrodynamics-access"]], "Class ostk::astrodynamics::Dynamics": [[130, "class-ostk-astrodynamics-dynamics"]], "Class ostk::astrodynamics::EventCondition": [[131, "class-ostk-astrodynamics-eventcondition"]], "Class ostk::astrodynamics::GuidanceLaw": [[132, "class-ostk-astrodynamics-guidancelaw"]], "Class ostk::astrodynamics::RootSolver": [[133, "class-ostk-astrodynamics-rootsolver"]], "Class ostk::astrodynamics::Trajectory": [[134, "class-ostk-astrodynamics-trajectory"]], "Class ostk::astrodynamics::access::Generator": [[135, "class-ostk-astrodynamics-access-generator"]], "Class ostk::astrodynamics::access::GeneratorContext": [[136, "class-ostk-astrodynamics-access-generatorcontext"]], "Class ostk::astrodynamics::conjunction::message::ccsds::CDM": [[137, "class-ostk-astrodynamics-conjunction-message-ccsds-cdm"]], "Class ostk::astrodynamics::dynamics::AtmosphericDrag": [[138, "class-ostk-astrodynamics-dynamics-atmosphericdrag"]], "Class ostk::astrodynamics::dynamics::CentralBodyGravity": [[139, "class-ostk-astrodynamics-dynamics-centralbodygravity"]], "Class ostk::astrodynamics::dynamics::PositionDerivative": [[140, "class-ostk-astrodynamics-dynamics-positionderivative"]], "Class ostk::astrodynamics::dynamics::Tabulated": [[141, "class-ostk-astrodynamics-dynamics-tabulated"]], "Class ostk::astrodynamics::dynamics::ThirdBodyGravity": [[142, "class-ostk-astrodynamics-dynamics-thirdbodygravity"]], "Class ostk::astrodynamics::dynamics::Thruster": [[143, "class-ostk-astrodynamics-dynamics-thruster"]], "Class ostk::astrodynamics::eventcondition::AngularCondition": [[144, "class-ostk-astrodynamics-eventcondition-angularcondition"]], "Class ostk::astrodynamics::eventcondition::BooleanCondition": [[145, "class-ostk-astrodynamics-eventcondition-booleancondition"]], "Class ostk::astrodynamics::eventcondition::COECondition": [[146, "class-ostk-astrodynamics-eventcondition-coecondition"]], "Class ostk::astrodynamics::eventcondition::InstantCondition": [[147, "class-ostk-astrodynamics-eventcondition-instantcondition"]], "Class ostk::astrodynamics::eventcondition::LogicalCondition": [[148, "class-ostk-astrodynamics-eventcondition-logicalcondition"]], "Class ostk::astrodynamics::eventcondition::RealCondition": [[149, "class-ostk-astrodynamics-eventcondition-realcondition"]], "Class ostk::astrodynamics::flight::Maneuver": [[150, "class-ostk-astrodynamics-flight-maneuver"]], "Class ostk::astrodynamics::flight::Profile": [[151, "class-ostk-astrodynamics-flight-profile"]], "Class ostk::astrodynamics::flight::System": [[152, "class-ostk-astrodynamics-flight-system"]], "Class ostk::astrodynamics::flight::profile::Model": [[153, "class-ostk-astrodynamics-flight-profile-model"]], "Class ostk::astrodynamics::flight::profile::model::Tabulated": [[154, "class-ostk-astrodynamics-flight-profile-model-tabulated"]], "Class ostk::astrodynamics::flight::profile::model::Transform": [[155, "class-ostk-astrodynamics-flight-profile-model-transform"]], "Class ostk::astrodynamics::flight::system::PropulsionSystem": [[156, "class-ostk-astrodynamics-flight-system-propulsionsystem"]], "Class ostk::astrodynamics::flight::system::SatelliteSystem": [[157, "class-ostk-astrodynamics-flight-system-satellitesystem"]], "Class ostk::astrodynamics::flight::system::SatelliteSystemBuilder": [[158, "class-ostk-astrodynamics-flight-system-satellitesystembuilder"]], "Class ostk::astrodynamics::guidancelaw::ConstantThrust": [[159, "class-ostk-astrodynamics-guidancelaw-constantthrust"]], "Class ostk::astrodynamics::guidancelaw::QLaw": [[160, "class-ostk-astrodynamics-guidancelaw-qlaw"]], "Class ostk::astrodynamics::solver::FiniteDifferenceSolver": [[161, "class-ostk-astrodynamics-solver-finitedifferencesolver"]], "Class ostk::astrodynamics::solver::TemporalConditionSolver": [[162, "class-ostk-astrodynamics-solver-temporalconditionsolver"]], "Class ostk::astrodynamics::trajectory::LocalOrbitalFrameDirection": [[163, "class-ostk-astrodynamics-trajectory-localorbitalframedirection"]], "Class ostk::astrodynamics::trajectory::LocalOrbitalFrameFactory": [[164, "class-ostk-astrodynamics-trajectory-localorbitalframefactory"]], "Class ostk::astrodynamics::trajectory::LocalOrbitalFrameTransformProvider": [[165, "class-ostk-astrodynamics-trajectory-localorbitalframetransformprovider"]], "Class ostk::astrodynamics::trajectory::Model": [[166, "class-ostk-astrodynamics-trajectory-model"]], "Class ostk::astrodynamics::trajectory::Orbit": [[167, "class-ostk-astrodynamics-trajectory-orbit"]], "Class ostk::astrodynamics::trajectory::Propagator": [[168, "class-ostk-astrodynamics-trajectory-propagator"]], "Class ostk::astrodynamics::trajectory::Segment": [[169, "class-ostk-astrodynamics-trajectory-segment"]], "Class ostk::astrodynamics::trajectory::Sequence": [[170, "class-ostk-astrodynamics-trajectory-sequence"]], "Class ostk::astrodynamics::trajectory::State": [[171, "class-ostk-astrodynamics-trajectory-state"]], "Class ostk::astrodynamics::trajectory::StateBuilder": [[172, "class-ostk-astrodynamics-trajectory-statebuilder"]], "Class ostk::astrodynamics::trajectory::model::Static": [[173, "class-ostk-astrodynamics-trajectory-model-static"]], "Class ostk::astrodynamics::trajectory::model::Tabulated": [[174, "class-ostk-astrodynamics-trajectory-model-tabulated"]], "Class ostk::astrodynamics::trajectory::orbit::Model": [[175, "class-ostk-astrodynamics-trajectory-orbit-model"]], "Class ostk::astrodynamics::trajectory::orbit::Pass": [[176, "class-ostk-astrodynamics-trajectory-orbit-pass"]], "Class ostk::astrodynamics::trajectory::orbit::message::spacex::OPM": [[177, "class-ostk-astrodynamics-trajectory-orbit-message-spacex-opm"]], "Class ostk::astrodynamics::trajectory::orbit::model::Kepler": [[178, "class-ostk-astrodynamics-trajectory-orbit-model-kepler"]], "Class ostk::astrodynamics::trajectory::orbit::model::Propagated": [[179, "class-ostk-astrodynamics-trajectory-orbit-model-propagated"]], "Class ostk::astrodynamics::trajectory::orbit::model::SGP4": [[180, "class-ostk-astrodynamics-trajectory-orbit-model-sgp4"]], "Class ostk::astrodynamics::trajectory::orbit::model::SGP4::Impl": [[181, "class-ostk-astrodynamics-trajectory-orbit-model-sgp4-impl"]], "Class ostk::astrodynamics::trajectory::orbit::model::Tabulated": [[182, "class-ostk-astrodynamics-trajectory-orbit-model-tabulated"]], "Class ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMean": [[183, "class-ostk-astrodynamics-trajectory-orbit-model-blm-brouwerlyddanemean"]], "Class ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanLong": [[184, "class-ostk-astrodynamics-trajectory-orbit-model-blm-brouwerlyddanemeanlong"]], "Class ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanShort": [[185, "class-ostk-astrodynamics-trajectory-orbit-model-blm-brouwerlyddanemeanshort"]], "Class ostk::astrodynamics::trajectory::orbit::model::kepler::COE": [[186, "class-ostk-astrodynamics-trajectory-orbit-model-kepler-coe"]], "Class ostk::astrodynamics::trajectory::orbit::model::sgp4::TLE": [[187, "class-ostk-astrodynamics-trajectory-orbit-model-sgp4-tle"]], "Class ostk::astrodynamics::trajectory::state::CoordinateBroker": [[188, "class-ostk-astrodynamics-trajectory-state-coordinatebroker"]], "Class ostk::astrodynamics::trajectory::state::CoordinateSubset": [[189, "class-ostk-astrodynamics-trajectory-state-coordinatesubset"]], "Class ostk::astrodynamics::trajectory::state::NumericalSolver": [[190, "class-ostk-astrodynamics-trajectory-state-numericalsolver"]], "Class ostk::astrodynamics::trajectory::state::coordinatesubset::AngularVelocity": [[191, "class-ostk-astrodynamics-trajectory-state-coordinatesubset-angularvelocity"]], "Class ostk::astrodynamics::trajectory::state::coordinatesubset::AttitudeQuaternion": [[192, "class-ostk-astrodynamics-trajectory-state-coordinatesubset-attitudequaternion"]], "Class ostk::astrodynamics::trajectory::state::coordinatesubset::CartesianPosition": [[193, 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"define-satellites"]], "Define Scenario": [[117, "define-scenario"]], "Define our condition": [[116, "define-our-condition"]], "Define our solver": [[116, "define-our-solver"]], "Dependencies": [[196, "dependencies"]], "Development Environment": [[196, "development-environment"]], "Docker Images": [[196, "docker-images"]], "Documentation": [[196, "documentation"]], "Eccentricity targeting": [[123, "eccentricity-targeting"]], "Eclipse condition": [[115, "eclipse-condition"]], "Environment": [[111, "environment"], [112, "environment"], [124, "environment"]], "Examples {#Examples}": [[0, "examples-examples"]], "Find RF Interference Accesses": [[117, "find-rf-interference-accesses"]], "Getting Started": [[196, "getting-started"]], "Inclination targeting": [[123, "inclination-targeting"]], "Installation": [[196, "installation"]], "Interference Filter": [[117, "interference-filter"]], "JupyterLab": [[196, "jupyterlab"]], "License": [[196, "license"]], "Maneuver segment": [[125, "maneuver-segment"]], "Multiple targets": [[123, "multiple-targets"]], "OSTk Cross-Platform Validation Against GMAT/Orekit (Mission Sequence Scenario 1)": [[118, "ostk-cross-platform-validation-against-gmat-orekit-mission-sequence-scenario-1"]], "OSTk Cross-Platform Validation Against GMAT/Orekit (Mission Sequence Scenario 2)": [[119, "ostk-cross-platform-validation-against-gmat-orekit-mission-sequence-scenario-2"]], "OSTk Cross-Platform Validation Against GMAT/Orekit (Mission Sequence Scenario 3)": [[120, "ostk-cross-platform-validation-against-gmat-orekit-mission-sequence-scenario-3"]], "OSTk Cross-Platform Validation Against GMAT/Orekit (Mission Sequence Scenario 4)": [[121, "ostk-cross-platform-validation-against-gmat-orekit-mission-sequence-scenario-4"]], "Open Space Toolkit \u25b8 Astrodynamics": [[196, "open-space-toolkit-astrodynamics"]], "Orbit Computation": [[122, "orbit-computation"]], "Orbit Station-keeping with QLaw": [[123, "orbit-station-keeping-with-qlaw"]], "Origin": [[111, "origin"]], "Output": [[111, "output"], [122, "output"]], "Plots": [[117, "plots"]], "Process Cross Platform Results": [[118, "process-cross-platform-results"], [119, "process-cross-platform-results"], [120, "process-cross-platform-results"], [121, "process-cross-platform-results"]], "Propagate with OSTk": [[118, "propagate-with-ostk"], [119, "propagate-with-ostk"], [120, "propagate-with-ostk"], [121, "propagate-with-ostk"]], "Propagation": [[113, "propagation"]], "Python": [[196, "python"]], "Python API Documentation": [[198, "python-api-documentation"]], "Right Ascension of Ascending Node targeting": [[123, "right-ascension-of-ascending-node-targeting"]], "Run the analysis": [[117, "run-the-analysis"]], "Running the Validation Tests": [[196, "running-the-validation-tests"]], "SGP4": [[122, "sgp4"]], "SMA + Ecc": [[123, "sma-ecc"]], "SMA + Ecc + Inc + Raan targeting": [[123, "sma-ecc-inc-raan-targeting"]], "SMA + Ecc + Inclination": [[123, "sma-ecc-inclination"]], "SMA targeting": [[123, "sma-targeting"]], "Satellite": [[112, "satellite"], [124, "satellite"]], "Scenario Definition": [[196, "scenario-definition"]], "Semi Major Axis + Inclination": [[123, "semi-major-axis-inclination"]], "Sensor": [[112, "sensor"], [124, "sensor"]], "Sensor Modeling": [[124, "sensor-modeling"]], "Sequence": [[125, "sequence"], [126, "sequence"]], "Set up Comparison Files": [[118, "set-up-comparison-files"], [119, "set-up-comparison-files"], [120, "set-up-comparison-files"], [121, "set-up-comparison-files"]], "Setup": [[111, "setup"], [112, "setup"], [117, "setup"], [122, "setup"], [124, "setup"], [196, "setup"]], "Setup Comparison Scenario in OSTk": [[118, "setup-comparison-scenario-in-ostk"], [119, "setup-comparison-scenario-in-ostk"], [120, "setup-comparison-scenario-in-ostk"], [121, "setup-comparison-scenario-in-ostk"]], "Setup Dynamics, initial state and Satellite System": [[113, "setup-dynamics-initial-state-and-satellite-system"], [126, "setup-dynamics-initial-state-and-satellite-system"]], "Setup environment, initial state and Satellite System": [[123, "setup-environment-initial-state-and-satellite-system"], [125, "setup-environment-initial-state-and-satellite-system"]], "Setup {#Setup}": [[0, "setup-setup"]], "Special Thanks": [[196, "special-thanks"]], "Station-keeping Sequence": [[126, "station-keeping-sequence"]], "Target": [[111, "target"], [124, "target"]], "Target Intersection": [[112, "target-intersection"]], "Test": [[196, "test"]], "Trajectory RMS error vs GMAT run in the GCRF frame": [[118, "trajectory-rms-error-vs-gmat-run-in-the-gcrf-frame"], [119, "trajectory-rms-error-vs-gmat-run-in-the-gcrf-frame"], [120, "trajectory-rms-error-vs-gmat-run-in-the-gcrf-frame"], [121, "trajectory-rms-error-vs-gmat-run-in-the-gcrf-frame"]], "Tutorial": [[0, "tutorial"]], "Tutorial Notebooks": [[197, "tutorial-notebooks"]], "Tutorials": [[196, "tutorials"]], "User inputs": [[113, "user-inputs"], [123, "user-inputs"], [125, "user-inputs"], [126, "user-inputs"]], "Utility functions": [[123, "utility-functions"]], "Validation": [[196, "validation"]], "Validation Plots": [[118, "validation-plots"], [119, "validation-plots"], [120, "validation-plots"], [121, "validation-plots"]], "Visualization": [[112, "visualization"], [124, "visualization"]], "Visualize Satellite States (Cesium)": [[127, "visualize-satellite-states-cesium"]], "Window generation": [[116, "window-generation"]], "iPython": [[196, "ipython"]], "ostk.astrodynamics": [[1, "module-ostk.astrodynamics"]], "ostk.astrodynamics.Access": [[2, "ostk-astrodynamics-access"]], "ostk.astrodynamics.Dynamics": [[3, "ostk-astrodynamics-dynamics"]], "ostk.astrodynamics.EventCondition": [[4, "ostk-astrodynamics-eventcondition"]], "ostk.astrodynamics.GuidanceLaw": [[5, "ostk-astrodynamics-guidancelaw"]], "ostk.astrodynamics.RootSolver": [[6, "ostk-astrodynamics-rootsolver"]], "ostk.astrodynamics.Trajectory": [[7, "ostk-astrodynamics-trajectory"]], "ostk.astrodynamics.access": [[8, "module-ostk.astrodynamics.access"]], "ostk.astrodynamics.access.Generator": [[9, "ostk-astrodynamics-access-generator"]], "ostk.astrodynamics.conjunction.message.ccsds": [[10, "module-ostk.astrodynamics.conjunction.message.ccsds"]], "ostk.astrodynamics.conjunction.message.ccsds.CDM": [[11, "ostk-astrodynamics-conjunction-message-ccsds-cdm"]], "ostk.astrodynamics.converters": [[12, "module-ostk.astrodynamics.converters"]], "ostk.astrodynamics.converters.coerce_to_datetime": [[13, "ostk-astrodynamics-converters-coerce-to-datetime"]], "ostk.astrodynamics.converters.coerce_to_duration": [[14, "ostk-astrodynamics-converters-coerce-to-duration"]], "ostk.astrodynamics.converters.coerce_to_instant": [[15, "ostk-astrodynamics-converters-coerce-to-instant"]], "ostk.astrodynamics.converters.coerce_to_interval": [[16, "ostk-astrodynamics-converters-coerce-to-interval"]], "ostk.astrodynamics.converters.coerce_to_iso": [[17, "ostk-astrodynamics-converters-coerce-to-iso"]], "ostk.astrodynamics.converters.coerce_to_position": [[18, "ostk-astrodynamics-converters-coerce-to-position"]], "ostk.astrodynamics.converters.coerce_to_quaternion": [[19, "ostk-astrodynamics-converters-coerce-to-quaternion"]], "ostk.astrodynamics.converters.coerce_to_velocity": [[20, "ostk-astrodynamics-converters-coerce-to-velocity"]], "ostk.astrodynamics.display": [[21, "module-ostk.astrodynamics.display"]], "ostk.astrodynamics.display.AccessesPlot": [[22, "ostk-astrodynamics-display-accessesplot"]], "ostk.astrodynamics.display.convert_to_ground_track_plotting_data": [[23, "ostk-astrodynamics-display-convert-to-ground-track-plotting-data"]], "ostk.astrodynamics.display.create_2d_map": [[24, "ostk-astrodynamics-display-create-2d-map"]], "ostk.astrodynamics.display.create_3d_globe": [[25, "ostk-astrodynamics-display-create-3d-globe"]], "ostk.astrodynamics.display.create_plotly_figure": [[26, "ostk-astrodynamics-display-create-plotly-figure"]], "ostk.astrodynamics.dynamics": [[27, "module-ostk.astrodynamics.dynamics"]], "ostk.astrodynamics.dynamics.AtmosphericDrag": [[28, "ostk-astrodynamics-dynamics-atmosphericdrag"]], "ostk.astrodynamics.dynamics.CentralBodyGravity": [[29, "ostk-astrodynamics-dynamics-centralbodygravity"]], "ostk.astrodynamics.dynamics.PositionDerivative": [[30, "ostk-astrodynamics-dynamics-positionderivative"]], "ostk.astrodynamics.dynamics.Tabulated": [[31, "ostk-astrodynamics-dynamics-tabulated"]], "ostk.astrodynamics.dynamics.ThirdBodyGravity": [[32, "ostk-astrodynamics-dynamics-thirdbodygravity"]], "ostk.astrodynamics.dynamics.Thruster": [[33, "ostk-astrodynamics-dynamics-thruster"]], "ostk.astrodynamics.event_condition": [[34, "module-ostk.astrodynamics.event_condition"]], "ostk.astrodynamics.event_condition.AngularCondition": [[35, "ostk-astrodynamics-event-condition-angularcondition"]], "ostk.astrodynamics.event_condition.BooleanCondition": [[36, "ostk-astrodynamics-event-condition-booleancondition"]], "ostk.astrodynamics.event_condition.COECondition": [[37, "ostk-astrodynamics-event-condition-coecondition"]], "ostk.astrodynamics.event_condition.InstantCondition": [[38, "ostk-astrodynamics-event-condition-instantcondition"]], "ostk.astrodynamics.event_condition.LogicalCondition": [[39, "ostk-astrodynamics-event-condition-logicalcondition"]], "ostk.astrodynamics.event_condition.RealCondition": [[40, "ostk-astrodynamics-event-condition-realcondition"]], "ostk.astrodynamics.flight": [[41, "module-ostk.astrodynamics.flight"]], "ostk.astrodynamics.flight.Maneuver": [[42, "ostk-astrodynamics-flight-maneuver"]], "ostk.astrodynamics.flight.Profile": [[43, "ostk-astrodynamics-flight-profile"]], "ostk.astrodynamics.flight.System": [[44, "ostk-astrodynamics-flight-system"]], "ostk.astrodynamics.flight.profile": [[45, "module-ostk.astrodynamics.flight.profile"]], "ostk.astrodynamics.flight.profile.Model": [[46, 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"ostk.astrodynamics.conjunction.message.ccsds.CDM.Data.area_pc", false]], "area_srp (cdm.data property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Data.area_srp", false]], "as_kepler() (kepler method)": [[78, "ostk.astrodynamics.trajectory.orbit.model.Kepler.as_kepler", false]], "as_kepler() (orbitmodel method)": [[72, "ostk.astrodynamics.trajectory.orbit.OrbitModel.as_kepler", false]], "as_kepler() (propagated method)": [[79, "ostk.astrodynamics.trajectory.orbit.model.Propagated.as_kepler", false]], "as_kepler() (sgp4 method)": [[80, "ostk.astrodynamics.trajectory.orbit.model.SGP4.as_kepler", false]], "as_kepler() (tabulated method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.Tabulated.as_kepler", false]], "as_propagated() (kepler method)": [[78, "ostk.astrodynamics.trajectory.orbit.model.Kepler.as_propagated", false]], "as_propagated() (orbitmodel method)": [[72, "ostk.astrodynamics.trajectory.orbit.OrbitModel.as_propagated", false]], "as_propagated() (propagated method)": [[79, "ostk.astrodynamics.trajectory.orbit.model.Propagated.as_propagated", false]], "as_propagated() (sgp4 method)": [[80, "ostk.astrodynamics.trajectory.orbit.model.SGP4.as_propagated", false]], "as_propagated() (tabulated method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.Tabulated.as_propagated", false]], "as_sgp4() (kepler method)": [[78, "ostk.astrodynamics.trajectory.orbit.model.Kepler.as_sgp4", false]], "as_sgp4() (orbitmodel method)": [[72, "ostk.astrodynamics.trajectory.orbit.OrbitModel.as_sgp4", false]], "as_sgp4() (propagated method)": [[79, "ostk.astrodynamics.trajectory.orbit.model.Propagated.as_sgp4", false]], "as_sgp4() (sgp4 method)": [[80, "ostk.astrodynamics.trajectory.orbit.model.SGP4.as_sgp4", false]], "as_sgp4() (tabulated method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.Tabulated.as_sgp4", false]], "atmospheric_model (cdm.metadata property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Metadata.atmospheric_model", false]], "atmosphericdrag (class in ostk.astrodynamics.dynamics)": [[28, "ostk.astrodynamics.dynamics.AtmosphericDrag", false]], "attitudequaternion (class in ostk.astrodynamics.trajectory.state.coordinate_subset)": [[95, "ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion", false]], "b (qlaw.parameters property)": [[56, "ostk.astrodynamics.guidance_law.QLaw.Parameters.b", false]], "ballistic_coefficient (opm.deployment property)": [[75, "ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.Deployment.ballistic_coefficient", false]], "bisection() (rootsolver method)": [[6, "ostk.astrodynamics.RootSolver.bisection", false]], "booleancondition (class in ostk.astrodynamics.event_condition)": [[36, "ostk.astrodynamics.event_condition.BooleanCondition", false]], "booleancondition.criterion (class in ostk.astrodynamics.event_condition)": [[36, "ostk.astrodynamics.event_condition.BooleanCondition.Criterion", false]], "booleancondition.target (class in ostk.astrodynamics.event_condition)": [[36, "ostk.astrodynamics.event_condition.BooleanCondition.Target", false]], "booleancondition.target.type (class in ostk.astrodynamics.event_condition)": [[36, "ostk.astrodynamics.event_condition.BooleanCondition.Target.Type", false]], "bracket_and_solve() (rootsolver method)": [[6, "ostk.astrodynamics.RootSolver.bracket_and_solve", false]], "brouwerlyddanemean (class in ostk.astrodynamics.trajectory.orbit.model)": [[77, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean", false]], "brouwerlyddanemean.anomalytype (class in ostk.astrodynamics.trajectory.orbit.model)": [[77, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.AnomalyType", false]], "brouwerlyddanemean.element (class in ostk.astrodynamics.trajectory.orbit.model)": [[77, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.Element", false]], "brouwerlyddanemeanlong (class in ostk.astrodynamics.trajectory.orbit.model.brouwerlyddanemean)": [[83, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong", false]], "brouwerlyddanemeanlong.anomalytype (class in ostk.astrodynamics.trajectory.orbit.model.brouwerlyddanemean)": [[83, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.AnomalyType", false]], "brouwerlyddanemeanlong.element (class in ostk.astrodynamics.trajectory.orbit.model.brouwerlyddanemean)": [[83, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.Element", false]], "brouwerlyddanemeanshort (class in ostk.astrodynamics.trajectory.orbit.model.brouwerlyddanemean)": [[84, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort", false]], "brouwerlyddanemeanshort.anomalytype (class in ostk.astrodynamics.trajectory.orbit.model.brouwerlyddanemean)": [[84, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.AnomalyType", false]], "brouwerlyddanemeanshort.element (class in ostk.astrodynamics.trajectory.orbit.model.brouwerlyddanemean)": [[84, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.Element", false]], "build() (satellitesystembuilder method)": [[53, "ostk.astrodynamics.flight.system.SatelliteSystemBuilder.build", false]], "build() (statebuilder method)": [[70, "ostk.astrodynamics.trajectory.StateBuilder.build", false]], "calculate_average_specific_impulse() (maneuver method)": [[42, "ostk.astrodynamics.flight.Maneuver.calculate_average_specific_impulse", false]], "calculate_average_thrust() (maneuver method)": [[42, "ostk.astrodynamics.flight.Maneuver.calculate_average_thrust", false]], "calculate_delta_mass() (maneuver method)": [[42, "ostk.astrodynamics.flight.Maneuver.calculate_delta_mass", false]], "calculate_delta_v() (maneuver method)": [[42, "ostk.astrodynamics.flight.Maneuver.calculate_delta_v", false]], "calculate_revolution_number_at() (kepler method)": [[78, "ostk.astrodynamics.trajectory.orbit.model.Kepler.calculate_revolution_number_at", false]], "calculate_revolution_number_at() (orbitmodel method)": [[72, "ostk.astrodynamics.trajectory.orbit.OrbitModel.calculate_revolution_number_at", false]], "calculate_revolution_number_at() (propagated method)": [[79, "ostk.astrodynamics.trajectory.orbit.model.Propagated.calculate_revolution_number_at", false]], "calculate_revolution_number_at() (sgp4 method)": [[80, "ostk.astrodynamics.trajectory.orbit.model.SGP4.calculate_revolution_number_at", false]], "calculate_revolution_number_at() (tabulated method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.Tabulated.calculate_revolution_number_at", false]], "calculate_state_at() (kepler method)": [[78, "ostk.astrodynamics.trajectory.orbit.model.Kepler.calculate_state_at", false]], "calculate_state_at() (model method)": [[46, "ostk.astrodynamics.flight.profile.Model.calculate_state_at", false], [64, "ostk.astrodynamics.trajectory.Model.calculate_state_at", false]], "calculate_state_at() (orbitmodel method)": [[72, "ostk.astrodynamics.trajectory.orbit.OrbitModel.calculate_state_at", false]], "calculate_state_at() (propagated method)": [[79, "ostk.astrodynamics.trajectory.orbit.model.Propagated.calculate_state_at", false]], "calculate_state_at() (propagator method)": [[66, "ostk.astrodynamics.trajectory.Propagator.calculate_state_at", false]], "calculate_state_at() (sgp4 method)": [[80, "ostk.astrodynamics.trajectory.orbit.model.SGP4.calculate_state_at", false]], "calculate_state_at() (tabulated method)": [[48, "ostk.astrodynamics.flight.profile.model.Tabulated.calculate_state_at", false], [81, "ostk.astrodynamics.trajectory.orbit.model.Tabulated.calculate_state_at", false]], "calculate_state_at() (transform method)": [[49, "ostk.astrodynamics.flight.profile.model.Transform.calculate_state_at", false]], "calculate_state_to_condition() (propagator method)": [[66, "ostk.astrodynamics.trajectory.Propagator.calculate_state_to_condition", false]], "calculate_states_at() (model method)": [[46, "ostk.astrodynamics.flight.profile.Model.calculate_states_at", false], [64, "ostk.astrodynamics.trajectory.Model.calculate_states_at", false]], "calculate_states_at() (propagated method)": [[79, "ostk.astrodynamics.trajectory.orbit.model.Propagated.calculate_states_at", false]], "calculate_states_at() (propagator method)": [[66, "ostk.astrodynamics.trajectory.Propagator.calculate_states_at", false]], "calculate_states_at() (segment.solution method)": [[67, "ostk.astrodynamics.trajectory.Segment.Solution.calculate_states_at", false]], "calculate_states_at() (sequence.solution method)": [[68, "ostk.astrodynamics.trajectory.Sequence.Solution.calculate_states_at", false]], "calculate_states_at() (tabulated method)": [[48, "ostk.astrodynamics.flight.profile.model.Tabulated.calculate_states_at", false], [81, "ostk.astrodynamics.trajectory.orbit.model.Tabulated.calculate_states_at", false]], "calculate_states_at() (transform method)": [[49, "ostk.astrodynamics.flight.profile.model.Transform.calculate_states_at", false]], "calculate_thrust_acceleration_at() (constantthrust method)": [[55, "ostk.astrodynamics.guidance_law.ConstantThrust.calculate_thrust_acceleration_at", false]], "calculate_thrust_acceleration_at() (guidancelaw method)": [[5, "ostk.astrodynamics.GuidanceLaw.calculate_thrust_acceleration_at", false]], "calculate_thrust_acceleration_at() (qlaw method)": [[56, "ostk.astrodynamics.guidance_law.QLaw.calculate_thrust_acceleration_at", false]], "can_parse() (tle static method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE.can_parse", false]], "cartesian() (brouwerlyddanemean static method)": [[77, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.cartesian", false]], "cartesian() (brouwerlyddanemeanlong static method)": [[83, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.cartesian", false]], "cartesian() (brouwerlyddanemeanshort static method)": [[84, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.cartesian", false]], "cartesian() (coe static method)": [[86, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.cartesian", false]], "cartesianposition (class in ostk.astrodynamics.trajectory.state.coordinate_subset)": [[96, "ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition", false]], "cartesianvelocity (class in ostk.astrodynamics.trajectory.state.coordinate_subset)": [[97, "ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity", false]], "catalog_name (cdm.metadata property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Metadata.catalog_name", false]], "ccsds_cdm_version (cdm.header property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Header.ccsds_cdm_version", false]], "cd_area_over_mass (cdm.data property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Data.cd_area_over_mass", false]], "cdm (class in ostk.astrodynamics.conjunction.message.ccsds)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM", false]], "cdm.data (class in ostk.astrodynamics.conjunction.message.ccsds)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Data", false]], "cdm.header (class in ostk.astrodynamics.conjunction.message.ccsds)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Header", false]], "cdm.metadata (class in ostk.astrodynamics.conjunction.message.ccsds)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Metadata", false]], "cdm.objecttype (class in ostk.astrodynamics.conjunction.message.ccsds)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.ObjectType", false]], "cdm.relativemetadata (class in ostk.astrodynamics.conjunction.message.ccsds)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.RelativeMetadata", false]], "centralbodygravity (class in ostk.astrodynamics.dynamics)": [[29, "ostk.astrodynamics.dynamics.CentralBodyGravity", false]], "circular() (orbit static method)": [[65, "ostk.astrodynamics.trajectory.Orbit.circular", false]], "circular_equatorial() (orbit static method)": [[65, "ostk.astrodynamics.trajectory.Orbit.circular_equatorial", false]], "clear_dynamics() (propagator method)": [[66, "ostk.astrodynamics.trajectory.Propagator.clear_dynamics", false]], "coast() (segment static method)": [[67, "ostk.astrodynamics.trajectory.Segment.coast", false]], "coe (class in ostk.astrodynamics.trajectory.orbit.model.kepler)": [[86, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE", false]], "coe() (brouwerlyddanemeanlong static method)": [[83, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.COE", false]], "coe() (brouwerlyddanemeanshort static method)": [[84, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.COE", false]], "coe.anomalytype (class in ostk.astrodynamics.trajectory.orbit.model.kepler)": [[86, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.AnomalyType", false]], "coe.element (class in ostk.astrodynamics.trajectory.orbit.model.kepler)": [[86, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element", false]], "coecondition (class in ostk.astrodynamics.event_condition)": [[37, "ostk.astrodynamics.event_condition.COECondition", false]], "coerce_to_datetime() (in module ostk.astrodynamics.converters)": [[13, "ostk.astrodynamics.converters.coerce_to_datetime", false]], "coerce_to_duration() (in module ostk.astrodynamics.converters)": [[14, "ostk.astrodynamics.converters.coerce_to_duration", false]], "coerce_to_instant() (in module ostk.astrodynamics.converters)": [[15, "ostk.astrodynamics.converters.coerce_to_instant", false]], "coerce_to_interval() (in module ostk.astrodynamics.converters)": [[16, "ostk.astrodynamics.converters.coerce_to_interval", false]], "coerce_to_iso() (in module ostk.astrodynamics.converters)": [[17, "ostk.astrodynamics.converters.coerce_to_iso", false]], "coerce_to_position() (in module ostk.astrodynamics.converters)": [[18, "ostk.astrodynamics.converters.coerce_to_position", false]], "coerce_to_quaternion() (in module ostk.astrodynamics.converters)": [[19, "ostk.astrodynamics.converters.coerce_to_quaternion", false]], "coerce_to_velocity() (in module ostk.astrodynamics.converters)": [[20, "ostk.astrodynamics.converters.coerce_to_velocity", false]], "collision_probability (cdm.relativemetadata property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.RelativeMetadata.collision_probability", false]], "collision_probability_method (cdm.relativemetadata property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.RelativeMetadata.collision_probability_method", false]], "comment (cdm.header property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Header.comment", false]], "comment (cdm.metadata property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Metadata.comment", false]], "comment (cdm.relativemetadata property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.RelativeMetadata.comment", false]], "compute_accesses() (generator method)": [[9, "ostk.astrodynamics.access.Generator.compute_accesses", false]], "compute_aer() (in module ostk.astrodynamics.utilities)": [[99, "ostk.astrodynamics.utilities.compute_aer", false]], "compute_angular_momentum() (brouwerlyddanemean static method)": [[77, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.compute_angular_momentum", false]], "compute_angular_momentum() (brouwerlyddanemeanlong static method)": [[83, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.compute_angular_momentum", false]], "compute_angular_momentum() (brouwerlyddanemeanshort static method)": [[84, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.compute_angular_momentum", false]], "compute_angular_momentum() (coe static method)": [[86, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.compute_angular_momentum", false]], "compute_contribution() (atmosphericdrag method)": [[28, "ostk.astrodynamics.dynamics.AtmosphericDrag.compute_contribution", false]], "compute_contribution() (centralbodygravity method)": [[29, "ostk.astrodynamics.dynamics.CentralBodyGravity.compute_contribution", false]], "compute_contribution() (dynamics method)": [[3, "ostk.astrodynamics.Dynamics.compute_contribution", false]], "compute_contribution() (positionderivative method)": [[30, "ostk.astrodynamics.dynamics.PositionDerivative.compute_contribution", false]], "compute_contribution() (tabulated method)": [[31, "ostk.astrodynamics.dynamics.Tabulated.compute_contribution", false]], "compute_contribution() (thirdbodygravity method)": [[32, "ostk.astrodynamics.dynamics.ThirdBodyGravity.compute_contribution", false]], "compute_contribution() (thruster method)": [[33, "ostk.astrodynamics.dynamics.Thruster.compute_contribution", false]], "compute_delta_mass() (segment.solution method)": [[67, "ostk.astrodynamics.trajectory.Segment.Solution.compute_delta_mass", false]], "compute_delta_mass() (sequence.solution method)": [[68, "ostk.astrodynamics.trajectory.Sequence.Solution.compute_delta_mass", false]], "compute_delta_v() (segment.solution method)": [[67, "ostk.astrodynamics.trajectory.Segment.Solution.compute_delta_v", false]], "compute_delta_v() (sequence.solution method)": [[68, "ostk.astrodynamics.trajectory.Sequence.Solution.compute_delta_v", false]], "compute_gradient() (finitedifferencesolver method)": [[58, "ostk.astrodynamics.solver.FiniteDifferenceSolver.compute_gradient", false]], "compute_jacobian() (finitedifferencesolver method)": [[58, "ostk.astrodynamics.solver.FiniteDifferenceSolver.compute_jacobian", false]], "compute_passes() (orbit static method)": [[65, "ostk.astrodynamics.trajectory.Orbit.compute_passes", false]], "compute_radial_distance() (brouwerlyddanemean static method)": [[77, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.compute_radial_distance", false]], "compute_radial_distance() (brouwerlyddanemeanlong static method)": [[83, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.compute_radial_distance", false]], "compute_radial_distance() (brouwerlyddanemeanshort static method)": [[84, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.compute_radial_distance", false]], "compute_radial_distance() (coe static method)": [[86, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.compute_radial_distance", false]], "compute_semi_latus_rectum() (brouwerlyddanemean static method)": [[77, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.compute_semi_latus_rectum", false]], "compute_semi_latus_rectum() (brouwerlyddanemeanlong static method)": [[83, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.compute_semi_latus_rectum", false]], "compute_semi_latus_rectum() (brouwerlyddanemeanshort static method)": [[84, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.compute_semi_latus_rectum", false]], "compute_semi_latus_rectum() (coe static method)": [[86, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.compute_semi_latus_rectum", false]], "compute_time_lla_aer_state() (in module ostk.astrodynamics.utilities)": [[100, "ostk.astrodynamics.utilities.compute_time_lla_aer_state", false]], "compute_trajectory_geometry() (in module ostk.astrodynamics.utilities)": [[101, "ostk.astrodynamics.utilities.compute_trajectory_geometry", false]], "condition_is_satisfied (numericalsolver.conditionsolution property)": [[92, 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[111, 112, 123, 124], "temporalconditionsolv": [59, 162], "test": 196, "thank": 196, "thirdbodygrav": [32, 142], "thrust": 114, "thruster": [33, 143], "tle": [88, 187], "toler": 196, "toolkit": 196, "trajectori": [7, 60, 61, 62, 63, 64, 65, 66, 67, 68, 69, 70, 71, 72, 73, 74, 75, 76, 77, 78, 79, 80, 81, 82, 83, 84, 85, 86, 87, 88, 89, 90, 91, 92, 93, 94, 95, 96, 97, 118, 119, 120, 121, 134, 163, 164, 165, 166, 167, 168, 169, 170, 171, 172, 173, 174, 175, 176, 177, 178, 179, 180, 181, 182, 183, 184, 185, 186, 187, 188, 189, 190, 191, 192, 193, 194], "transform": [49, 155], "tutori": [0, 196, 197], "ubuntu": 196, "up": [118, 119, 120, 121], "user": [113, 123, 125, 126], "util": [98, 99, 100, 101, 102, 103, 104, 105, 123], "v": [118, 119, 120, 121], "valid": [118, 119, 120, 121, 196], "viewer": [106, 107, 108, 109, 110], "visual": [112, 124, 127], "window": 116}}) \ No newline at end of file +Search.setIndex({"alltitles": {"Access": [[111, "access"], [111, "id1"]], "Access Computation": [[111, "access-computation"]], "Alternatives": [[196, "alternatives"]], "Altitude + Eccentricity Station-keeping Sequence": [[125, "altitude-eccentricity-station-keeping-sequence"]], "Area Coverage": [[112, "area-coverage"]], "Area Target": [[112, "area-target"]], "Benchmark": [[196, "benchmark"]], "Beta angle condition": [[115, "beta-angle-condition"]], "Build": [[196, "build"]], "C++": [[196, "c"]], "C++ API Documentation": [[128, "c-api-documentation"]], "Class list": [[195, "class-list"]], "Class ostk::astrodynamics::Access": [[129, "class-ostk-astrodynamics-access"]], "Class ostk::astrodynamics::Dynamics": [[130, "class-ostk-astrodynamics-dynamics"]], "Class ostk::astrodynamics::EventCondition": [[131, "class-ostk-astrodynamics-eventcondition"]], "Class ostk::astrodynamics::GuidanceLaw": [[132, "class-ostk-astrodynamics-guidancelaw"]], "Class ostk::astrodynamics::RootSolver": [[133, "class-ostk-astrodynamics-rootsolver"]], "Class ostk::astrodynamics::Trajectory": [[134, "class-ostk-astrodynamics-trajectory"]], "Class ostk::astrodynamics::access::Generator": [[135, "class-ostk-astrodynamics-access-generator"]], "Class ostk::astrodynamics::access::GeneratorContext": [[136, "class-ostk-astrodynamics-access-generatorcontext"]], "Class ostk::astrodynamics::conjunction::message::ccsds::CDM": [[137, "class-ostk-astrodynamics-conjunction-message-ccsds-cdm"]], "Class ostk::astrodynamics::dynamics::AtmosphericDrag": [[138, "class-ostk-astrodynamics-dynamics-atmosphericdrag"]], "Class ostk::astrodynamics::dynamics::CentralBodyGravity": [[139, "class-ostk-astrodynamics-dynamics-centralbodygravity"]], "Class ostk::astrodynamics::dynamics::PositionDerivative": [[140, "class-ostk-astrodynamics-dynamics-positionderivative"]], "Class ostk::astrodynamics::dynamics::Tabulated": [[141, "class-ostk-astrodynamics-dynamics-tabulated"]], "Class ostk::astrodynamics::dynamics::ThirdBodyGravity": [[142, "class-ostk-astrodynamics-dynamics-thirdbodygravity"]], "Class ostk::astrodynamics::dynamics::Thruster": [[143, "class-ostk-astrodynamics-dynamics-thruster"]], "Class ostk::astrodynamics::eventcondition::AngularCondition": [[144, "class-ostk-astrodynamics-eventcondition-angularcondition"]], "Class ostk::astrodynamics::eventcondition::BooleanCondition": [[145, "class-ostk-astrodynamics-eventcondition-booleancondition"]], "Class ostk::astrodynamics::eventcondition::COECondition": [[146, "class-ostk-astrodynamics-eventcondition-coecondition"]], "Class ostk::astrodynamics::eventcondition::InstantCondition": [[147, "class-ostk-astrodynamics-eventcondition-instantcondition"]], "Class ostk::astrodynamics::eventcondition::LogicalCondition": [[148, "class-ostk-astrodynamics-eventcondition-logicalcondition"]], "Class ostk::astrodynamics::eventcondition::RealCondition": [[149, "class-ostk-astrodynamics-eventcondition-realcondition"]], "Class ostk::astrodynamics::flight::Maneuver": [[150, "class-ostk-astrodynamics-flight-maneuver"]], "Class ostk::astrodynamics::flight::Profile": [[151, "class-ostk-astrodynamics-flight-profile"]], "Class ostk::astrodynamics::flight::System": [[152, "class-ostk-astrodynamics-flight-system"]], "Class ostk::astrodynamics::flight::profile::Model": [[153, "class-ostk-astrodynamics-flight-profile-model"]], "Class ostk::astrodynamics::flight::profile::model::Tabulated": [[154, "class-ostk-astrodynamics-flight-profile-model-tabulated"]], "Class ostk::astrodynamics::flight::profile::model::Transform": [[155, "class-ostk-astrodynamics-flight-profile-model-transform"]], "Class ostk::astrodynamics::flight::system::PropulsionSystem": [[156, "class-ostk-astrodynamics-flight-system-propulsionsystem"]], "Class ostk::astrodynamics::flight::system::SatelliteSystem": [[157, "class-ostk-astrodynamics-flight-system-satellitesystem"]], "Class ostk::astrodynamics::flight::system::SatelliteSystemBuilder": [[158, "class-ostk-astrodynamics-flight-system-satellitesystembuilder"]], "Class ostk::astrodynamics::guidancelaw::ConstantThrust": [[159, "class-ostk-astrodynamics-guidancelaw-constantthrust"]], "Class ostk::astrodynamics::guidancelaw::QLaw": [[160, "class-ostk-astrodynamics-guidancelaw-qlaw"]], "Class ostk::astrodynamics::solver::FiniteDifferenceSolver": [[161, "class-ostk-astrodynamics-solver-finitedifferencesolver"]], "Class ostk::astrodynamics::solver::TemporalConditionSolver": [[162, "class-ostk-astrodynamics-solver-temporalconditionsolver"]], "Class ostk::astrodynamics::trajectory::LocalOrbitalFrameDirection": [[163, "class-ostk-astrodynamics-trajectory-localorbitalframedirection"]], "Class ostk::astrodynamics::trajectory::LocalOrbitalFrameFactory": [[164, "class-ostk-astrodynamics-trajectory-localorbitalframefactory"]], "Class ostk::astrodynamics::trajectory::LocalOrbitalFrameTransformProvider": [[165, "class-ostk-astrodynamics-trajectory-localorbitalframetransformprovider"]], "Class ostk::astrodynamics::trajectory::Model": [[166, "class-ostk-astrodynamics-trajectory-model"]], "Class ostk::astrodynamics::trajectory::Orbit": [[167, "class-ostk-astrodynamics-trajectory-orbit"]], "Class ostk::astrodynamics::trajectory::Propagator": [[168, "class-ostk-astrodynamics-trajectory-propagator"]], "Class ostk::astrodynamics::trajectory::Segment": [[169, "class-ostk-astrodynamics-trajectory-segment"]], "Class ostk::astrodynamics::trajectory::Sequence": [[170, "class-ostk-astrodynamics-trajectory-sequence"]], "Class ostk::astrodynamics::trajectory::State": [[171, "class-ostk-astrodynamics-trajectory-state"]], "Class ostk::astrodynamics::trajectory::StateBuilder": [[172, "class-ostk-astrodynamics-trajectory-statebuilder"]], "Class ostk::astrodynamics::trajectory::model::Static": [[173, "class-ostk-astrodynamics-trajectory-model-static"]], "Class ostk::astrodynamics::trajectory::model::Tabulated": [[174, "class-ostk-astrodynamics-trajectory-model-tabulated"]], "Class ostk::astrodynamics::trajectory::orbit::Model": [[175, "class-ostk-astrodynamics-trajectory-orbit-model"]], "Class ostk::astrodynamics::trajectory::orbit::Pass": [[176, "class-ostk-astrodynamics-trajectory-orbit-pass"]], "Class ostk::astrodynamics::trajectory::orbit::message::spacex::OPM": [[177, "class-ostk-astrodynamics-trajectory-orbit-message-spacex-opm"]], "Class ostk::astrodynamics::trajectory::orbit::model::Kepler": [[178, "class-ostk-astrodynamics-trajectory-orbit-model-kepler"]], "Class ostk::astrodynamics::trajectory::orbit::model::Propagated": [[179, "class-ostk-astrodynamics-trajectory-orbit-model-propagated"]], "Class ostk::astrodynamics::trajectory::orbit::model::SGP4": [[180, "class-ostk-astrodynamics-trajectory-orbit-model-sgp4"]], "Class ostk::astrodynamics::trajectory::orbit::model::SGP4::Impl": [[181, "class-ostk-astrodynamics-trajectory-orbit-model-sgp4-impl"]], "Class ostk::astrodynamics::trajectory::orbit::model::Tabulated": [[182, "class-ostk-astrodynamics-trajectory-orbit-model-tabulated"]], "Class ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMean": [[183, "class-ostk-astrodynamics-trajectory-orbit-model-blm-brouwerlyddanemean"]], "Class ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanLong": [[184, "class-ostk-astrodynamics-trajectory-orbit-model-blm-brouwerlyddanemeanlong"]], "Class ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanShort": [[185, "class-ostk-astrodynamics-trajectory-orbit-model-blm-brouwerlyddanemeanshort"]], "Class ostk::astrodynamics::trajectory::orbit::model::kepler::COE": [[186, "class-ostk-astrodynamics-trajectory-orbit-model-kepler-coe"]], "Class ostk::astrodynamics::trajectory::orbit::model::sgp4::TLE": [[187, "class-ostk-astrodynamics-trajectory-orbit-model-sgp4-tle"]], "Class ostk::astrodynamics::trajectory::state::CoordinateBroker": [[188, "class-ostk-astrodynamics-trajectory-state-coordinatebroker"]], "Class ostk::astrodynamics::trajectory::state::CoordinateSubset": [[189, "class-ostk-astrodynamics-trajectory-state-coordinatesubset"]], "Class ostk::astrodynamics::trajectory::state::NumericalSolver": [[190, "class-ostk-astrodynamics-trajectory-state-numericalsolver"]], "Class ostk::astrodynamics::trajectory::state::coordinatesubset::AngularVelocity": [[191, "class-ostk-astrodynamics-trajectory-state-coordinatesubset-angularvelocity"]], "Class ostk::astrodynamics::trajectory::state::coordinatesubset::AttitudeQuaternion": [[192, "class-ostk-astrodynamics-trajectory-state-coordinatesubset-attitudequaternion"]], "Class ostk::astrodynamics::trajectory::state::coordinatesubset::CartesianPosition": [[193, "class-ostk-astrodynamics-trajectory-state-coordinatesubset-cartesianposition"]], "Class ostk::astrodynamics::trajectory::state::coordinatesubset::CartesianVelocity": [[194, "class-ostk-astrodynamics-trajectory-state-coordinatesubset-cartesianvelocity"]], "Coast segment": [[125, "coast-segment"]], "Computation": [[112, "computation"], [122, "computation"], [124, "computation"]], "Constant Solar Flux and Geomagnetic Index Atmospheric Density Model": [[113, "constant-solar-flux-and-geomagnetic-index-atmospheric-density-model"]], "Constant Thrust Dynamics": [[114, "constant-thrust-dynamics"]], "Contribution": [[196, "contribution"]], "Create a model": [[116, "create-a-model"]], "Cross Validation and Accuracy Tolerances": [[196, "cross-validation-and-accuracy-tolerances"]], "Custom Event Condition": [[115, "custom-event-condition"]], "Custom Window Generation": [[116, "custom-window-generation"]], "Debian / Ubuntu": [[196, "debian-ubuntu"]], "Define Satellites": [[117, "define-satellites"]], "Define Scenario": [[117, "define-scenario"]], "Define our condition": [[116, "define-our-condition"]], "Define our solver": [[116, "define-our-solver"]], "Dependencies": [[196, "dependencies"]], "Development Environment": [[196, "development-environment"]], "Docker Images": [[196, "docker-images"]], "Documentation": [[196, "documentation"]], "Eccentricity targeting": [[123, "eccentricity-targeting"]], "Eclipse condition": [[115, "eclipse-condition"]], "Environment": [[111, "environment"], [112, "environment"], [124, "environment"]], "Examples {#Examples}": [[0, "examples-examples"]], "Find RF Interference Accesses": [[117, "find-rf-interference-accesses"]], "Getting Started": [[196, "getting-started"]], "Inclination targeting": [[123, "inclination-targeting"]], "Installation": [[196, "installation"]], "Interference Filter": [[117, "interference-filter"]], "JupyterLab": [[196, "jupyterlab"]], "License": [[196, "license"]], "Maneuver segment": [[125, "maneuver-segment"]], "Multiple targets": [[123, "multiple-targets"]], "OSTk Cross-Platform Validation Against GMAT/Orekit (Mission Sequence Scenario 1)": [[118, "ostk-cross-platform-validation-against-gmat-orekit-mission-sequence-scenario-1"]], "OSTk Cross-Platform Validation Against GMAT/Orekit (Mission Sequence Scenario 2)": [[119, "ostk-cross-platform-validation-against-gmat-orekit-mission-sequence-scenario-2"]], "OSTk Cross-Platform Validation Against GMAT/Orekit (Mission Sequence Scenario 3)": [[120, "ostk-cross-platform-validation-against-gmat-orekit-mission-sequence-scenario-3"]], "OSTk Cross-Platform Validation Against GMAT/Orekit (Mission Sequence Scenario 4)": [[121, "ostk-cross-platform-validation-against-gmat-orekit-mission-sequence-scenario-4"]], "Open Space Toolkit \u25b8 Astrodynamics": [[196, "open-space-toolkit-astrodynamics"]], "Orbit Computation": [[122, "orbit-computation"]], "Orbit Station-keeping with QLaw": [[123, "orbit-station-keeping-with-qlaw"]], "Origin": [[111, "origin"]], "Output": [[111, "output"], [122, "output"]], "Plots": [[117, "plots"]], "Process Cross Platform Results": [[118, "process-cross-platform-results"], [119, "process-cross-platform-results"], [120, "process-cross-platform-results"], [121, "process-cross-platform-results"]], "Propagate with OSTk": [[118, "propagate-with-ostk"], [119, "propagate-with-ostk"], [120, "propagate-with-ostk"], [121, "propagate-with-ostk"]], "Propagation": [[113, "propagation"]], "Python": [[196, "python"]], "Python API Documentation": [[198, "python-api-documentation"]], "Right Ascension of Ascending Node targeting": [[123, "right-ascension-of-ascending-node-targeting"]], "Run the analysis": [[117, "run-the-analysis"]], "Running the Validation Tests": [[196, "running-the-validation-tests"]], "SGP4": [[122, "sgp4"]], "SMA + Ecc": [[123, "sma-ecc"]], "SMA + Ecc + Inc + Raan targeting": [[123, "sma-ecc-inc-raan-targeting"]], "SMA + Ecc + Inclination": [[123, "sma-ecc-inclination"]], "SMA targeting": [[123, "sma-targeting"]], "Satellite": [[112, "satellite"], [124, "satellite"]], "Scenario Definition": [[196, "scenario-definition"]], "Semi Major Axis + Inclination": [[123, "semi-major-axis-inclination"]], "Sensor": [[112, "sensor"], [124, "sensor"]], "Sensor Modeling": [[124, "sensor-modeling"]], "Sequence": [[125, "sequence"], [126, "sequence"]], "Set up Comparison Files": [[118, "set-up-comparison-files"], [119, "set-up-comparison-files"], [120, "set-up-comparison-files"], [121, "set-up-comparison-files"]], "Setup": [[111, "setup"], [112, "setup"], [117, "setup"], [122, "setup"], [124, "setup"], [196, "setup"]], "Setup Comparison Scenario in OSTk": [[118, "setup-comparison-scenario-in-ostk"], [119, "setup-comparison-scenario-in-ostk"], [120, "setup-comparison-scenario-in-ostk"], [121, "setup-comparison-scenario-in-ostk"]], "Setup Dynamics, initial state and Satellite System": [[113, "setup-dynamics-initial-state-and-satellite-system"], [126, "setup-dynamics-initial-state-and-satellite-system"]], "Setup environment, initial state and Satellite System": [[123, "setup-environment-initial-state-and-satellite-system"], [125, "setup-environment-initial-state-and-satellite-system"]], "Setup {#Setup}": [[0, "setup-setup"]], "Special Thanks": [[196, "special-thanks"]], "Station-keeping Sequence": [[126, "station-keeping-sequence"]], "Target": [[111, "target"], [124, "target"]], "Target Intersection": [[112, "target-intersection"]], "Test": [[196, "test"]], "Trajectory RMS error vs GMAT run in the GCRF frame": [[118, "trajectory-rms-error-vs-gmat-run-in-the-gcrf-frame"], [119, "trajectory-rms-error-vs-gmat-run-in-the-gcrf-frame"], [120, "trajectory-rms-error-vs-gmat-run-in-the-gcrf-frame"], [121, "trajectory-rms-error-vs-gmat-run-in-the-gcrf-frame"]], "Tutorial": [[0, "tutorial"]], "Tutorial Notebooks": [[197, "tutorial-notebooks"]], "Tutorials": [[196, "tutorials"]], "User inputs": [[113, "user-inputs"], [123, "user-inputs"], [125, "user-inputs"], [126, "user-inputs"]], "Utility functions": [[123, "utility-functions"]], "Validation": [[196, "validation"]], "Validation Plots": [[118, "validation-plots"], [119, "validation-plots"], [120, "validation-plots"], [121, "validation-plots"]], "Visualization": [[112, "visualization"], [124, "visualization"]], "Visualize Satellite States (Cesium)": [[127, "visualize-satellite-states-cesium"]], "Window generation": [[116, "window-generation"]], "iPython": [[196, "ipython"]], "ostk.astrodynamics": [[1, "module-ostk.astrodynamics"]], "ostk.astrodynamics.Access": [[2, "ostk-astrodynamics-access"]], "ostk.astrodynamics.Dynamics": [[3, "ostk-astrodynamics-dynamics"]], "ostk.astrodynamics.EventCondition": [[4, "ostk-astrodynamics-eventcondition"]], "ostk.astrodynamics.GuidanceLaw": [[5, "ostk-astrodynamics-guidancelaw"]], "ostk.astrodynamics.RootSolver": [[6, "ostk-astrodynamics-rootsolver"]], "ostk.astrodynamics.Trajectory": [[7, "ostk-astrodynamics-trajectory"]], "ostk.astrodynamics.access": [[8, "module-ostk.astrodynamics.access"]], "ostk.astrodynamics.access.Generator": [[9, "ostk-astrodynamics-access-generator"]], "ostk.astrodynamics.conjunction.message.ccsds": [[10, "module-ostk.astrodynamics.conjunction.message.ccsds"]], "ostk.astrodynamics.conjunction.message.ccsds.CDM": [[11, 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b/_build/jupyter_execute/_notebooks/Custom Window Generation.ipynb @@ -376,7 +376,7 @@ { "data": { "image/svg+xml": [ - "trace 1" + "trace 1" ] }, "metadata": {}, diff --git a/_build/jupyter_execute/_notebooks/Sensor Modeling.ipynb b/_build/jupyter_execute/_notebooks/Sensor Modeling.ipynb index 037544fbc..88c76f517 100644 --- a/_build/jupyter_execute/_notebooks/Sensor Modeling.ipynb +++ b/_build/jupyter_execute/_notebooks/Sensor Modeling.ipynb @@ -804,7 +804,7 @@ { "data": { "image/svg+xml": [ - "" + "" ] }, "metadata": {}, @@ -874,7 +874,7 @@ { "data": { "image/svg+xml": [ - "" + "" ] }, "metadata": {}, diff --git a/_build/jupyter_execute/_notebooks/Station-keeping Sequence.ipynb b/_build/jupyter_execute/_notebooks/Station-keeping Sequence.ipynb index a2bc7d9c5..8684d307d 100644 --- a/_build/jupyter_execute/_notebooks/Station-keeping Sequence.ipynb +++ b/_build/jupyter_execute/_notebooks/Station-keeping Sequence.ipynb @@ -257,7 +257,7 @@ "name": "stdout", "output_type": "stream", "text": [ - "[2024-05-08 15:29:37.894356] [0x00007f018897c280] [debug] Solving Segment:\n", + "[2024-05-15 16:57:14.851844] [0x00007f6743286280] [debug] Solving Segment:\n", "-- Segment -----------------------------------------------------------------------------------------\n", " Name: Coast \n", " Type: Coast \n", @@ -286,7 +286,7 @@ "name": "stdout", "output_type": "stream", "text": [ - "[2024-05-08 15:29:38.658581] [0x00007f018897c280] [debug] \n", + "[2024-05-15 16:57:15.623754] [0x00007f6743286280] [debug] \n", "-- Segment Solution --------------------------------------------------------------------------------\n", " Name: Coast - Mean SMA crossing - coast - 0 \n", " Condition satisfied: True \n", @@ -297,7 +297,7 @@ "----------------------------------------------------------------------------------------------------\n", "\n", "\n", - "[2024-05-08 15:29:38.658777] [0x00007f018897c280] [debug] Solving Segment:\n", + "[2024-05-15 16:57:15.623954] [0x00007f6743286280] [debug] Solving Segment:\n", "-- Segment -----------------------------------------------------------------------------------------\n", " Name: Maneuver \n", " Type: Maneuver \n", @@ -350,7 +350,7 @@ "name": "stdout", "output_type": "stream", "text": [ - "[2024-05-08 15:29:39.570278] [0x00007f018897c280] [debug] \n", + "[2024-05-15 16:57:16.546301] [0x00007f6743286280] [debug] \n", "-- Segment Solution --------------------------------------------------------------------------------\n", " Name: Maneuver - Mean SMA crossing - thrust - 0 \n", " Condition satisfied: True \n", @@ -364,7 +364,7 @@ "----------------------------------------------------------------------------------------------------\n", "\n", "\n", - "[2024-05-08 15:29:39.570514] [0x00007f018897c280] [debug] Solving Segment:\n", + "[2024-05-15 16:57:16.546532] [0x00007f6743286280] [debug] Solving Segment:\n", "-- Segment -----------------------------------------------------------------------------------------\n", " Name: Coast \n", " Type: Coast \n", @@ -393,7 +393,7 @@ "name": "stdout", "output_type": "stream", "text": [ - "[2024-05-08 15:29:42.626245] [0x00007f018897c280] [debug] \n", + "[2024-05-15 16:57:19.648189] [0x00007f6743286280] [debug] \n", "-- Segment Solution --------------------------------------------------------------------------------\n", " Name: Coast - Mean SMA crossing - coast - 1 \n", " Condition satisfied: True \n", @@ -404,7 +404,7 @@ "----------------------------------------------------------------------------------------------------\n", "\n", "\n", - "[2024-05-08 15:29:42.626818] [0x00007f018897c280] [debug] Solving Segment:\n", + "[2024-05-15 16:57:19.648770] [0x00007f6743286280] [debug] Solving Segment:\n", "-- Segment -----------------------------------------------------------------------------------------\n", " Name: Maneuver \n", " Type: Maneuver \n", @@ -457,7 +457,7 @@ "name": "stdout", "output_type": "stream", "text": [ - "[2024-05-08 15:29:43.544916] [0x00007f018897c280] [debug] \n", + "[2024-05-15 16:57:20.585195] [0x00007f6743286280] [debug] \n", "-- Segment Solution --------------------------------------------------------------------------------\n", " Name: Maneuver - Mean SMA crossing - thrust - 1 \n", " Condition satisfied: True \n", @@ -468,14 +468,7 @@ " Initial mass: 109.98712414601253 [kg] \n", " Final mass: 109.97436777064368 [kg] \n", " Total mass consumed: 0.012756375368851991 [kg] \n", - "------------------------------------------------------" - ] - }, - { - "name": "stdout", - "output_type": "stream", - "text": [ - "----------------------------------------------\n", + "----------------------------------------------------------------------------------------------------\n", "\n", "\n" ] diff --git a/_build/jupyter_execute/_notebooks/Visualize Satellite Trajectory (Cesium).ipynb b/_build/jupyter_execute/_notebooks/Visualize Satellite Trajectory (Cesium).ipynb index de2f38109..f391dcf80 100644 --- a/_build/jupyter_execute/_notebooks/Visualize Satellite Trajectory (Cesium).ipynb +++ b/_build/jupyter_execute/_notebooks/Visualize Satellite Trajectory (Cesium).ipynb @@ -19,8 +19,8 @@ "output_type": "stream", "text": [ "Collecting cesiumpy\r\n", - " Cloning https://github.com/open-space-collective/cesiumpy.git to /tmp/pip-install-zye6o7x2/cesiumpy_21e431fb96a54654b143be4dd8c2d905\r\n", - " Running command git clone --filter=blob:none --quiet https://github.com/open-space-collective/cesiumpy.git /tmp/pip-install-zye6o7x2/cesiumpy_21e431fb96a54654b143be4dd8c2d905\r\n" + " Cloning https://github.com/open-space-collective/cesiumpy.git to /tmp/pip-install-gu01cwfr/cesiumpy_e50c8e43a91944649036bb06e931a235\r\n", + " Running command git clone --filter=blob:none --quiet https://github.com/open-space-collective/cesiumpy.git /tmp/pip-install-gu01cwfr/cesiumpy_e50c8e43a91944649036bb06e931a235\r\n" ] }, { @@ -45,13 +45,7 @@ "\b \bdone\r\n", "\u001b[?25hRequirement already satisfied: six in /usr/local/lib/python3.11/site-packages (from cesiumpy) (1.16.0)\r\n", "Requirement already satisfied: traitlets in /usr/local/lib/python3.11/site-packages (from cesiumpy) (5.14.3)\r\n", - "Requirement already satisfied: geopy>=1.11.0 in /usr/local/lib/python3.11/site-packages (from cesiumpy) (2.4.1)\r\n" - ] - }, - { - "name": "stdout", - "output_type": "stream", - "text": [ + "Requirement already satisfied: geopy>=1.11.0 in /usr/local/lib/python3.11/site-packages (from cesiumpy) (2.4.1)\r\n", "Requirement already satisfied: geographiclib<3,>=1.52 in /usr/local/lib/python3.11/site-packages (from geopy>=1.11.0->cesiumpy) (2.0)\r\n" ] }, @@ -193,730 +187,730 @@ " async function init() {\n", " Cesium.Ion.defaultAccessToken = \"eyJhbGciOiJIUzI1NiIsInR5cCI6IkpXVCJ9.eyJqdGkiOiJlYmYyODhkOS1jNDY5LTQ0NTUtOWNlZi0zMDhjNjE1NDY2OTUiLCJpZCI6NzE4ODUsImlhdCI6MTYzNTUzNzc1Mn0.YQiV6xUFOiEhdQ-w3Dmgy1XYZogK5dclhn7X0U6i7Oo\";\n", " var widget = new Cesium.Viewer(\"cesiumContainer\", {fullscreenButton: false, homeButton: false, infoBox: false, sceneModePicker: false, selectionIndicator: false, timeline: true, navigationHelpButton: false, navigationInstructionsInitiallyVisible: false, scene3dOnly: true, clockViewModel: new Cesium.ClockViewModel(new Cesium.Clock({startTime: Cesium.JulianDate.fromIso8601(\"2023-01-01T00:00:00+00:00\"), stopTime: Cesium.JulianDate.fromIso8601(\"2023-01-01T03:00:00+00:00\"), clockRange: Cesium.ClockRange.CLAMPED, canAnimate: true, shouldAnimate: false}))});\n", - " widget.property_9bfe1ee8 = new Cesium.SampledProperty(Cesium.Cartesian3);\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:00:00+00:00\", Cesium.Cartesian3.fromDegrees(29.98055060896214, -0.08103079020036194, 500000.0424350213));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:00:30+00:00\", Cesium.Cartesian3.fromDegrees(29.61394459855244, 1.8152541965297813, 500021.2891134799));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:01:00+00:00\", Cesium.Cartesian3.fromDegrees(29.246837283092006, 3.711457477700564, 500088.9038070484));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:01:30+00:00\", Cesium.Cartesian3.fromDegrees(28.878700725097563, 5.607493659242157, 500202.5852361204));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:02:00+00:00\", Cesium.Cartesian3.fromDegrees(28.508998078325064, 7.503277246472494, 500361.82691467437));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:02:30+00:00\", Cesium.Cartesian3.fromDegrees(28.137178834920114, 9.39872257658667, 500565.9194959655));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:03:00+00:00\", Cesium.Cartesian3.fromDegrees(27.76267381978467, 11.29374373104158, 500813.95405548724));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:03:30+00:00\", Cesium.Cartesian3.fromDegrees(27.384889834542843, 13.188254420285343, 501104.82629379485));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:04:00+00:00\", Cesium.Cartesian3.fromDegrees(27.003203842160705, 15.082167832578493, 501437.2416369357));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:04:30+00:00\", Cesium.Cartesian3.fromDegrees(26.61695656805757, 16.975396437707136, 501809.7212076043));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:05:00+00:00\", Cesium.Cartesian3.fromDegrees(26.225445373867096, 18.867851735144278, 502220.6086357079));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:05:30+00:00\", Cesium.Cartesian3.fromDegrees(25.82791623448943, 20.75944393460629, 502668.0776729075));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:06:00+00:00\", Cesium.Cartesian3.fromDegrees(25.42355444852117, 22.650081554882785, 503150.14057144115));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:06:30+00:00\", Cesium.Cartesian3.fromDegrees(25.011474847567403, 24.53967092416804, 503664.65718443843));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:07:00+00:00\", Cesium.Cartesian3.fromDegrees(24.590708687169503, 26.42811556172291, 504209.34474088927));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:07:30+00:00\", Cesium.Cartesian3.fromDegrees(24.160190218573536, 28.315315416339914, 504781.78824600566));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:08:00+00:00\", Cesium.Cartesian3.fromDegrees(23.71873997101196, 30.20116593146087, 505379.45145462017));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:08:30+00:00\", Cesium.Cartesian3.fromDegrees(23.265045193937162, 32.08555689952976, 505999.68836319674));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:09:00+00:00\", Cesium.Cartesian3.fromDegrees(22.797636588863732, 33.96837105870364, 506639.75516373105));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:09:30+00:00\", Cesium.Cartesian3.fromDegrees(22.31486044260936, 35.84948237266498, 507296.82260151353));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:10:00+00:00\", Cesium.Cartesian3.fromDegrees(21.814845029896325, 37.72875391796016, 507967.98867721425));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:10:30+00:00\", Cesium.Cartesian3.fromDegrees(21.295459831252085, 39.60603528162094, 508650.29163284163));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:11:00+00:00\", Cesium.Cartesian3.fromDegrees(20.754265683819927, 41.481159342815566, 509340.7231607127));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:11:30+00:00\", Cesium.Cartesian3.fromDegrees(20.188453407339118, 43.35393827309509, 510036.2417740361));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:12:00+00:00\", Cesium.Cartesian3.fromDegrees(19.59476766873308, 45.22415853637336, 510733.7862780438));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:12:30+00:00\", Cesium.Cartesian3.fromDegrees(18.96941178348625, 47.09157459619166, 511430.2892808057));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:13:00+00:00\", Cesium.Cartesian3.fromDegrees(18.307927680695265, 48.95590093534189, 512122.6906835406));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:13:30+00:00\", Cesium.Cartesian3.fromDegrees(17.60504320496362, 50.81680184855506, 512807.9510913192));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:14:00+00:00\", Cesium.Cartesian3.fromDegrees(16.854476029141797, 52.673878263022765, 513483.0650859812));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:14:30+00:00\", Cesium.Cartesian3.fromDegrees(16.048679311763394, 54.526650543828474, 514145.0743047504));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:15:00+00:00\", Cesium.Cartesian3.fromDegrees(15.17850824810701, 56.374535804885824, 514791.0802694849));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:15:30+00:00\", Cesium.Cartesian3.fromDegrees(14.232777903949135, 58.21681759626829, 515418.25691348885));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:16:00+00:00\", Cesium.Cartesian3.fromDegrees(13.197669735589734, 60.052604856026605, 516023.8627545611));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:16:30+00:00\", Cesium.Cartesian3.fromDegrees(12.055924707421658, 61.880775502464516, 516605.25266542385));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:17:00+00:00\", Cesium.Cartesian3.fromDegrees(10.785731141158601, 63.69989767427881, 517159.8891946781));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:17:30+00:00\", Cesium.Cartesian3.fromDegrees(9.359171168837772, 65.50811784627128, 517685.3533939366));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:18:00+00:00\", Cesium.Cartesian3.fromDegrees(7.740015925313452, 67.30299890154708, 518179.35510937124));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:18:30+00:00\", Cesium.Cartesian3.fromDegrees(5.880557025318269, 69.08128105776676, 518639.74269833014));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:19:00+00:00\", Cesium.Cartesian3.fromDegrees(3.7169906891635627, 70.83852138912368, 519064.5121344491));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:19:30+00:00\", Cesium.Cartesian3.fromDegrees(1.1626334563986747, 72.56853842648421, 519451.81546731724));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:20:00+00:00\", Cesium.Cartesian3.fromDegrees(-1.902062436770439, 74.26253830833996, 519799.96860562864));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:20:30+00:00\", Cesium.Cartesian3.fromDegrees(-5.643970587222167, 75.90771521943759, 520107.4583953582));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:21:00+00:00\", Cesium.Cartesian3.fromDegrees(-10.297080753352736, 77.48498908533233, 520372.9489675021));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:21:30+00:00\", Cesium.Cartesian3.fromDegrees(-16.185244683786046, 78.96538971558137, 520595.2873326828));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:22:00+00:00\", Cesium.Cartesian3.fromDegrees(-23.733179641860527, 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50.49191479842679, 512688.864470835));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:34:30+00:00\", Cesium.Cartesian3.fromDegrees(-150.33903656412133, 48.630388644209646, 512002.1385418101));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:35:00+00:00\", Cesium.Cartesian3.fromDegrees(-150.99385369627547, 46.76549987638047, 511308.8006082331));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:35:30+00:00\", Cesium.Cartesian3.fromDegrees(-151.6133754814116, 44.89757457618284, 510611.89464388724));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:36:00+00:00\", Cesium.Cartesian3.fromDegrees(-152.20193446038556, 43.0268906103346, 509914.48299145134));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:36:30+00:00\", Cesium.Cartesian3.fromDegrees(-152.76322486340518, 41.1536874022938, 509219.6329336911));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:37:00+00:00\", Cesium.Cartesian3.fromDegrees(-153.30041780819613, 39.278173583611945, 508530.403195255));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:37:30+00:00\", Cesium.Cartesian3.fromDegrees(-153.81625279938652, 37.40053303566828, 507849.83043442527));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:38:00+00:00\", Cesium.Cartesian3.fromDegrees(-154.3131110090462, 35.52092969622229, 507180.91578518687));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:38:30+00:00\", Cesium.Cartesian3.fromDegrees(-154.79307442878903, 33.63951140858381, 506526.61151042336));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:39:00+00:00\", Cesium.Cartesian3.fromDegrees(-155.25797397597836, 31.75641302167021, 505889.8078275608));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:39:30+00:00\", Cesium.Cartesian3.fromDegrees(-155.7094290665667, 29.871758898647325, 505273.3199677718));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:40:00+00:00\", Cesium.Cartesian3.fromDegrees(-156.14887944424657, 27.98566495469677, 504679.87552976457));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:40:30+00:00\", Cesium.Cartesian3.fromDegrees(-156.57761317843475, 26.098240316905777, 504112.10218830843));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:41:00+00:00\", Cesium.Cartesian3.fromDegrees(-156.9967885535992, 24.20958867866036, 503572.5158168839));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:41:30+00:00\", Cesium.Cartesian3.fromDegrees(-157.40745322341814, 22.319809405386913, 503063.50908229966));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:42:00+00:00\", Cesium.Cartesian3.fromDegrees(-157.81056029565892, 20.42899843667915, 502587.3405675108));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:42:30+00:00\", Cesium.Cartesian3.fromDegrees(-158.206982053685, 18.537249020817296, 502146.12447687704));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:43:00+00:00\", Cesium.Cartesian3.fromDegrees(-158.59752174679778, 16.644652310740476, 501741.82097554376));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:43:30+00:00\", Cesium.Cartesian3.fromDegrees(-158.98292379923365, 14.751297845159367, 501376.227211997));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:44:00+00:00\", Cesium.Cartesian3.fromDegrees(-159.36388272347386, 12.857273934321597, 501050.9690697095));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:44:30+00:00\", Cesium.Cartesian3.fromDegrees(-159.74105097299213, 10.962667966691134, 500767.4936903933));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:45:00+00:00\", Cesium.Cartesian3.fromDegrees(-160.1150459300038, 9.06756665026388, 500527.0628076465));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:45:30+00:00\", Cesium.Cartesian3.fromDegrees(-160.48645619266784, 7.172056200260941, 500330.7469257952));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:46:00+00:00\", Cesium.Cartesian3.fromDegrees(-160.85584730175177, 5.2762224834022495, 500179.4203744899));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:46:30+00:00\", Cesium.Cartesian3.fromDegrees(-161.22376702796555, 3.3801511277748517, 500073.75726517633));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:47:00+00:00\", Cesium.Cartesian3.fromDegrees(-161.5907503266743, 1.4839276064098703, 500014.22837074933));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:47:30+00:00\", Cesium.Cartesian3.fromDegrees(-161.95732405598213, -0.41236269798181335, 500001.09894505603));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:48:00+00:00\", Cesium.Cartesian3.fromDegrees(-162.32401154677652, -2.308634440128287, 500034.4274937818));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:48:30+00:00\", Cesium.Cartesian3.fromDegrees(-162.69133710859748, -4.204802264466732, 500114.0655033297));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:49:00+00:00\", Cesium.Cartesian3.fromDegrees(-163.05983055331401, -6.10078075598479, 500239.65812902915));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:49:30+00:00\", Cesium.Cartesian3.fromDegrees(-163.43003181902174, -7.996484383019531, 500410.6458391872));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:50:00+00:00\", Cesium.Cartesian3.fromDegrees(-163.80249577980234, -9.891827425207591, 500626.2670060124));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:50:30+00:00\", Cesium.Cartesian3.fromDegrees(-164.17779733276518, -11.786723879421537, 500885.56142980413));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:51:00+00:00\", Cesium.Cartesian3.fromDegrees(-164.55653703068967, -13.6810873359798, 501187.3747776679));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:51:30+00:00\", Cesium.Cartesian3.fromDegrees(-164.93934636423123, -15.574830816657336, 501530.36391323386));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:52:00+00:00\", Cesium.Cartesian3.fromDegrees(-165.3268953438948, -17.467866565001803, 501913.0030894203));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:52:30+00:00\", Cesium.Cartesian3.fromDegrees(-165.71989916977046, -19.360105778134816, 502333.5909717588));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:53:00+00:00\", Cesium.Cartesian3.fromDegrees(-166.11912668752834, -21.251458267492346, 502790.2584557664));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:53:30+00:00\", Cesium.Cartesian3.fromDegrees(-166.5254098336956, -23.14183203375625, 503280.97723775444));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:54:00+00:00\", Cesium.Cartesian3.fromDegrees(-166.93965449395094, -25.031132738399243, 503803.5690952676));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:54:30+00:00\", Cesium.Cartesian3.fromDegrees(-167.36285308604894, -26.919263050642854, 504355.71582969144));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:55:00+00:00\", Cesium.Cartesian3.fromDegrees(-167.7960992505605, -28.80612184397096, 504934.9698208067));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:55:30+00:00\", Cesium.Cartesian3.fromDegrees(-168.24060512429895, -30.691603210336158, 505538.76514047914));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:56:00+00:00\", Cesium.Cartesian3.fromDegrees(-168.69772178934673, -32.57559525241569, 506164.4291703355));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:56:30+00:00\", Cesium.Cartesian3.fromDegrees(-169.1689636436393, -34.45797860413529, 506809.1946664192));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:57:00+00:00\", Cesium.Cartesian3.fromDegrees(-169.65603763850487, -36.33862461638469, 507470.2122123029));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:57:30+00:00\", Cesium.Cartesian3.fromDegrees(-170.16087859048807, -38.21739312729571, 508144.5630008639));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:58:00+00:00\", Cesium.Cartesian3.fromDegrees(-170.68569212130916, -40.094129713093096, 508829.271884173));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:58:30+00:00\", Cesium.Cartesian3.fromDegrees(-171.23300724203722, -41.96866228418769, 509521.3206303791));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:59:00+00:00\", Cesium.Cartesian3.fromDegrees(-171.8057412193713, -43.84079684874571, 510217.6613263583));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T00:59:30+00:00\", Cesium.Cartesian3.fromDegrees(-172.40728020619724, -45.710312207958474, 510915.22986498737));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:00:00+00:00\", Cesium.Cartesian3.fromDegrees(-173.04158027603893, -47.57695326711263, 511610.95945635554));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:00:30+00:00\", Cesium.Cartesian3.fromDegrees(-173.71329510397612, -49.440422534655035, 512301.7941030726));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:01:00+00:00\", Cesium.Cartesian3.fromDegrees(-174.4279387806934, -51.30036922329144, 512984.7019805861));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:01:30+00:00\", Cesium.Cartesian3.fromDegrees(-175.1920954234289, -53.15637514079682, 513656.68866496097));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:02:00+00:00\", Cesium.Cartesian3.fromDegrees(-176.01369196707364, -55.0079362298119, 514314.8101518461));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:02:30+00:00\", Cesium.Cartesian3.fromDegrees(-176.90235594253622, -56.85443813254697, 514956.1856120419));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:03:00+00:00\", Cesium.Cartesian3.fromDegrees(-177.8698932722313, -58.695123433869405, 515578.009831105));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:03:30+00:00\", Cesium.Cartesian3.fromDegrees(-178.93092964496495, -60.52904713870872, 516177.5652822965));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:04:00+00:00\", Cesium.Cartesian3.fromDegrees(179.89621337587832, -62.35501524326767, 516752.2337844397));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:04:30+00:00\", Cesium.Cartesian3.fromDegrees(178.58830681702977, -64.1714985895305, 517299.5076985581));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:05:00+00:00\", Cesium.Cartesian3.fromDegrees(177.11551460120486, -65.97650991085136, 517817.0006195834));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:05:30+00:00\", Cesium.Cartesian3.fromDegrees(175.4389744793243, -67.76742497901446, 518302.45752199605));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:06:00+00:00\", Cesium.Cartesian3.fromDegrees(173.5073070768232, -69.54071711705829, 518753.7643207166));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:06:30+00:00\", Cesium.Cartesian3.fromDegrees(171.251517088181, -71.29155464768192, 519168.95681146363));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:07:00+00:00\", Cesium.Cartesian3.fromDegrees(168.5774888235921, -73.013177195508, 519546.2289572532));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:07:30+00:00\", Cesium.Cartesian3.fromDegrees(165.3549628840619, -74.69590938062527, 519883.94049077114));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:08:00+00:00\", Cesium.Cartesian3.fromDegrees(161.40171773519558, -76.32557553771517, 520180.6238048203));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:08:30+00:00\", Cesium.Cartesian3.fromDegrees(156.46252288175037, -77.88093780038403, 520434.9901061781));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:09:00+00:00\", Cesium.Cartesian3.fromDegrees(150.1871573672711, -79.32963873752848, 520645.9348108238));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:09:30+00:00\", Cesium.Cartesian3.fromDegrees(142.12842263406904, -80.62229067913985, 520812.54216151265));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:10:00+00:00\", Cesium.Cartesian3.fromDegrees(131.82412513542155, -81.68594313725679, 520934.08905134036));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:10:30+00:00\", Cesium.Cartesian3.fromDegrees(119.0842521598398, -82.42365260045183, 521010.0480400166));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:11:00+00:00\", Cesium.Cartesian3.fromDegrees(104.49741098318235, -82.73551520425212, 521040.08955236647));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:11:30+00:00\", Cesium.Cartesian3.fromDegrees(89.62558141939809, -82.56776147148199, 521024.0832513269));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:12:00+00:00\", Cesium.Cartesian3.fromDegrees(76.21151200295154, -81.95030552915767, 520962.09858080413));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:12:30+00:00\", Cesium.Cartesian3.fromDegrees(65.1595723865476, -80.97492694431195, 520854.404476465));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:13:00+00:00\", Cesium.Cartesian3.fromDegrees(56.46073158350803, -79.7431515679702, 520701.4682454272));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:13:30+00:00\", Cesium.Cartesian3.fromDegrees(49.69257969636662, -78.33582607442469, 520503.9536188246));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:14:00+00:00\", Cesium.Cartesian3.fromDegrees(44.387912711807594, -76.80890246584512, 520262.7179838526));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:14:30+00:00\", Cesium.Cartesian3.fromDegrees(40.165093304537244, -75.1992237719078, 519978.80880506634));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:15:00+00:00\", Cesium.Cartesian3.fromDegrees(36.741995096200995, -73.53090480046316, 519653.4592473066));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:15:30+00:00\", Cesium.Cartesian3.fromDegrees(33.91657197969568, -71.81994502469261, 519288.0830156669));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:16:00+00:00\", Cesium.Cartesian3.fromDegrees(31.544648094398568, -70.07718780054088, 518884.26843080233));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:16:30+00:00\", Cesium.Cartesian3.fromDegrees(29.522452573063212, -68.31015585690093, 518443.77176046453));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:17:00+00:00\", Cesium.Cartesian3.fromDegrees(27.77426384329059, -66.52418955622221, 517968.50983149046));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:17:30+00:00\", Cesium.Cartesian3.fromDegrees(26.243964341330372, -64.72316265474306, 517460.5519487355));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:18:00+00:00\", Cesium.Cartesian3.fromDegrees(24.889306933482526, -62.90994130055134, 516922.1111507197));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:18:30+00:00\", Cesium.Cartesian3.fromDegrees(23.67800099609904, -61.086684758570414, 516355.5348342103));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:19:00+00:00\", Cesium.Cartesian3.fromDegrees(22.585010940237943, -59.25504671102925, 515763.2947829343));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:19:30+00:00\", Cesium.Cartesian3.fromDegrees(21.590666281359734, -57.41631280936791, 515147.9766381164));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:20:00+00:00\", Cesium.Cartesian3.fromDegrees(20.67932040325302, -55.571496504915686, 514512.2688512626));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:20:30+00:00\", Cesium.Cartesian3.fromDegrees(19.838384997074957, -53.72140702772875, 513858.95116215356));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:21:00+00:00\", Cesium.Cartesian3.fromDegrees(19.05762522980383, -51.86669841944499, 513190.88264741626));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:21:30+00:00\", Cesium.Cartesian3.fromDegrees(18.328638371334513, -50.00790544866275, 512510.98938747443));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:22:00+00:00\", Cesium.Cartesian3.fromDegrees(17.644463261997537, -48.14547029312339, 511822.2518017856));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:22:30+00:00\", Cesium.Cartesian3.fromDegrees(16.999284313268543, -46.27976262193474, 511127.69170452695));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:23:00+00:00\", Cesium.Cartesian3.fromDegrees(16.388204659561097, -44.411094891840044, 510430.35913457273));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:23:30+00:00\", Cesium.Cartesian3.fromDegrees(15.807070489976029, -42.53973412608288, 509733.3190156438));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:24:00+00:00\", Cesium.Cartesian3.fromDegrees(15.252333679663362, -40.66591107552644, 509039.63770376967));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:24:30+00:00\", Cesium.Cartesian3.fromDegrees(14.72094321315295, -38.789827408499, 508352.36948073783));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:25:00+00:00\", Cesium.Cartesian3.fromDegrees(14.210259560457075, -36.911661399655635, 507674.5430530753));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:25:30+00:00\", Cesium.Cartesian3.fromDegrees(13.717984410973417, -35.03157246395762, 507009.1481171805));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:26:00+00:00\", Cesium.Cartesian3.fromDegrees(13.242105330354534, -33.14970479325459, 506359.122051495));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:26:30+00:00\", Cesium.Cartesian3.fromDegrees(12.780849950652167, -31.266190289021132, 505727.33679699904));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:27:00+00:00\", Cesium.Cartesian3.fromDegrees(12.332648516080507, -29.38115093816642, 505116.58598727523));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:27:30+00:00\", Cesium.Cartesian3.fromDegrees(11.89610293544671, -27.49470074449376, 504529.5723887815));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:28:00+00:00\", Cesium.Cartesian3.fromDegrees(11.469961038524506, -25.60694730286095, 503968.89571150363));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:28:30+00:00\", Cesium.Cartesian3.fromDegrees(11.053095018555702, -23.717993083957783, 503437.0408488948));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:29:00+00:00\", Cesium.Cartesian3.fromDegrees(10.644483259697004, -21.827936483155813, 502936.3666045627));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:29:30+00:00\", Cesium.Cartesian3.fromDegrees(10.243194914014595, -19.936872675884867, 502469.0949615631));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:30:00+00:00\", Cesium.Cartesian3.fromDegrees(9.848376720256306, -18.044894313558864, 502037.3009477118));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:30:30+00:00\", Cesium.Cartesian3.fromDegrees(9.459241655716186, -16.152092087579025, 501642.9031481749));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:31:00+00:00\", Cesium.Cartesian3.fromDegrees(9.07505908952084, -14.258555183913842, 501287.65491341887));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:31:30+00:00\", Cesium.Cartesian3.fromDegrees(8.695146166087302, -12.364371646842592, 500973.1363076525));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:32:00+00:00\", Cesium.Cartesian3.fromDegrees(8.318860194833796, -10.469628667401853, 500700.7468394011));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:32:30+00:00\", Cesium.Cartesian3.fromDegrees(7.945591859381568, -8.574412809693486, 500471.6990118566));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:33:00+00:00\", Cesium.Cartesian3.fromDegrees(7.574759088814816, -6.678810186356989, 500287.0127268138));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:33:30+00:00\", Cesium.Cartesian3.fromDegrees(7.2058014562829324, -4.782906593069165, 500147.5105716122));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:34:00+00:00\", Cesium.Cartesian3.fromDegrees(6.838174987960179, -2.8867876108253196, 500053.8140139325));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:34:30+00:00\", Cesium.Cartesian3.fromDegrees(6.471347278768828, -0.9905386839228563, 500006.3405246064));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:35:00+00:00\", Cesium.Cartesian3.fromDegrees(6.1047928210641205, 0.9057548190420274, 500005.3016437287));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:35:30+00:00\", Cesium.Cartesian3.fromDegrees(5.737988459225639, 2.8020075542670195, 500050.7020003768));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:36:00+00:00\", Cesium.Cartesian3.fromDegrees(5.370408718880848, 4.698134155270786, 500142.3392911794));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:36:30+00:00\", Cesium.Cartesian3.fromDegrees(5.001521937543872, 6.5940491822800915, 500279.8052177833));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:37:00+00:00\", Cesium.Cartesian3.fromDegrees(4.630784592175432, 8.48966706182752, 500462.4873782902));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:37:30+00:00\", Cesium.Cartesian3.fromDegrees(4.257637098730488, 10.384902009679097, 500689.5721025413));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:38:00+00:00\", Cesium.Cartesian3.fromDegrees(3.881498468860959, 12.279667929801029, 500960.04821628));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:38:30+00:00\", Cesium.Cartesian3.fromDegrees(3.50176072923468, 14.173878281478657, 501272.71171409386));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:39:00+00:00\", Cesium.Cartesian3.fromDegrees(3.1177828190721746, 16.067445905873832, 501626.17131660075));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:39:30+00:00\", Cesium.Cartesian3.fromDegrees(2.72888383211098, 17.96028280221575, 502018.85488258937));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:40:00+00:00\", Cesium.Cartesian3.fromDegrees(2.3343354466444906, 19.85229984239388, 502449.01664263016));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:40:30+00:00\", Cesium.Cartesian3.fromDegrees(1.9333533584266476, 21.7434064108876, 502914.7452165162));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:41:00+00:00\", Cesium.Cartesian3.fromDegrees(1.5250874943062667, 23.633509954613018, 503413.97237311426));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:41:30+00:00\", Cesium.Cartesian3.fromDegrees(1.1086107377408885, 25.522515424252465, 503944.48248771887));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:42:00+00:00\", Cesium.Cartesian3.fromDegrees(0.6829058375670721, 27.410324584763647, 504503.92264887743));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:42:30+00:00\", Cesium.Cartesian3.fromDegrees(0.24685009514204756, 29.296835167794068, 505089.81336355855));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:43:00+00:00\", Cesium.Cartesian3.fromDegrees(-0.2008026728434789, 31.181939832304185, 505699.55980740604));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:43:30+00:00\", Cesium.Cartesian3.fromDegrees(-0.6614435249207059, 33.06552489137243, 506330.4635642186));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:44:00+00:00\", Cesium.Cartesian3.fromDegrees(-1.136633931530598, 34.94746875228285, 506979.7347973979));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:44:30+00:00\", Cesium.Cartesian3.fromDegrees(-1.6281364646493215, 36.827640002715036, 507644.5047943661));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:45:00+00:00\", Cesium.Cartesian3.fromDegrees(-2.1379519286206956, 38.705895056961644, 508321.83882393147));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:45:30+00:00\", Cesium.Cartesian3.fromDegrees(-2.668364593668249, 40.58207525090352, 509008.7492459364));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:46:00+00:00\", Cesium.Cartesian3.fromDegrees(-3.2219976924632503, 42.45600324058878, 509702.20881196647));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:46:30+00:00\", Cesium.Cartesian3.fromDegrees(-3.8018820128016215, 44.327478513275416, 510399.1640958789));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:47:00+00:00\", Cesium.Cartesian3.fromDegrees(-4.411541503223743, 46.19627175676522, 511096.54899312154));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:47:30+00:00\", Cesium.Cartesian3.fromDegrees(-5.055099890199524, 48.0621177455532, 511791.298228331));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:48:00+00:00\", Cesium.Cartesian3.fromDegrees(-5.737417583374546, 49.92470628000877, 512480.36081152194));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:48:30+00:00\", Cesium.Cartesian3.fromDegrees(-6.4642647157296125, 51.783670541410004, 513160.71338427346));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:49:00+00:00\", Cesium.Cartesian3.fromDegrees(-7.24254553352347, 53.638571976600886, 513829.37339845696));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:49:30+00:00\", Cesium.Cartesian3.fromDegrees(-8.080590828509507, 55.488880463416024, 514483.4120718708));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:50:00+00:00\", Cesium.Cartesian3.fromDegrees(-8.988543567041054, 57.33394797218925, 515119.96706659946));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:50:30+00:00\", Cesium.Cartesian3.fromDegrees(-9.978873436987506, 59.172973134468506, 515736.2548379796));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:51:00+00:00\", Cesium.Cartesian3.fromDegrees(-11.067072050394119, 61.00495290291618, 516329.5826041209));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:51:30+00:00\", Cesium.Cartesian3.fromDegrees(-12.272604735017042, 62.82861558082195, 516897.3598881027));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:52:00+00:00\", Cesium.Cartesian3.fromDegrees(-13.620231807503009, 64.64232648603164, 517437.1095873548));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:52:30+00:00\", Cesium.Cartesian3.fromDegrees(-15.141869173827256, 66.44395265747539, 517946.47852712875));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:53:00+00:00\", Cesium.Cartesian3.fromDegrees(-16.87924620204164, 68.23066503687464, 518423.24745757657));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:53:30+00:00\", Cesium.Cartesian3.fromDegrees(-18.887754283020456, 69.99864322467181, 518865.3404565907));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:54:00+00:00\", Cesium.Cartesian3.fromDegrees(-21.24208235934019, 71.74262528396027, 519270.8337030503));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:54:30+00:00\", Cesium.Cartesian3.fromDegrees(-24.044517336030477, 73.4552063655887, 519637.96358820423));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:55:00+00:00\", Cesium.Cartesian3.fromDegrees(-27.43709658339608, 75.12572421230743, 519965.1341352664));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:55:30+00:00\", Cesium.Cartesian3.fromDegrees(-31.618829600092294, 76.7384627275978, 520250.9237005726));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:56:00+00:00\", Cesium.Cartesian3.fromDegrees(-36.86776657704847, 78.26975425042454, 520494.09093199205));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:56:30+00:00\", Cesium.Cartesian3.fromDegrees(-43.56094193606876, 79.68345020256388, 520693.5799635584));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:57:00+00:00\", Cesium.Cartesian3.fromDegrees(-52.163192552605835, 80.92460061186564, 520848.5248278875));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:57:30+00:00\", Cesium.Cartesian3.fromDegrees(-63.104697351166074, 81.91351292073773, 520958.2530708835));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:58:00+00:00\", Cesium.Cartesian3.fromDegrees(-76.42431760661306, 82.54918237431579, 521022.28855611547));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:58:30+00:00\", Cesium.Cartesian3.fromDegrees(-91.26461427537956, 82.73831271064938, 521040.35344916524));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:59:00+00:00\", Cesium.Cartesian3.fromDegrees(-105.90321814567902, 82.44730197482923, 521012.3693749638));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T01:59:30+00:00\", Cesium.Cartesian3.fromDegrees(-118.74590143183833, 81.72663570004366, 520938.45774420054));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:00:00+00:00\", Cesium.Cartesian3.fromDegrees(-129.15878740200174, 80.67534523908161, 520818.93924770784));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:00:30+00:00\", Cesium.Cartesian3.fromDegrees(-137.30861605394608, 79.39118279801033, 520654.3325204021));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:01:00+00:00\", Cesium.Cartesian3.fromDegrees(-143.6535591628729, 77.94825452457741, 520445.3519796203));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:01:30+00:00\", Cesium.Cartesian3.fromDegrees(-148.64425141594637, 76.39687054233647, 520192.9048451947));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:02:00+00:00\", Cesium.Cartesian3.fromDegrees(-152.6355056008026, 74.77001009508037, 519898.08735166804));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:02:30+00:00\", Cesium.Cartesian3.fromDegrees(-155.88636158653563, 73.08930840544613, 519562.1801659232));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:03:00+00:00\", Cesium.Cartesian3.fromDegrees(-158.58182029054137, 71.36919316871214, 519186.64302635984));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:03:30+00:00\", Cesium.Cartesian3.fromDegrees(-160.8540862886609, 69.61950153228285, 518773.1086224584));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:04:00+00:00\", Cesium.Cartesian3.fromDegrees(-162.79862473625218, 67.8470997683861, 518323.3757367888));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:04:30+00:00\", Cesium.Cartesian3.fromDegrees(-164.48537220928205, 66.05689043218273, 517839.40167388436));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:05:00+00:00\", Cesium.Cartesian3.fromDegrees(-165.96637234011504, 64.25244870600984, 517323.29400369804));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:05:30+00:00\", Cesium.Cartesian3.fromDegrees(-167.28096286892207, 62.43643272224014, 516777.301649807));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:06:00+00:00\", Cesium.Cartesian3.fromDegrees(-168.45932538062794, 60.61085391489719, 516203.8053554825));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:06:30+00:00\", Cesium.Cartesian3.fromDegrees(-169.5249436581278, 58.77725898013542, 515605.30756343156));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:07:00+00:00\", Cesium.Cartesian3.fromDegrees(-170.49632988024686, 56.93685485709969, 514984.42174760846));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:07:30+00:00\", Cesium.Cartesian3.fromDegrees(-171.38825425919032, 55.090596221523654, 514343.86123826203));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:08:00+00:00\", Cesium.Cartesian3.fromDegrees(-172.2126335122648, 53.239247828539305, 513686.4275837223));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:08:30+00:00\", Cesium.Cartesian3.fromDegrees(-172.97918170462953, 51.383429666142874, 513014.99849498365));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:09:00+00:00\", Cesium.Cartesian3.fromDegrees(-173.69589329364916, 49.523650154872115, 512332.51542145945));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:09:30+00:00\", Cesium.Cartesian3.fromDegrees(-174.3694062580661, 47.66033089872983, 511641.9708083982));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:10:00+00:00\", Cesium.Cartesian3.fromDegrees(-175.00527734056382, 45.7938253736752, 510946.3950885711));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:10:30+00:00\", Cesium.Cartesian3.fromDegrees(-175.60819509846073, 43.924433204188915, 510248.8434626312));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:11:00+00:00\", Cesium.Cartesian3.fromDegrees(-176.18214386104668, 42.0524111864549, 509552.3825243892));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:11:30+00:00\", Cesium.Cartesian3.fromDegrees(-176.73053294889854, 40.177981882684634, 508860.076788529));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:12:00+00:00\", Cesium.Cartesian3.fromDegrees(-177.25629875272168, 38.30134038101089, 508174.9751797051));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:12:30+00:00\", Cesium.Cartesian3.fromDegrees(-177.76198616734908, 36.42265965471515, 507500.0975429317));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:13:00+00:00\", Cesium.Cartesian3.fromDegrees(-178.24981408140377, 34.5420948409269, 506838.42123584123));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:13:30+00:00\", Cesium.Cartesian3.fromDegrees(-178.7217284491364, 32.659786677626386, 506192.867863982));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:14:00+00:00\", Cesium.Cartesian3.fromDegrees(-179.17944561474482, 30.775864278937437, 505566.2902203723));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:14:30+00:00\", Cesium.Cartesian3.fromDegrees(-179.62448792925528, 28.89044738567743, 504961.4594904507));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:15:00+00:00\", Cesium.Cartesian3.fromDegrees(179.94178676823708, 27.00364819636468, 504381.0527829646));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:15:30+00:00\", Cesium.Cartesian3.fromDegrees(179.51816058415264, 25.115572860221544, 503827.6410467364));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:16:00+00:00\", Cesium.Cartesian3.fromDegrees(179.10353496318635, 23.226322695933373, 503303.6774317281));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:16:30+00:00\", Cesium.Cartesian3.fromDegrees(178.6969132864886, 21.335995186466025, 502811.4861516829));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:17:00+00:00\", Cesium.Cartesian3.fromDegrees(178.29738607627567, 19.44468478998351, 502353.25190337683));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:17:30+00:00\", Cesium.Cartesian3.fromDegrees(177.90411832738144, 17.552483599034368, 501931.0098956087));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:18:00+00:00\", Cesium.Cartesian3.fromDegrees(177.5163385789333, 15.659481874103067, 501546.63653810596));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:18:30+00:00\", Cesium.Cartesian3.fromDegrees(177.13332941165427, 13.765768472909262, 501201.84083804535));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:19:00+00:00\", Cesium.Cartesian3.fromDegrees(176.75441911299356, 11.871431193177534, 500898.15654807707));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:19:30+00:00\", Cesium.Cartesian3.fromDegrees(176.3789742966597, 9.976557043738131, 500636.9351067115));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:20:00+00:00\", Cesium.Cartesian3.fromDegrees(176.006393298206, 8.081232456590053, 500419.3394077307));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:20:30+00:00\", Cesium.Cartesian3.fromDegrees(175.63610019562216, 6.18554345081802, 500246.33843120496));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:21:00+00:00\", Cesium.Cartesian3.fromDegrees(175.2675391572243, 4.289575757908757, 500118.70276443317));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:21:30+00:00\", Cesium.Cartesian3.fromDegrees(174.9001700123255, 2.393414916979529, 500037.0010364557));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:22:00+00:00\", Cesium.Cartesian3.fromDegrees(174.5334624224442, 0.49714634766264787, 500001.5972850214));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:22:30+00:00\", Cesium.Cartesian3.fromDegrees(174.1668919233058, -1.399144592171316, 500012.64927008236));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:23:00+00:00\", Cesium.Cartesian3.fromDegrees(173.799935230314, -3.2953725570313095, 500070.10774259723));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:23:30+00:00\", Cesium.Cartesian3.fromDegrees(173.43206573358242, -5.191452166144861, 500173.7166728911));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:24:00+00:00\", Cesium.Cartesian3.fromDegrees(173.06274893248445, -7.087297950941766, 500323.01443696476));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:24:30+00:00\", Cesium.Cartesian3.fromDegrees(172.69143772595686, -8.982824290986935, 500517.33595468244));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:25:00+00:00\", Cesium.Cartesian3.fromDegrees(172.31756747030133, -10.877945331392024, 500755.8157684324));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:25:30+00:00\", Cesium.Cartesian3.fromDegrees(171.94055070884522, -12.772574874280426, 501037.39204579405));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:26:00+00:00\", Cesium.Cartesian3.fromDegrees(171.55977146728233, -14.666626236225897, 501360.81148515246));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:26:30+00:00\", Cesium.Cartesian3.fromDegrees(171.1745789942984, -16.560012062696096, 501724.63509830233));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:27:00+00:00\", Cesium.Cartesian3.fromDegrees(170.7842808083441, -18.45264408935846, 502127.2448397432));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:27:30+00:00\", Cesium.Cartesian3.fromDegrees(170.38813488735812, -20.344432838583682, 502566.8510479958));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:28:00+00:00\", Cesium.Cartesian3.fromDegrees(169.98534080745478, -22.23528723752406, 503041.5006603348));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:28:30+00:00\", Cesium.Cartesian3.fromDegrees(169.5750295973613, -24.1251141416318, 503549.0861585852));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:29:00+00:00\", Cesium.Cartesian3.fromDegrees(169.1562520255705, -26.013817744268547, 504087.3552002067));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:29:30+00:00\", Cesium.Cartesian3.fromDegrees(168.72796497349185, -27.901298848926928, 504653.92088583193));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:30:00+00:00\", Cesium.Cartesian3.fromDegrees(168.28901546661467, -29.787453975274207, 505246.27261145914));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:30:30+00:00\", Cesium.Cartesian3.fromDegrees(167.83812183114048, -31.67217426335989, 505861.7874514589));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:31:00+00:00\", Cesium.Cartesian3.fromDegrees(167.37385130851197, -33.55534413140548, 506497.7420160348));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:31:30+00:00\", Cesium.Cartesian3.fromDegrees(166.89459328479367, -35.43683963093145, 507151.3247254321));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:32:00+00:00\", Cesium.Cartesian3.fromDegrees(166.39852689411745, -37.31652642762592, 507819.6484415539));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:32:30+00:00\", Cesium.Cartesian3.fromDegrees(165.88358262940872, -39.19425731601344, 508499.7633968974));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:33:00+00:00\", Cesium.Cartesian3.fromDegrees(165.347393661357, -41.06986914878751, 509188.6703597659));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:33:30+00:00\", Cesium.Cartesian3.fromDegrees(164.78723791130707, -42.94317902502271, 509883.3339746536));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:34:00+00:00\", Cesium.Cartesian3.fromDegrees(164.19996531206436, -44.81397953160567, 510580.6962165304));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:34:30+00:00\", Cesium.Cartesian3.fromDegrees(163.58190722692711, -46.68203276369342, 511277.68989809585));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:35:00+00:00\", Cesium.Cartesian3.fromDegrees(162.92876245129924, -48.547062754801374, 511971.2521697295));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:35:30+00:00\", Cesium.Cartesian3.fromDegrees(162.23545248215694, -50.40874581334991, 512658.3379526461));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:36:00+00:00\", Cesium.Cartesian3.fromDegrees(161.49593605548333, -52.266698072210616, 513335.9332469342));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:36:30+00:00\", Cesium.Cartesian3.fromDegrees(160.7029691268167, -54.12045928354186, 514001.0682575881));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:37:00+00:00\", Cesium.Cartesian3.fromDegrees(159.84779095597753, -55.96947149037744, 514650.830283107));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:37:30+00:00\", Cesium.Cartesian3.fromDegrees(158.91970890835387, -57.81305061181537, 515282.37631305796));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:38:00+00:00\", Cesium.Cartesian3.fromDegrees(157.90554268726797, -59.65034808244533, 515892.9452830966));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:38:30+00:00\", Cesium.Cartesian3.fromDegrees(156.78887090073331, -61.48029831299158, 516479.86993778346));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:39:00+00:00\", Cesium.Cartesian3.fromDegrees(155.54899587834583, -63.30154559605312, 517040.5882540407));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:39:30+00:00\", Cesium.Cartesian3.fromDegrees(154.159501322441, -65.11234067500604, 517572.65438032994));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:40:00+00:00\", Cesium.Cartesian3.fromDegrees(152.58621358519062, -66.91039167835258, 518073.74904919224));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:40:30+00:00\", Cesium.Cartesian3.fromDegrees(150.78427871592663, -68.69264502015265, 518541.68942321173));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:41:00+00:00\", Cesium.Cartesian3.fromDegrees(148.69391637507454, -70.45495658603429, 518974.43833732343));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:41:30+00:00\", Cesium.Cartesian3.fromDegrees(146.23418843935872, -72.19158751697027, 519370.1129028848));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:42:00+00:00\", Cesium.Cartesian3.fromDegrees(143.29382130344996, -73.89441441369763, 519726.99244178727));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:42:30+00:00\", Cesium.Cartesian3.fromDegrees(139.71783569178402, -75.5516687243367, 520043.52572161594));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:43:00+00:00\", Cesium.Cartesian3.fromDegrees(135.28891317119, -77.1459007631398, 520318.33746571833));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:43:30+00:00\", Cesium.Cartesian3.fromDegrees(129.7047040479027, -78.65070842154365, 520550.234114851));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:44:00+00:00\", Cesium.Cartesian3.fromDegrees(122.56171566360003, -80.02571608625895, 520738.2088199259));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:44:30+00:00\", Cesium.Cartesian3.fromDegrees(113.384977829587, -81.20996561735971, 520881.4456482458));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:45:00+00:00\", Cesium.Cartesian3.fromDegrees(101.80044842306854, -82.11715280723617, 520979.32298847125));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:45:30+00:00\", Cesium.Cartesian3.fromDegrees(87.9586904062353, -82.64414952846583, 521031.4161424525));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:46:00+00:00\", Cesium.Cartesian3.fromDegrees(72.98790359032388, -82.7081101100689, 521037.49909495556));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:46:30+00:00\", Cesium.Cartesian3.fromDegrees(58.69557917028935, -82.29749711830864, 520997.5454550519));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:47:00+00:00\", Cesium.Cartesian3.fromDegrees(46.46556426924445, -81.48061980562845, 520911.7285660751));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:47:30+00:00\", Cesium.Cartesian3.fromDegrees(36.677365297833475, -80.36014187630758, 520780.42078358866));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:48:00+00:00\", Cesium.Cartesian3.fromDegrees(29.04402211908452, -79.02859730464526, 520604.19192401005));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:48:30+00:00\", Cesium.Cartesian3.fromDegrees(23.091410387351104, -77.55343343110597, 520383.8068891903));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:49:00+00:00\", Cesium.Cartesian3.fromDegrees(18.39071477434518, -75.97978922965925, 520120.22247514414));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:49:30+00:00\", Cesium.Cartesian3.fromDegrees(14.613616782573732, -74.33718989119004, 519814.58337620005));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:50:00+00:00\", Cesium.Cartesian3.fromDegrees(11.522593834814476, -72.64506850025201, 519468.21739836136));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:50:30+00:00\", Cesium.Cartesian3.fromDegrees(8.948234665510743, -70.91645523532945, 519082.6298989306));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:51:00+00:00\", Cesium.Cartesian3.fromDegrees(6.7692229187467765, -69.16028866561427, 518659.4974719566));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:51:30+00:00\", Cesium.Cartesian3.fromDegrees(4.897647396640505, -67.38284554349102, 518200.66090216));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:52:00+00:00\", Cesium.Cartesian3.fromDegrees(3.268845583507671, -65.5886329526647, 517708.1174127873));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:52:30+00:00\", Cesium.Cartesian3.fromDegrees(1.834500851053595, -63.78095483692992, 517184.0122354818));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:53:00+00:00\", Cesium.Cartesian3.fromDegrees(0.5579473694726861, -61.962279348558816, 516630.62953335344));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:53:30+00:00\", Cesium.Cartesian3.fromDegrees(-0.5890519737559708, -60.13448224558599, 516050.38271094096));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:54:00+00:00\", Cesium.Cartesian3.fromDegrees(-1.6285447935683612, -58.299011596840316, 515445.8041475929));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:54:30+00:00\", Cesium.Cartesian3.fromDegrees(-2.5779675661283123, -56.45700148707586, 514819.5343933315));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:55:00+00:00\", Cesium.Cartesian3.fromDegrees(-3.4512733696043796, -54.609351994417985, 514174.31086910976));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:55:30+00:00\", Cesium.Cartesian3.fromDegrees(-4.259751191367272, -52.7567864276439, 513512.95611549553));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:56:00+00:00\", Cesium.Cartesian3.fromDegrees(-5.012626777387922, -50.89989294955182, 512838.3656365703));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:56:30+00:00\", Cesium.Cartesian3.fromDegrees(-5.717510708048135, -49.039155295041596, 512153.49538790097));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:57:00+00:00\", Cesium.Cartesian3.fromDegrees(-6.380735999547074, -47.17497575032658, 511461.3489596675));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:57:30+00:00\", Cesium.Cartesian3.fromDegrees(-7.007615486926174, -45.3076925581469, 510764.9645080608));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:58:00+00:00\", Cesium.Cartesian3.fromDegrees(-7.602640163621876, -43.43759325222386, 510067.40148983285));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:58:30+00:00\", Cesium.Cartesian3.fromDegrees(-8.169633566456284, -41.5649249800242, 509371.7272565973));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:59:00+00:00\", Cesium.Cartesian3.fromDegrees(-8.711873087096642, -39.689902570157315, 508681.0035667502));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T02:59:30+00:00\", Cesium.Cartesian3.fromDegrees(-9.23218614609716, -37.8127148914289, 507998.2730743476));\n", - " widget.property_9bfe1ee8.addSample(\"2023-01-01T03:00:00+00:00\", Cesium.Cartesian3.fromDegrees(-9.733027080406703, -35.93352990392803, 507326.54585491726));\n", - " widget.property_84f93f67 = new Cesium.SampledProperty(Cesium.Quaternion);\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:00:00+00:00\", new Cesium.Quaternion(0.225870746218323, -0.6695369062609688, 0.13911886637469034, 0.693792964922454));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:00:30+00:00\", new Cesium.Quaternion(0.22740326811385295, -0.6811959792253213, 0.13461027180213792, 0.6827443637729641));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:01:00+00:00\", new Cesium.Quaternion(0.22884831234911612, -0.6926718542220105, 0.13008915274085728, 0.6714990429202183));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:01:30+00:00\", new Cesium.Quaternion(0.2302058867199159, -0.7039611994206347, 0.12555717248812823, 0.660060054742404));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:02:00+00:00\", new Cesium.Quaternion(0.23147603017609403, -0.7150607340957256, 0.12101599059291675, 0.648430508249892));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:02:30+00:00\", new Cesium.Quaternion(0.23265881269839941, -0.725967229592505, 0.11646726227910868, 0.636613568225469));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:03:00+00:00\", new Cesium.Quaternion(0.23375433516463806, -0.7366775102781513, 0.11191263787169166, 0.6246124543480717));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:03:30+00:00\", new Cesium.Quaternion(0.23476272920535185, -0.7471884544782379, 0.10735376222625476, 0.6124304403002397));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:04:00+00:00\", new Cesium.Quaternion(0.23568415704916315, -0.7574969953980396, 0.10279227416203772, 0.6000708528595307));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:04:30+00:00\", new Cesium.Quaternion(0.2365188113575476, -0.767600122028534, 0.09822980589846257, 0.5875370709742008));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:05:00+00:00\", new Cesium.Quaternion(0.23726691504946898, -0.7774948800367182, 0.09366798249563026, 0.5748325248233572));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:05:30+00:00\", new Cesium.Quaternion(0.23792872111579602, -0.7871783726400192, 0.08910842129883272, 0.5619606948618767));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:06:00+00:00\", new Cesium.Quaternion(0.23850451125486227, -0.7966477618144392, 0.08455273058195828, 0.5489251109744016));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:06:30+00:00\", new Cesium.Quaternion(0.23899460032774378, -0.8059002677375983, 0.08000251224096304, 0.5357293509877765));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:07:00+00:00\", new Cesium.Quaternion(0.2393993291716508, -0.8149331717108688, 0.07545935636216387, 0.5223770404361541));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:07:30+00:00\", new Cesium.Quaternion(0.23971906900775275, -0.8237438155704697, 0.0709248439633663, 0.5088718510315073));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:08:00+00:00\", new Cesium.Quaternion(0.23995422005096206, -0.8323296028276064, 0.06640054563674273, 0.4952174997672402));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:08:30+00:00\", new Cesium.Quaternion(0.24010521126510204, -0.8406879994420968, 0.061888021021368776, 0.48141774787750036));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:09:00+00:00\", new Cesium.Quaternion(0.24017250010839575, -0.8488165345784013, 0.05738881828095242, 0.46747639978325356));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:09:30+00:00\", new Cesium.Quaternion(0.24015657226952447, -0.8567128013437878, 0.05290447358701884, 0.4533973020254009));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:10:00+00:00\", new Cesium.Quaternion(0.24005794139451492, -0.864374457508369, 0.048436510607798966, 0.43918434218523916));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:10:30+00:00\", new Cesium.Quaternion(0.23987714880411865, -0.8717992262069187, 0.04398644000274705, 0.424841447792596));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:11:00+00:00\", new Cesium.Quaternion(0.23961476320253516, -0.878984896622055, 0.039555758923237705, 0.4103725852219116));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:11:30+00:00\", new Cesium.Quaternion(0.23927138037680068, -0.8859293246487991, 0.03514595051918822, 0.39578175857662523));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:12:00+00:00\", new Cesium.Quaternion(0.23884762288745642, -0.8926304335401783, 0.030758483452027932, 0.38107300856215987));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:12:30+00:00\", new Cesium.Quaternion(0.23834413975060548, -0.8990862145336801, 0.026394811414147373, 0.3662504113478276));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:13:00+00:00\", new Cesium.Quaternion(0.2377616061112025, -0.9052947274584419, 0.022056372654859286, 0.351318077417996));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:13:30+00:00\", new Cesium.Quaternion(0.2371007229080448, -0.9112541013229063, 0.017744589513172027, 0.33628015041282816));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:14:00+00:00\", new Cesium.Quaternion(0.2363622165302961, -0.9169625348828384, 0.013460867957399262, 0.32114080595894146));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:14:30+00:00\", new Cesium.Quaternion(0.23554683846602725, -0.9224182971894435, 0.009206597131886684, 0.3059042504903098));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:15:00+00:00\", new Cesium.Quaternion(0.2346553649425145, -0.9276197281175199, 0.004983148910851656, 0.29057472005975704));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:15:30+00:00\", new Cesium.Quaternion(0.23368859655870333, -0.9325652388734175, 0.0007918774595805631, 0.27515647914137664));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:16:00+00:00\", new Cesium.Quaternion(0.23264735790996727, -0.9372533124826465, -0.0033658811968886706, 0.25965381942422233));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:16:30+00:00\", new Cesium.Quaternion(0.23153249720518881, -0.9416825042570238, -0.007488809597500302, 0.24407105859761796));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:17:00+00:00\", new Cesium.Quaternion(0.23034488448898166, -0.9458514425790615, -0.011575609596212696, 0.2284125391114558));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:17:30+00:00\", new Cesium.Quaternion(0.22908541678815741, -0.9497588279742954, -0.015625001406813038, 0.2126826270077702));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:18:00+00:00\", new Cesium.Quaternion(0.22775500939963012, -0.953403435548934, -0.019635726082516066, 0.1968857105990089));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:18:30+00:00\", new Cesium.Quaternion(0.22635460101062027, -0.9567841140167468, -0.023606544498680836, 0.18102619927331925));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:19:00+00:00\", new Cesium.Quaternion(0.2248851518985464, -0.959899786401397, -0.027536238094606723, 0.16510852223225012));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:19:30+00:00\", new Cesium.Quaternion(0.2233476435058086, -0.962749450377826, -0.03142360924889237, 0.1491371272331917));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:20:00+00:00\", new Cesium.Quaternion(0.22174307800784354, -0.9653321785923245, -0.035267481646353564, 0.13311647932592077));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:20:30+00:00\", new Cesium.Quaternion(0.22007247787504552, -0.9676471189610811, -0.03906670063631043, 0.11705105958362941));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:21:00+00:00\", new Cesium.Quaternion(0.21833688542831226, -0.9696934949472129, -0.04282013358220184, 0.1009453638287878));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:21:30+00:00\", new Cesium.Quaternion(0.21653736238864885, -0.9714706058161258, -0.046526670202374484, 0.0848039013542212));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:22:00+00:00\", new Cesium.Quaternion(0.21467498942106394, -0.9729778268691063, -0.05018522290194801, 0.06863119363977042));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:22:30+00:00\", new Cesium.Quaternion(0.21275086567251977, -0.9742146096551647, -0.05379472709569319, 0.052431773064891773));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:23:00+00:00\", new Cesium.Quaternion(0.21076610830465997, -0.975180482160933, -0.05735414152177461, 0.03621018161759086));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:23:30+00:00\", new Cesium.Quaternion(0.2087218520209978, -0.9758750489786628, -0.06086244854630584, 0.019970969600042462));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:24:00+00:00\", new Cesium.Quaternion(0.20661924858909725, -0.9762979914521912, -0.06431865445860062, 0.0037186943312858926));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:24:30+00:00\", new Cesium.Quaternion(0.20445946635778905, -0.9764490678008515, -0.06772178975704693, -0.012542081152632261));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:25:00+00:00\", new Cesium.Quaternion(0.20224368976947948, -0.9763281132213086, -0.07107090942551754, -0.02880678940070158));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:25:30+00:00\", new Cesium.Quaternion(0.19997311886799124, -0.9759350399672306, -0.0743650932002339, -0.04507085985078382));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:26:00+00:00\", new Cesium.Quaternion(0.19764896880191757, -0.9752698374068023, -0.0776034458270106, -0.06132972013487677));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:26:30+00:00\", new Cesium.Quaternion(0.19527246932374265, -0.9743325720580457, -0.08078509730880433, -0.07757879738542352));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:27:00+00:00\", new Cesium.Quaternion(0.19284486428497621, -0.9731233876019122, -0.08390920314350428, -0.0938135195422803));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:27:30+00:00\", new Cesium.Quaternion(0.19036741112729327, -0.971642504873179, -0.0869749445518833, -0.11002931665998487));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:28:00+00:00\", new Cesium.Quaternion(-0.18784138037012765, 0.9698902218290841, 0.08998152869566532, 0.126221622214921));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:28:30+00:00\", new Cesium.Quaternion(-0.185268053674913, 0.9678669137675237, 0.09292818867676562, 0.14238587454833526));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:29:00+00:00\", new Cesium.Quaternion(-0.18264872900842966, 0.9655730321602907, 0.09581418454722124, 0.15851751763113997));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:29:30+00:00\", new Cesium.Quaternion(-0.17998471159192286, 0.9630091061971893, 0.09863880231505157, 0.17461200317365205));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:30:00+00:00\", new Cesium.Quaternion(-0.1772773190643528, 0.9601757415673247, 0.10140135488658962, 0.1906647913962041));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:30:30+00:00\", new Cesium.Quaternion(-0.17452787953168974, 0.9570736205922783, 0.1041011820491199, 0.20667135246215365));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:31:00+00:00\", new Cesium.Quaternion(-0.171737731036317, 0.9537035020616265, 0.10673765062845715, 0.22262716777654146));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:31:30+00:00\", new Cesium.Quaternion(-0.16890822102423464, 0.9500662210463423, 0.10931015463632031, 0.23852773128199373));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:32:00+00:00\", new Cesium.Quaternion(-0.16604070581003688, 0.9461626886901706, 0.11181811540742567, 0.25436855075151094));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:32:30+00:00\", new Cesium.Quaternion(-0.1631365500400233, 0.9419938919789986, 0.11426098172630411, 0.2701451490777488));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:33:00+00:00\", new Cesium.Quaternion(-0.16019712615342158, 0.9375608934883168, 0.11663822994376316, 0.2858530655584436));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:33:30+00:00\", new Cesium.Quaternion(-0.157223813842174, 0.9328648311087933, 0.11894936408303322, 0.30148785717757554));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:34:00+00:00\", new Cesium.Quaternion(-0.15421799950936155, 0.9279069177500543, 0.12119391593555542, 0.3170450998819104));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:34:30+00:00\", new Cesium.Quaternion(-0.15118107572633765, 0.9226884410227688, 0.12337144514634889, 0.3325203898525647));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:35:00+00:00\", new Cesium.Quaternion(-0.14811444068902802, 0.9172107628990802, 0.1254815392890299, 0.3479093447711911));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:35:30+00:00\", new Cesium.Quaternion(-0.14501949767338773, 0.9114753193515078, 0.1275238139304084, 0.3632076050804385));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:36:00+00:00\", new Cesium.Quaternion(-0.14189765449027675, 0.9054836199704069, 0.12949791268467922, 0.3784108352383124));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:36:30+00:00\", new Cesium.Quaternion(-0.1387503229400221, 0.8992372475600767, 0.13140350725723382, 0.39351472496606127));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:37:00+00:00\", new Cesium.Quaternion(-0.1355789182666441, 0.8927378577136662, 0.1332402974780079, 0.40851499048925083));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:37:30+00:00\", new Cesium.Quaternion(-0.13238485861227522, 0.8859871783669324, 0.135008011324509, 0.4234073757716212));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:38:00+00:00\", new Cesium.Quaternion(-0.12916956447167688, 0.8789870093310306, 0.13670640493441402, 0.4381876537414038));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:38:30+00:00\", new Cesium.Quaternion(-0.12593445814703108, 0.8717392218044558, 0.13833526260772736, 0.45285162750974733));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:39:00+00:00\", new Cesium.Quaternion(-0.12268096320370009, 0.8642457578642027, 0.13989439679876697, 0.4673951315808196));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:39:30+00:00\", new Cesium.Quaternion(-0.11941050266989589, 0.8565086301115724, 0.1413836473908103, 0.4818140332607507));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:40:00+00:00\", new Cesium.Quaternion(-0.11612450353153703, 0.8485299204168331, 0.14280288447355902, 0.49610423302264695));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:40:30+00:00\", new Cesium.Quaternion(-0.11282438861728467, 0.8403117804145525, 0.1441520041264144, 0.5102616669278611));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:41:00+00:00\", new Cesium.Quaternion(-0.10951158111850468, 0.831856430198268, 0.14543093113302277, 0.524282306976405));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:41:30+00:00\", new Cesium.Quaternion(-0.10618750278291306, 0.8231661578902336, 0.14663961823613303, 0.5381621624756998));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:42:00+00:00\", new Cesium.Quaternion(-0.1028535733776369, 0.814243319011426, 0.14777804606783507, 0.5518972811937755));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:42:30+00:00\", new Cesium.Quaternion(-0.0995112101544039, 0.8050903358319115, 0.14884622306978462, 0.5654837505017505));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:43:00+00:00\", new Cesium.Quaternion(-0.09616182731660988, 0.7957096967018064, 0.14984418540317265, 0.5789176985053314));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:43:30+00:00\", new Cesium.Quaternion(-0.09280683548893809, 0.7861039553629652, 0.15077199684880893, 0.592195295164909));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:44:00+00:00\", new Cesium.Quaternion(-0.08944764118929072, 0.7762757302416378, 0.15162974869708581, 0.6053127534040091));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:44:30+00:00\", new Cesium.Quaternion(-0.08608564630352761, 0.7662277037222582, 0.15241755962808876, 0.6182663302057109));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:45:00+00:00\", new Cesium.Quaternion(-0.08272224756308427, 0.7559626214025876, 0.15313557558184415, 0.6310523276967268));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:45:30+00:00\", new Cesium.Quaternion(-0.07935883602549243, 0.7454832913304303, 0.15378396961862928, 0.6436670942188705));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:46:00+00:00\", new Cesium.Quaternion(-0.07599679655835079, 0.7347925832221107, 0.15436294176970541, 0.6561070253875115));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:46:30+00:00\", new Cesium.Quaternion(-0.07263750732659563, 0.7238934276629582, 0.1548727188782841, 0.668368565136782));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:47:00+00:00\", new Cesium.Quaternion(-0.06928233928332767, 0.7127888152900206, 0.15531355443084446, 0.6804482067512092));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:47:30+00:00\", new Cesium.Quaternion(-0.06593265566455508, 0.7014817959572243, 0.15568572837905104, 0.6923424938834326));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:48:00+00:00\", new Cesium.Quaternion(-0.0625898114877288, 0.6899754778832415, 0.1559895469520746, 0.7040480215577696));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:48:30+00:00\", new Cesium.Quaternion(-0.05925515305457113, 0.6782730267822767, 0.15622534245970685, 0.7155614371592672));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:49:00+00:00\", new Cesium.Quaternion(-0.05593001745801113, 0.6663776649780566, 0.15639347308600224, 0.7268794414080216));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:49:30+00:00\", new Cesium.Quaternion(-0.05261573209378584, 0.6542926705012361, 0.15649432267392532, 0.7379987893184009));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:50:00+00:00\", new Cesium.Quaternion(-0.049313614176583365, 0.6420213761705056, 0.15652830050080127, 0.7489162911429452));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:50:30+00:00\", new Cesium.Quaternion(-0.04602497026095098, 0.6295671686576558, 0.15649584104471007, 0.7596288133006608));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:51:00+00:00\", new Cesium.Quaternion(-0.04275109486230805, 0.616933487599568, 0.156397402612387, 0.7701332795188158));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:51:30+00:00\", new Cesium.Quaternion(-0.039493273626741154, 0.6041238243763544, 0.15623347159172207, 0.7804266708112492));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:52:00+00:00\", new Cesium.Quaternion(-0.03625277738131119, 0.5911417215205433, 0.15600455545907296, 0.7905060277353277));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:52:30+00:00\", new Cesium.Quaternion(-0.03303086535173355, 0.5779907714554255, 0.15571118698371175, 0.800368450336844));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:53:00+00:00\", new Cesium.Quaternion(-0.02982878378629411, 0.5646746155514932, 0.1553539228364606, 0.8100110992257618));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:53:30+00:00\", new Cesium.Quaternion(-0.02664776550911077, 0.5511969431009803, 0.15493334330434222, 0.8194311964051926));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:54:00+00:00\", new Cesium.Quaternion(-0.023489029479239754, 0.5375614902783228, 0.15445005199685857, 0.828626026082961));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:54:30+00:00\", new Cesium.Quaternion(-0.020353780355933326, 0.5237720390868303, 0.15390467554423867, 0.8375929354654736));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:55:00+00:00\", new Cesium.Quaternion(-0.017243208070122917, 0.5098324162918704, 0.15329786328767664, 0.8463293355336778));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:55:30+00:00\", new Cesium.Quaternion(-0.014158487402205433, 0.4957464923408763, 0.15263028696157055, 0.8548327018009008));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:56:00+00:00\", new Cesium.Quaternion(-0.011100777566423276, 0.4815181802704841, 0.15190264036811918, 0.8631005750523032));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:56:30+00:00\", new Cesium.Quaternion(-0.008071221801865897, 0.4671514346011112, 0.1511156390442269, 0.8711305620657583));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:57:00+00:00\", new Cesium.Quaternion(-0.005070946970274409, 0.45265025021929967, 0.15027001992091765, 0.878920336313933));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:57:30+00:00\", new Cesium.Quaternion(-0.0021010631607767394, 0.4380186612481371, 0.1493665409753721, 0.8864676386473658));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:58:00+00:00\", new Cesium.Quaternion(0.0008373366982878661, 0.42326073990608687, 0.14840598087578247, 0.8937702779583258));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:58:30+00:00\", new Cesium.Quaternion(0.0037431772203752045, 0.40838059535455135, 0.14738913861905617, 0.9008261318252773));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:59:00+00:00\", new Cesium.Quaternion(0.006615400934413818, 0.39338237253449926, 0.14631683316157013, 0.907633147137749));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T00:59:30+00:00\", new Cesium.Quaternion(0.009452968650999483, 0.3782702509924954, 0.14518990304318427, 0.9141893407014046));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:00:00+00:00\", new Cesium.Quaternion(0.012254859821044128, 0.3630484436964664, 0.1440092060045305, 0.9204927998231627));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:00:30+00:00\", new Cesium.Quaternion(0.01502007288670032, 0.34772119584154426, 0.14277561859785984, 0.9265416828761691));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:01:00+00:00\", new Cesium.Quaternion(0.017747625624494723, 0.3322927836463344, 0.14149003579147668, 0.9323342198444666));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:01:30+00:00\", new Cesium.Quaternion(0.02043655548056017, 0.31676751313994905, 0.1401533705678863, 0.9378687128472104));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:02:00+00:00\", new Cesium.Quaternion(0.0230859203394968, 0.3011497189062998, 0.13876655213263275, 0.9431435368457741));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:02:30+00:00\", new Cesium.Quaternion(0.02569479705333598, 0.285443762985348, 0.1373305310271914, 0.9481571393102213));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:03:00+00:00\", new Cesium.Quaternion(0.028262284471860966, 0.26965403344291283, 0.13584627043089068, 0.952908041908776));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:03:30+00:00\", new Cesium.Quaternion(0.03078750190908515, 0.25378494324815515, 0.13431475124715148, 0.9573948401282226));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:04:00+00:00\", new Cesium.Quaternion(0.03326958990187326, 0.23784092898977577, 0.13273697029726783, 0.961616203899115));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:04:30+00:00\", new Cesium.Quaternion(0.03570771049533475, 0.22182644961508857, 0.13111393988472755, 0.9655708779940759));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:05:00+00:00\", new Cesium.Quaternion(0.03810104751957534, 0.20574598516236353, 0.12944668735443426, 0.9692576824046548));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:05:30+00:00\", new Cesium.Quaternion(0.04044880685769847, 0.1896040354868055, 0.12773625464708588, 0.9726755126966248));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:06:00+00:00\", new Cesium.Quaternion(0.0427502167050144, 0.1734051189805279, 0.12598369784866423, 0.97582334034363));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:06:30+00:00\", new Cesium.Quaternion(0.04500452781931572, 0.15715377128689983, 0.12419008673547902, 0.9787002130390592));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:07:00+00:00\", new Cesium.Quaternion(0.047211013762171045, 0.14085454400964095, 0.1223565043148014, 0.981305254986055));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:07:30+00:00\", new Cesium.Quaternion(0.049368971131177025, 0.12451200341701958, 0.1204840463611352, 0.9836376671655968));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:08:00+00:00\", new Cesium.Quaternion(0.05147771978304065, 0.1081307291415524, 0.11857382094863599, 0.9856967275825237));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:08:30+00:00\", new Cesium.Quaternion(0.053536603047486475, 0.09171531287555917, 0.11662694797943221, 0.9874817914894823));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:09:00+00:00\", new Cesium.Quaternion(0.05554498793186094, 0.07527035706296949, 0.11464455870846563, 0.9889922915886675));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:09:30+00:00\", new Cesium.Quaternion(0.05750226531642033, 0.05880047358774371, 0.11262779526461351, 0.9902277382113518));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:10:00+00:00\", new Cesium.Quaternion(0.05940785014020989, 0.042310282459294406, 0.11057781016853577, 0.9911877194751075));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:10:30+00:00\", new Cesium.Quaternion(0.06126118157748072, 0.025804410495298493, 0.10849576584750262, 0.9918719014186685));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:11:00+00:00\", new Cesium.Quaternion(0.0630617232046135, 0.009287490002255046, 0.10638283414695822, 0.9922800281144348));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:11:30+00:00\", new Cesium.Quaternion(0.0648089631574687, -0.007235842545796234, 0.10424019583956515, 0.9924119217585183));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:12:00+00:00\", new Cesium.Quaternion(0.06650241427913803, -0.02376094783004655, 0.10206904013139696, 0.9922674827383587));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:12:30+00:00\", new Cesium.Quaternion(0.06814161425804281, -0.040283185010762626, 0.09987056416590963, 0.9918466896778352));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:13:00+00:00\", new Cesium.Quaternion(0.06972612575634768, -0.05679791305184917, 0.09764597252555278, 0.9911495994598917));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:13:30+00:00\", new Cesium.Quaternion(0.0712555364211099, -0.07330049215026788, 0.09539647527867796, 0.9901763473666058));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:14:00+00:00\", new Cesium.Quaternion(0.07272945939914033, -0.0897862846449053, 0.09312329328934651, 0.9889271464936733));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:14:30+00:00\", new Cesium.Quaternion(0.07414753286355577, -0.10625065696154741, 0.09082764899298519, 0.9874022885551231));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:15:00+00:00\", new Cesium.Quaternion(0.07550942046061247, -0.12268898052496918, 0.08851077170573554, 0.9856021432461993));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:15:30+00:00\", new Cesium.Quaternion(0.07681481130586766, -0.13909663318356313, 0.08617389566359789, 0.9835271582967094));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:16:00+00:00\", new Cesium.Quaternion(0.07806342005382624, -0.15546900053007473, 0.08381825951459049, 0.9811778593586509));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:16:30+00:00\", new Cesium.Quaternion(0.07925498695770822, -0.17180147722036612, 0.08144510580985849, 0.9785548498714085));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:17:00+00:00\", new Cesium.Quaternion(0.08038927791930743, -0.188089468289834, 0.07905568049389512, 0.9756588109045636));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:17:30+00:00\", new Cesium.Quaternion(0.08146608452903259, -0.20432839046704532, 0.07665123239461881, 0.9724905009783085));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:18:00+00:00\", new Cesium.Quaternion(0.08248522409597214, -0.22051367348429382, 0.07423301271259047, 0.9690507558615864));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:18:30+00:00\", new Cesium.Quaternion(0.08344653966812532, -0.2366407613846207, 0.07180227451039235, 0.9653404883479494));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:19:00+00:00\", new Cesium.Quaternion(0.08434990004271097, -0.25270511382496613, 0.06936027220184496, 0.9613606880092308));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:19:30+00:00\", new Cesium.Quaternion(0.08519519976658638, -0.26870220737506034, 0.06690826104141494, 0.9571124209270903));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:20:00+00:00\", new Cesium.Quaternion(0.08598235912683394, -0.28462753681165975, 0.06444749661416961, 0.9525968294024908));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:20:30+00:00\", new Cesium.Quaternion(0.08671132413138982, -0.3004766164077983, 0.06197923432595544, 0.9478151316432283));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:21:00+00:00\", new Cesium.Quaternion(0.0873820664799615, -0.31624498121660966, 0.05950472889480622, 0.9427686214295392));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:21:30+00:00\", new Cesium.Quaternion(0.08799458352500308, -0.3319281883494207, 0.05702523384288811, 0.9374586677579427));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:22:00+00:00\", new Cesium.Quaternion(0.08854889822292199, -0.34752181824770256, 0.05454200098970657, 0.9318867144633816));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:22:30+00:00\", new Cesium.Quaternion(0.08904505907555044, -0.3630214759485087, 0.052056279946736325, 0.9260542798197658));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:23:00+00:00\", new Cesium.Quaternion(0.08948314006179996, -0.37842279234305837, 0.04956931761334872, 0.9199629561190549));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:23:30+00:00\", new Cesium.Quaternion(0.08986324055969416, -0.3937214254280653, 0.0470823576746608, 0.9136144092289692));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:24:00+00:00\", new Cesium.Quaternion(0.09018548525859178, -0.4089130615494978, 0.04459664010091262, 0.9070103781294891));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:24:30+00:00\", new Cesium.Quaternion(0.09045002344000222, -0.42399341677101443, 0.04211339932890341, 0.9001526744900047));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:25:00+00:00\", new Cesium.Quaternion(0.09065703133651543, -0.4389582375710164, 0.039633869057941265, 0.893043181913));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:25:30+00:00\", new Cesium.Quaternion(0.09080670834959363, -0.4538033028565207, 0.03715927380250387, 0.8856838557892401));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:26:00+00:00\", new Cesium.Quaternion(0.09089927934532371, -0.46852442464325755, 0.034690833713553956, 0.8780767224926669));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:26:30+00:00\", new Cesium.Quaternion(0.09093499391914894, -0.4831174493883397, 0.03222976275958234, 0.8702238788782405));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:27:00+00:00\", new Cesium.Quaternion(0.09091412625117443, -0.4975782591808855, 0.02977726824132819, 0.8621274916940007));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:27:30+00:00\", new Cesium.Quaternion(0.09083697495202483, -0.5119027729225883, 0.02733455030938102, 0.8537897969729519));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:28:00+00:00\", new Cesium.Quaternion(0.0907038628995846, -0.5260869474978407, 0.024902801485330785, 0.8452130994049253));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:28:30+00:00\", new Cesium.Quaternion(0.09051513706649139, -0.5401267789331045, 0.022483206186279633, 0.836399771688616));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:29:00+00:00\", new Cesium.Quaternion(0.09027116833847515, -0.5540183035451924, 0.02007694025294285, 0.8273522538639717));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:29:30+00:00\", new Cesium.Quaternion(0.08997235132376769, -0.5677575990780953, 0.01768517048174883, 0.8180730526251192));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:30:00+00:00\", new Cesium.Quaternion(0.08961910415342511, -0.581340785828066, 0.015309054160736022, 0.808564740614039));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:30:30+00:00\", new Cesium.Quaternion(0.08921186827290126, -0.5947640277565917, 0.012949738609810671, 0.7988299556951732));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:31:00+00:00\", new Cesium.Quaternion(0.08875110822470905, -0.6080235335909671, 0.010608360725165389, 0.7888714002111912));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:31:30+00:00\", new Cesium.Quaternion(0.08823731142241417, -0.6211155579121246, 0.008286046528260217, 0.7786918402201131));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:32:00+00:00\", new Cesium.Quaternion(0.08767098791609612, -0.6340364022294016, 0.005983910719572964, 0.7682941047140168));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:32:30+00:00\", new Cesium.Quaternion(0.08705267014911072, -0.646782416041965, 0.0037030562369469665, 0.7576810848195531));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:33:00+00:00\", new Cesium.Quaternion(0.08638291270658732, -0.6593499978865389, 0.0014445738191367508, 0.7468557329804926));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:33:30+00:00\", new Cesium.Quaternion(0.08566229205550102, -0.6717355963711642, -0.0007904584256280043, 0.7358210621225464));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:34:00+00:00\", new Cesium.Quaternion(0.0848914062765202, -0.6839357111946778, -0.0030009754457678314, 0.7245801448006971));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:34:30+00:00\", new Cesium.Quaternion(0.08407087478778075, -0.6959468941516083, -0.0051859256669716, 0.7131361123292834));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:35:00+00:00\", new Cesium.Quaternion(0.08320133806059085, -0.7077657501222069, -0.007344271407266435, 0.7014921538950908));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:35:30+00:00\", new Cesium.Quaternion(0.08228345732729633, -0.7193889380473115, -0.009474989286266156, 0.6896515156537057));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:36:00+00:00\", new Cesium.Quaternion(0.08131791320920728, -0.7308131720070699, -0.011577071622627203, 0.6776174997924045));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:36:30+00:00\", new Cesium.Quaternion(0.08030540968068575, -0.7420352216860097, -0.013649522837392335, 0.6653934636587011));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:37:00+00:00\", new Cesium.Quaternion(0.0792466673714105, -0.7530519140208487, -0.015691365862673556, 0.652982818715336));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:37:30+00:00\", new Cesium.Quaternion(0.07814242748185779, -0.7638601336304794, -0.017701638497243474, 0.6403890296310375));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:38:00+00:00\", new Cesium.Quaternion(0.07699345039810684, -0.7744568238315762, -0.019679394796492382, 0.6276156132832779));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:38:30+00:00\", new Cesium.Quaternion(0.07580051535468152, -0.7848389875167134, -0.021623705444168393, 0.6146661377598158));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:39:00+00:00\", new Cesium.Quaternion(0.07456442009039155, -0.7950036880154254, -0.023533658117326342, 0.6015442213454242));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:39:30+00:00\", new Cesium.Quaternion(0.07328598049720197, -0.8049480499379753, -0.025408357844438716, 0.588253531494086));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:40:00+00:00\", new Cesium.Quaternion(0.07196603026224702, -0.8146692600015807, -0.02724692735654459, 0.5747977837869572));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:40:30+00:00\", new Cesium.Quaternion(0.07060542050341528, -0.8241645678388326, -0.029048507431098828, 0.5611807408764053));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:41:00+00:00\", new Cesium.Quaternion(0.06920501939814883, -0.8334312867881165, -0.030812257228763816, 0.5474062114164169));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:41:30+00:00\", new Cesium.Quaternion(0.06776571180603636, -0.8424667946657642, -0.03253735462269699, 0.5334780489796848));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:42:00+00:00\", new Cesium.Quaternion(0.06628839888516996, -0.8512685345197307, -0.03422299652034956, 0.5194001509617022));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:42:30+00:00\", new Cesium.Quaternion(0.0647739977022942, -0.8598340153645789, -0.03586839917772822, 0.5051764574721544));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:43:00+00:00\", new Cesium.Quaternion(0.06322344083720105, -0.8681608128975437, -0.037472798505814996, 0.4908109502139536));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:43:30+00:00\", new Cesium.Quaternion(0.06163767598115466, -0.8762465701954836, -0.039035450369258984, 0.4763076513502205));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:44:00+00:00\", new Cesium.Quaternion(0.06001766552981336, -0.8840889983925018, -0.04055563087704402, 0.4616706223595559));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:44:30+00:00\", new Cesium.Quaternion(0.05836438617060985, -0.891685877338048, -0.04203263666513984, 0.4469039628799233));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:45:00+00:00\", new Cesium.Quaternion(0.05667882846480682, -0.8990350562353079, -0.04346578517099982, 0.43201180954147844));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:45:30+00:00\", new Cesium.Quaternion(0.05496199642444349, -0.906134454259687, -0.0448544148997776, 0.41699833478868686));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:46:00+00:00\", new Cesium.Quaternion(0.05321490708415194, -0.9129820611572246, -0.04619788568225579, 0.4018677456920627));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:46:30+00:00\", new Cesium.Quaternion(0.05143859006824625, -0.9195759378227439, -0.04749557892427603, 0.3866242827498809));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:47:00+00:00\", new Cesium.Quaternion(0.04963408579480316, -0.9259142169303918, -0.048746898392301216, 0.37127221860869725));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:47:30+00:00\", new Cesium.Quaternion(0.04780245045763509, -0.9319951031768565, -0.04995126824450847, 0.3558158571303019));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:48:00+00:00\", new Cesium.Quaternion(0.04594474745734245, -0.9378168742426495, -0.0511081365900747, 0.3402595317417542));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:48:30+00:00\", new Cesium.Quaternion(0.04406205235607635, -0.9433778809883953, -0.0522169734577649, 0.3246076044810517));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:49:00+00:00\", new Cesium.Quaternion(0.042155451073987105, -0.9486765480047497, -0.05327727156900577, 0.3088644646842744));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:49:30+00:00\", new Cesium.Quaternion(0.04022603943050618, -0.9537113740657015, -0.05428854653497437, 0.2930345277344754));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:50:00+00:00\", new Cesium.Quaternion(0.038274922682208945, -0.9584809325605517, -0.055250337044593624, 0.27712223380303713));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:50:30+00:00\", new Cesium.Quaternion(0.03630321505702949, -0.9629838719044639, -0.056162205043508016, 0.26113204658383316));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:51:00+00:00\", new Cesium.Quaternion(0.03431203928514237, -0.9672189159274625, -0.05702373590392335, 0.24506845202057148));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:51:30+00:00\", new Cesium.Quaternion(0.03230252612686124, -0.971184864241753, -0.05783453858520557, 0.2289359570276972));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:52:00+00:00\", new Cesium.Quaternion(0.030275813897216952, -0.9748805925872839, -0.05859424578531517, 0.21273908820519427));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:52:30+00:00\", new Cesium.Quaternion(0.028233047988231952, -0.9783050531554099, -0.059302514082811876, 0.1964823905477101));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:53:00+00:00\", new Cesium.Quaternion(0.02617538038808276, -0.981457274890605, -0.05995902406962024, 0.18017042614831488));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:53:30+00:00\", new Cesium.Quaternion(0.024103969198164488, -0.9843363637701046, -0.06056348047430952, 0.16380777289732176));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:54:00+00:00\", new Cesium.Quaternion(0.022019978147730823, -0.9869415030614106, -0.061115612275961455, 0.14739902317651715));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:54:30+00:00\", new Cesium.Quaternion(0.01992457610647247, -0.9892719535575839, -0.06161517280853957, 0.1309487825491826));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:55:00+00:00\", new Cesium.Quaternion(0.017818936595281054, -0.9913270537902449, -0.062061939855719735, 0.1144616684463036));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:55:30+00:00\", new Cesium.Quaternion(0.015704237295158463, -0.9931062202202361, -0.06245571573617727, 0.09794230884931843));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:56:00+00:00\", new Cesium.Quaternion(0.013581659554823211, -0.9946089474058744, -0.06279632737925461, 0.08139534096982148));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:56:30+00:00\", new Cesium.Quaternion(0.011452387896688787, -0.995834808148757, -0.06308362639104226, 0.06482540992656723));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:57:00+00:00\", new Cesium.Quaternion(0.009317609521874881, -0.9967834536170728, -0.06331748911079332, 0.048237167420188035));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:57:30+00:00\", new Cesium.Quaternion(0.007178513814229792, -0.9974546134463793, -0.06349781665768055, 0.03163527040599664));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:58:00+00:00\", new Cesium.Quaternion(0.00503629184341603, -0.9978480958178245, -0.06362453496788081, 0.01502437976525345));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:58:30+00:00\", new Cesium.Quaternion(0.0028921344036878516, -0.9979637875180257, -0.06369759481962294, -0.0015908411181392093));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:59:00+00:00\", new Cesium.Quaternion(0.0007472373718296899, -0.9978016539519913, -0.0637169718358387, -0.018205727314558377));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T01:59:30+00:00\", new Cesium.Quaternion(-0.0013972075746157553, -0.9973617391884442, -0.06368266655125782, -0.03481561424011809));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:00:00+00:00\", new Cesium.Quaternion(-0.0035400075999667546, -0.9966441659212312, -0.063594704346886, -0.05141583861416663));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:00:30+00:00\", new Cesium.Quaternion(-0.005679970672185508, -0.9956491354419176, -0.06345313546059606, -0.06800173988321634));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:01:00+00:00\", new Cesium.Quaternion(-0.007815906060453293, -0.9943769275823984, -0.06325803496598277, -0.0845686615507566));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:01:30+00:00\", new Cesium.Quaternion(-0.009946624832426754, -0.9928279006349252, -0.0630095027415113, -0.1011119525059121));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:02:00+00:00\", new Cesium.Quaternion(-0.012070940350727033, -0.9910024912495746, -0.06270766342997951, -0.11762696835053943));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:02:30+00:00\", new Cesium.Quaternion(-0.014187668768417705, -0.9889012143091895, -0.06235266638832577, -0.1341090727243843));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:03:00+00:00\", new Cesium.Quaternion(0.016295629523699562, 0.9865246627818256, 0.06194468562775548, 0.15055363862793353));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:03:30+00:00\", new Cesium.Quaternion(0.01839364583307851, 0.9838735075507481, 0.06148391974426657, 0.16695604974254674));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:04:00+00:00\", new Cesium.Quaternion(0.020480545183344023, 0.9809484972220298, 0.06097059183953881, 0.18331170174751701));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:04:30+00:00\", new Cesium.Quaternion(0.022555159821708415, 0.9777504579098036, 0.0604049494322808, 0.1996160036336521));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:05:00+00:00\", new Cesium.Quaternion(0.024616327244364355, 0.9742802929992322, 0.05978726435999594, 0.21586437901301928));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:05:30+00:00\", new Cesium.Quaternion(0.026662890682906504, 0.9705389828872677, 0.059117832671267564, 0.23205226742445675));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:06:00+00:00\", new Cesium.Quaternion(0.02869369958867879, 0.96652758470127, 0.05839697450855715, 0.24817512563448216));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:06:30+00:00\", new Cesium.Quaternion(0.030707610114696693, 0.962247231995575, 0.05762503398159714, 0.26422842893322085));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:07:00+00:00\", new Cesium.Quaternion(0.032703485595193205, 0.9576991344260887, 0.0568023790313649, 0.2802076724249768));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:07:30+00:00\", new Cesium.Quaternion(0.03468019702231895, 0.9528845774030155, 0.05592940128476179, 0.29610837231307385));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:08:00+00:00\", new Cesium.Quaternion(0.036636623520054534, 0.9478049217218112, 0.055006515899989214, 0.3119260671785954));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:08:30+00:00\", new Cesium.Quaternion(0.038571652814969826, 0.9424616031724755, 0.05403416140273266, 0.32765631925264715));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:09:00+00:00\", new Cesium.Quaternion(0.040484181703968225, 0.9368561321272871, 0.05301279951311011, 0.3432947156817915));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:09:30+00:00\", new Cesium.Quaternion(0.04237311788397746, 0.9309900930449654, 0.05194291443724751, 0.35883686986245167));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:10:00+00:00\", new Cesium.Quaternion(0.04423737494100044, 0.924865144261564, 0.05082501475896752, 0.37427842238514974));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:10:30+00:00\", new Cesium.Quaternion(0.046075881027551224, 0.9184830171496102, 0.04965963014952865, 0.38961504273923475));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:11:00+00:00\", new Cesium.Quaternion(0.047887573826701835, 0.9118455158612584, 0.04844731319589113, 0.4048424302377493));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:11:30+00:00\", new Cesium.Quaternion(0.049671402375256024, 0.9049545167508176, 0.047188638679298026, 0.4199563153209683));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:12:00+00:00\", new Cesium.Quaternion(0.05142632750823295, 0.8978119678359348, 0.04588420334876526, 0.43495246077316485));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:12:30+00:00\", new Cesium.Quaternion(0.05315132229918079, 0.8904198882381898, 0.04453462568579653, 0.4498266629300273));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:13:00+00:00\", new Cesium.Quaternion(0.054845372495576195, 0.8827803676032846, 0.04314054566067797, 0.46457475287635924));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:13:30+00:00\", new Cesium.Quaternion(0.05650747694972508, 0.874895565500976, 0.041702624480167635, 0.4791925976337385));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:14:00+00:00\", new Cesium.Quaternion(0.05813664804466834, 0.8667677108049356, 0.040221544326826945, 0.4936761013377769));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:14:30+00:00\", new Cesium.Quaternion(0.059731912114958985, 0.8583991010527234, 0.03869800809008143, 0.5080212064046417));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:15:00+00:00\", new Cesium.Quaternion(0.06129230986225287, 0.8497921017860497, 0.03713273908905564, 0.5222238946865051));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:15:30+00:00\", new Cesium.Quaternion(0.06281689676549479, 0.8409491458715269, 0.035526480787313866, 0.5362801886155888));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:16:00+00:00\", new Cesium.Quaternion(0.06430474348556647, 0.8318727328021022, 0.033879996499597144, 0.5501861523364664));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:16:30+00:00\", new Cesium.Quaternion(0.06575493626418033, 0.8225654279793831, 0.03219406909070688, 0.5639378928263032));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:17:00+00:00\", new Cesium.Quaternion(0.06716657731703524, 0.8130298619770511, 0.030469500666531778, 0.5775315610027076));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:17:30+00:00\", new Cesium.Quaternion(0.06853878522086865, 0.8032687297855925, 0.02870711225747223, 0.5909633528188747));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:18:00+00:00\", new Cesium.Quaternion(0.06987069529436257, 0.7932847900385637, 0.026907743494315673, 0.604229510345695));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:18:30+00:00\", new Cesium.Quaternion(0.0711614599728776, 0.7830808642206011, 0.02507225227658651, 0.6173263228405413));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:19:00+00:00\", new Cesium.Quaternion(0.07241024917656796, 0.7726598358574335, 0.023201514433718384, 0.6302501278023938));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:19:30+00:00\", new Cesium.Quaternion(0.07361625067215144, 0.7620246496880985, 0.021296423378857506, 0.6429973120130242));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:20:00+00:00\", new Cesium.Quaternion(0.07477867042774633, 0.7511783108196426, 0.019357889755770845, 0.655564312563924));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:20:30+00:00\", new Cesium.Quaternion(0.07589673296097427, 0.7401238838645223, 0.01738684107873181, 0.6679476178686835));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:21:00+00:00\", new Cesium.Quaternion(0.076969682749334, 0.7288644919480506, 0.015384220367817867, 0.6801437686831011));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:21:30+00:00\", new Cesium.Quaternion(0.07799678027053741, 0.7174033162621128, 0.013350989748673419, 0.6921493589943457));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:22:00+00:00\", new Cesium.Quaternion(0.07897730879466908, 0.7057435944793555, 0.011288124139072295, 0.7039610371322629));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:22:30+00:00\", new Cesium.Quaternion(0.07991057037688123, 0.6938886202709771, 0.009196614799959835, 0.7155755066215603));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:23:00+00:00\", new Cesium.Quaternion(0.08079588725514178, 0.6818417422501943, 0.007077467962707396, 0.7269895271426616));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:23:30+00:00\", new Cesium.Quaternion(0.08163260215446791, 0.6696063630113668, 0.0049317044302753755, 0.7381999154508163));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:24:00+00:00\", new Cesium.Quaternion(0.08242007858353953, 0.6571859381536675, 0.0027603591723062344, 0.749203546278718));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:24:30+00:00\", new Cesium.Quaternion(0.08315770112351659, 0.6445839752896104, 0.0005644809143420833, 0.7599973532223597));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:25:00+00:00\", new Cesium.Quaternion(0.08384487570882865, 0.6318040330387263, -0.0016548682785514708, 0.7705783296098794));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:25:30+00:00\", new Cesium.Quaternion(0.08448102989991588, 0.6188497200066752, -0.0038966134236895645, 0.7809435293531383));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:26:00+00:00\", new Cesium.Quaternion(0.0850656131478855, 0.6057246937500799, -0.006159667048141186, 0.7910900677817935));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:26:30+00:00\", new Cesium.Quaternion(0.08559809705081364, 0.5924326597274064, -0.00844292962121703, 0.8010151224596211));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:27:00+00:00\", new Cesium.Quaternion(0.08607797560172803, 0.5789773702361753, -0.010745289992069314, 0.8107159339828578));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:27:30+00:00\", new Cesium.Quaternion(0.08650476542812482, 0.5653626233368233, -0.013065625832196672, 0.8201898067603275));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:28:00+00:00\", new Cesium.Quaternion(0.08687800602289028, 0.551592261763529, -0.01540280408263308, 0.8294341097751365));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:28:30+00:00\", new Cesium.Quaternion(0.0871972599666607, 0.5376701718223094, -0.017755681405840214, 0.8384462773277067));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:29:00+00:00\", new Cesium.Quaternion(0.08746211314132718, 0.5236002822767265, -0.020123104641841368, 0.8472238097599475));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:29:30+00:00\", new Cesium.Quaternion(0.08767217493482865, 0.509386563221505, -0.022503911268764776, 0.8557642741603487));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:30:00+00:00\", new Cesium.Quaternion(0.08782707843699156, 0.4950330249444044, -0.024896929867399515, 0.8640653050497937));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:30:30+00:00\", new Cesium.Quaternion(0.08792648062636008, 0.4805437167766799, -0.027300980589609915, 0.8721246050479039));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:31:00+00:00\", new Cesium.Quaternion(0.08797006254800557, 0.4659227259324513, -0.02971487563055066, 0.8799399455197126));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:31:30+00:00\", new Cesium.Quaternion(0.08795752948220345, 0.4511741763373269, -0.03213741970444886, 0.8875091672024927));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:32:00+00:00\", new Cesium.Quaternion(0.08788861174394527, 0.4363022273176918, -0.0345674118364574, 0.8948301807618427));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:32:30+00:00\", new Cesium.Quaternion(0.08776306225101049, 0.42131107292475817, -0.03700364060471043, 0.901900967577545));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:33:00+00:00\", new Cesium.Quaternion(0.08758066057082856, 0.40620493995897783, -0.03944489247025209, 0.9087195800162506));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:33:30+00:00\", new Cesium.Quaternion(0.08734121042624299, 0.39098808727519774, -0.041889947046581284, 0.9152841421693024));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:34:00+00:00\", new Cesium.Quaternion(0.0870445404793425, 0.3756648044337088, -0.044337578892422555, 0.9215928503306012));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:34:30+00:00\", new Cesium.Quaternion(0.08669050444406848, 0.3602394104716268, -0.04678655800534633, 0.9276439735007718));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:35:00+00:00\", new Cesium.Quaternion(0.08627898118916556, 0.344716252666, -0.04923565031745996, 0.9334358538703593));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:35:30+00:00\", new Cesium.Quaternion(0.08580987483162503, 0.32909970528895305, -0.05168361819344719, 0.9389669072819018));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:36:00+00:00\", new Cesium.Quaternion(0.08528311482043585, 0.3133941683552601, -0.05412922093042658, 0.9442356236707575));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:36:30+00:00\", new Cesium.Quaternion(0.08469865601068834, 0.2976040663626972, -0.05657121525965214, 0.9492405674845639));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:37:00+00:00\", new Cesium.Quaternion(0.0840564787279637, 0.2817338470255407, -0.05900835584979824, 0.9539803780811995));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:37:30+00:00\", new Cesium.Quaternion(0.0833565888229853, 0.26578798000158205, -0.06143939581166291, 0.9584537701051482));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:38:00+00:00\", new Cesium.Quaternion(0.08259901771648073, 0.24977095561303292, -0.06386308720403047, 0.962659533842155));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:38:30+00:00\", new Cesium.Quaternion(0.08178382243428654, 0.23368728356167648, -0.0662781815407054, 0.9665965355520675));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:39:00+00:00\", new Cesium.Quaternion(0.08091108563260087, 0.2175414916386555, -0.06868343029827736, 0.9702637177797822));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:39:30+00:00\", new Cesium.Quaternion(0.07998091561340684, 0.2013381244292713, -0.07107758542456348, 0.9736600996442026));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:40:00+00:00\", new Cesium.Quaternion(0.07899344633005712, 0.18508174201315147, -0.07345939984756794, 0.9767847771051272));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:40:30+00:00\", new Cesium.Quaternion(0.07794883738300885, 0.1687769186601733, -0.07582762798481656, 0.9796369232079868));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:41:00+00:00\", new Cesium.Quaternion(0.07684727400563893, 0.15242824152254467, -0.07818102625251529, 0.9822157883063939));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:41:30+00:00\", new Cesium.Quaternion(0.07568896704024763, 0.13604030932337358, -0.08051835357495445, 0.9845207002623967));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:42:00+00:00\", new Cesium.Quaternion(0.07447415290415077, 0.11961773104215098, -0.0828383718934346, 0.9865510646244229));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:42:30+00:00\", new Cesium.Quaternion(0.07320309354590564, 0.10316512459750946, -0.08513984667474038, 0.9883063647828499));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:43:00+00:00\", new Cesium.Quaternion(0.07187607639169061, 0.08668711552763118, -0.08742154741910563, 0.9897861621031507));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:43:30+00:00\", new Cesium.Quaternion(0.07049341438476456, 0.07018833556530739, -0.08968224962082855, 0.9909900959050486));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:44:00+00:00\", new Cesium.Quaternion(0.06905544547608485, 0.05367342173054926, -0.09192072946095504, 0.9919178840736769));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:44:30+00:00\", new Cesium.Quaternion(0.06756253323156552, 0.037147014379598026, -0.09413577302965961, 0.9925693223458621));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:45:00+00:00\", new Cesium.Quaternion(0.06601506625465295, 0.02061375629960043, -0.09632617101983185, 0.992944284869636));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:45:30+00:00\", new Cesium.Quaternion(0.0644134582107496, 0.004078291277636502, -0.09849072068075541, 0.9930427240966887));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:46:00+00:00\", new Cesium.Quaternion(0.06275814771472926, -0.012454737224857616, -0.1006282263181498, 0.9928646707805345));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:46:30+00:00\", new Cesium.Quaternion(0.061049598208730474, -0.02898068739732253, -0.10273749979225384, 0.9924102339521534));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:47:00+00:00\", new Cesium.Quaternion(0.0592882978302664, -0.045494920404574694, -0.10481736101369112, 0.9916796008731331));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:47:30+00:00\", new Cesium.Quaternion(0.057474759270683046, -0.061992801710202064, -0.10686663843714815, 0.9906730369663044));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:48:00+00:00\", new Cesium.Quaternion(0.055609519624015155, -0.0784697023984552, -0.10888416955239473, 0.9893908857239233));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:48:30+00:00\", new Cesium.Quaternion(0.053693140226277705, -0.09492100049426398, -0.11086880137269522, 0.98783356859341));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:49:00+00:00\", new Cesium.Quaternion(0.05172620648525081, -0.11134208228099021, -0.1128193909202645, 0.9860015848406933));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:49:30+00:00\", new Cesium.Quaternion(0.049709327700800165, -0.1277283436155446, -0.11473480570872249, 0.9838955113911976));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:50:00+00:00\", new Cesium.Quaternion(0.04764313687577963, -0.1440751912404774, -0.11661392422238558, 0.9815160026485108));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:50:30+00:00\", new Cesium.Quaternion(0.04552829051762225, -0.1603780440926605, -0.1184556363918583, 0.978863790290843));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:51:00+00:00\", new Cesium.Quaternion(0.04336546843060535, -0.17663233460820224, -0.12025884406635999, 0.9759396830452554));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:51:30+00:00\", new Cesium.Quaternion(0.041155373498922426, -0.19283351002319427, -0.12202246148206125, 0.9727445664398017));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:52:00+00:00\", new Cesium.Quaternion(0.03889873146060803, -0.20897703366992507, -0.12374541572647958, 0.9692794025336323));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:52:30+00:00\", new Cesium.Quaternion(0.0365962906723565, -0.2250583862681911, -0.12542664719888463, 0.9655452296251218));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:53:00+00:00\", new Cesium.Quaternion(0.03424882186538089, -0.24107306721131758, -0.1270651100661905, 0.9615431619381567));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:53:30+00:00\", new Cesium.Quaternion(0.031857117892300287, -0.2570165958465333, -0.12865977271459406, 0.9572743892866271));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:54:00+00:00\", new Cesium.Quaternion(0.02942199346524102, -0.2728845127493156, -0.1302096181963307, 0.9527401767172758));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:54:30+00:00\", new Cesium.Quaternion(0.026944284461648815, -0.2886723810308747, -0.1317136460624514, 0.9479418639377366));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:55:00+00:00\", new Cesium.Quaternion(0.02442484931578709, -0.3043757874375613, -0.13317086723008323, 0.9428808656870991));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:55:30+00:00\", new Cesium.Quaternion(0.021864566259250484, -0.31999034385311265, -0.1345803127796993, 0.9375586701615959));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:56:00+00:00\", new Cesium.Quaternion(0.019264334649042106, -0.3355116883761894, -0.13594102879796816, 0.9319768393382094));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:56:30+00:00\", new Cesium.Quaternion(0.016625074262489173, -0.350935486602285, -0.13725207819645066, 0.926137008319903));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:57:00+00:00\", new Cesium.Quaternion(0.013947724984157459, -0.3662574328542791, -0.13851254112711872, 0.9200408848509224));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:57:30+00:00\", new Cesium.Quaternion(0.01123324648459019, -0.3814732514044341, -0.13972151539206243, 0.9136902488113201));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:58:00+00:00\", new Cesium.Quaternion(0.00848261789097228, -0.3965786976874882, -0.14087811684724086, 0.9070869516908435));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:58:30+00:00\", new Cesium.Quaternion(0.005696837449862588, -0.41156955950448676, -0.14198147980005707, 0.9002329160423644));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:59:00+00:00\", new Cesium.Quaternion(0.002876922182056832, -0.426441658217016, -0.14303075740071855, 0.8931301349149838));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T02:59:30+00:00\", new Cesium.Quaternion(2.390752968020604e-05, -0.44119084993148505, -0.14402512202726078, 0.8857806712669885));\n", - " widget.property_84f93f67.addSample(\"2023-01-01T03:00:00+00:00\", new Cesium.Quaternion(-0.002861153004257433, -0.4558130266731231, -0.14496376566383687, 0.8781866573588631));\n", + " widget.property_99affc87 = new Cesium.SampledProperty(Cesium.Cartesian3);\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:00:00+00:00\", Cesium.Cartesian3.fromDegrees(29.98055060896214, -0.08103079020036194, 500000.0424350213));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:00:30+00:00\", Cesium.Cartesian3.fromDegrees(29.61394459855244, 1.8152541965297813, 500021.2891134799));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:01:00+00:00\", Cesium.Cartesian3.fromDegrees(29.246837283092006, 3.711457477700564, 500088.9038070484));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:01:30+00:00\", Cesium.Cartesian3.fromDegrees(28.878700725097563, 5.607493659242157, 500202.5852361204));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:02:00+00:00\", Cesium.Cartesian3.fromDegrees(28.508998078325064, 7.503277246472494, 500361.82691467437));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:02:30+00:00\", Cesium.Cartesian3.fromDegrees(28.137178834920114, 9.39872257658667, 500565.9194959655));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:03:00+00:00\", Cesium.Cartesian3.fromDegrees(27.76267381978467, 11.29374373104158, 500813.95405548724));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:03:30+00:00\", Cesium.Cartesian3.fromDegrees(27.384889834542843, 13.188254420285343, 501104.82629379485));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:04:00+00:00\", Cesium.Cartesian3.fromDegrees(27.003203842160705, 15.082167832578493, 501437.2416369357));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:04:30+00:00\", Cesium.Cartesian3.fromDegrees(26.61695656805757, 16.975396437707136, 501809.7212076043));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:05:00+00:00\", Cesium.Cartesian3.fromDegrees(26.225445373867096, 18.867851735144278, 502220.6086357079));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:05:30+00:00\", Cesium.Cartesian3.fromDegrees(25.82791623448943, 20.75944393460629, 502668.0776729075));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:06:00+00:00\", Cesium.Cartesian3.fromDegrees(25.42355444852117, 22.650081554882785, 503150.14057144115));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:06:30+00:00\", Cesium.Cartesian3.fromDegrees(25.011474847567403, 24.53967092416804, 503664.65718443843));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:07:00+00:00\", Cesium.Cartesian3.fromDegrees(24.590708687169503, 26.42811556172291, 504209.34474088927));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:07:30+00:00\", Cesium.Cartesian3.fromDegrees(24.160190218573536, 28.315315416339914, 504781.78824600566));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:08:00+00:00\", Cesium.Cartesian3.fromDegrees(23.71873997101196, 30.20116593146087, 505379.45145462017));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:08:30+00:00\", Cesium.Cartesian3.fromDegrees(23.265045193937162, 32.08555689952976, 505999.68836319674));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:09:00+00:00\", Cesium.Cartesian3.fromDegrees(22.797636588863732, 33.96837105870364, 506639.75516373105));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:09:30+00:00\", Cesium.Cartesian3.fromDegrees(22.31486044260936, 35.84948237266498, 507296.82260151353));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:10:00+00:00\", Cesium.Cartesian3.fromDegrees(21.814845029896325, 37.72875391796016, 507967.98867721425));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:10:30+00:00\", Cesium.Cartesian3.fromDegrees(21.295459831252085, 39.60603528162094, 508650.29163284163));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:11:00+00:00\", Cesium.Cartesian3.fromDegrees(20.754265683819927, 41.481159342815566, 509340.7231607127));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:11:30+00:00\", Cesium.Cartesian3.fromDegrees(20.188453407339118, 43.35393827309509, 510036.2417740361));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:12:00+00:00\", Cesium.Cartesian3.fromDegrees(19.59476766873308, 45.22415853637336, 510733.7862780438));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:12:30+00:00\", Cesium.Cartesian3.fromDegrees(18.96941178348625, 47.09157459619166, 511430.2892808057));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:13:00+00:00\", Cesium.Cartesian3.fromDegrees(18.307927680695265, 48.95590093534189, 512122.6906835406));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:13:30+00:00\", Cesium.Cartesian3.fromDegrees(17.60504320496362, 50.81680184855506, 512807.9510913192));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:14:00+00:00\", Cesium.Cartesian3.fromDegrees(16.854476029141797, 52.673878263022765, 513483.0650859812));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:14:30+00:00\", Cesium.Cartesian3.fromDegrees(16.048679311763394, 54.526650543828474, 514145.0743047504));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:15:00+00:00\", Cesium.Cartesian3.fromDegrees(15.17850824810701, 56.374535804885824, 514791.0802694849));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:15:30+00:00\", Cesium.Cartesian3.fromDegrees(14.232777903949135, 58.21681759626829, 515418.25691348885));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:16:00+00:00\", Cesium.Cartesian3.fromDegrees(13.197669735589734, 60.052604856026605, 516023.8627545611));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:16:30+00:00\", Cesium.Cartesian3.fromDegrees(12.055924707421658, 61.880775502464516, 516605.25266542385));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:17:00+00:00\", Cesium.Cartesian3.fromDegrees(10.785731141158601, 63.69989767427881, 517159.8891946781));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:17:30+00:00\", Cesium.Cartesian3.fromDegrees(9.359171168837772, 65.50811784627128, 517685.3533939366));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:18:00+00:00\", Cesium.Cartesian3.fromDegrees(7.740015925313452, 67.30299890154708, 518179.35510937124));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:18:30+00:00\", Cesium.Cartesian3.fromDegrees(5.880557025318269, 69.08128105776676, 518639.74269833014));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:19:00+00:00\", Cesium.Cartesian3.fromDegrees(3.7169906891635627, 70.83852138912368, 519064.5121344491));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:19:30+00:00\", Cesium.Cartesian3.fromDegrees(1.1626334563986747, 72.56853842648421, 519451.81546731724));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:20:00+00:00\", Cesium.Cartesian3.fromDegrees(-1.902062436770439, 74.26253830833996, 519799.96860562864));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:20:30+00:00\", Cesium.Cartesian3.fromDegrees(-5.643970587222167, 75.90771521943759, 520107.4583953582));\n", + " 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widget.property_99affc87.addSample(\"2023-01-01T00:24:00+00:00\", Cesium.Cartesian3.fromDegrees(-74.74153391824163, 82.65743234261397, 521032.68367309216));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:24:30+00:00\", Cesium.Cartesian3.fromDegrees(-88.66595679339765, 82.14972102759158, 520982.644172717));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:25:00+00:00\", Cesium.Cartesian3.fromDegrees(-100.36078101909371, 81.25728358281702, 520886.80610334163));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:25:30+00:00\", Cesium.Cartesian3.fromDegrees(-109.63917157450736, 80.08337613308595, 520745.5853124434));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:26:00+00:00\", Cesium.Cartesian3.fromDegrees(-116.86274248532631, 78.71540437363116, 520559.59465751325));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:26:30+00:00\", Cesium.Cartesian3.fromDegrees(-122.50724006196045, 77.2154002015726, 520329.6414508252));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:27:00+00:00\", Cesium.Cartesian3.fromDegrees(-126.98060391409975, 75.62451136216028, 520056.72409055574));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:27:30+00:00\", Cesium.Cartesian3.fromDegrees(-130.58950094980614, 73.9696427298231, 519742.0278901196));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:28:00+00:00\", Cesium.Cartesian3.fromDegrees(-133.5545560952485, 72.26856284296153, 519386.920120182));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:28:30+00:00\", Cesium.Cartesian3.fromDegrees(-136.0330979380335, 70.5332432679434, 518992.9442809815));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:29:00+00:00\", Cesium.Cartesian3.fromDegrees(-138.13803210992867, 68.77193882849103, 518561.8136252563));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:29:30+00:00\", Cesium.Cartesian3.fromDegrees(-139.95143065769304, 66.99047529868179, 518095.403954947));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:30:00+00:00\", Cesium.Cartesian3.fromDegrees(-141.53386857095842, 65.19305557561566, 517595.7457177179));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:30:30+00:00\", Cesium.Cartesian3.fromDegrees(-142.93076419688757, 63.38277387773156, 517065.0154322012));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:31:00+00:00\", Cesium.Cartesian3.fromDegrees(-144.17669800922525, 61.56195074313122, 516505.52647348936));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:31:30+00:00\", Cesium.Cartesian3.fromDegrees(-145.2983839859477, 59.732356036798244, 515919.7192533581));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:32:00+00:00\", Cesium.Cartesian3.fromDegrees(-146.31674081706035, 57.89536053679485, 515310.15083225875));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:32:30+00:00\", Cesium.Cartesian3.fromDegrees(-147.24835628924433, 56.05204102462409, 514679.48400275235));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:33:00+00:00\", Cesium.Cartesian3.fromDegrees(-148.10653761302837, 54.20325449332078, 514030.4758868045));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:33:30+00:00\", Cesium.Cartesian3.fromDegrees(-148.90207540742983, 52.349691448425865, 513365.9660915495));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:34:00+00:00\", Cesium.Cartesian3.fromDegrees(-149.64380692065384, 50.49191479842679, 512688.864470835));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:34:30+00:00\", Cesium.Cartesian3.fromDegrees(-150.33903656412133, 48.630388644209646, 512002.1385418101));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:35:00+00:00\", Cesium.Cartesian3.fromDegrees(-150.99385369627547, 46.76549987638047, 511308.8006082331));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:35:30+00:00\", Cesium.Cartesian3.fromDegrees(-151.6133754814116, 44.89757457618284, 510611.89464388724));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:36:00+00:00\", Cesium.Cartesian3.fromDegrees(-152.20193446038556, 43.0268906103346, 509914.48299145134));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:36:30+00:00\", Cesium.Cartesian3.fromDegrees(-152.76322486340518, 41.1536874022938, 509219.6329336911));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:37:00+00:00\", Cesium.Cartesian3.fromDegrees(-153.30041780819613, 39.278173583611945, 508530.403195255));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:37:30+00:00\", Cesium.Cartesian3.fromDegrees(-153.81625279938652, 37.40053303566828, 507849.83043442527));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:38:00+00:00\", Cesium.Cartesian3.fromDegrees(-154.3131110090462, 35.52092969622229, 507180.91578518687));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:38:30+00:00\", Cesium.Cartesian3.fromDegrees(-154.79307442878903, 33.63951140858381, 506526.61151042336));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:39:00+00:00\", Cesium.Cartesian3.fromDegrees(-155.25797397597836, 31.75641302167021, 505889.8078275608));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:39:30+00:00\", Cesium.Cartesian3.fromDegrees(-155.7094290665667, 29.871758898647325, 505273.3199677718));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:40:00+00:00\", Cesium.Cartesian3.fromDegrees(-156.14887944424657, 27.98566495469677, 504679.87552976457));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:40:30+00:00\", Cesium.Cartesian3.fromDegrees(-156.57761317843475, 26.098240316905777, 504112.10218830843));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:41:00+00:00\", Cesium.Cartesian3.fromDegrees(-156.9967885535992, 24.20958867866036, 503572.5158168839));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:41:30+00:00\", Cesium.Cartesian3.fromDegrees(-157.40745322341814, 22.319809405386913, 503063.50908229966));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:42:00+00:00\", Cesium.Cartesian3.fromDegrees(-157.81056029565892, 20.42899843667915, 502587.3405675108));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:42:30+00:00\", Cesium.Cartesian3.fromDegrees(-158.206982053685, 18.537249020817296, 502146.12447687704));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:43:00+00:00\", Cesium.Cartesian3.fromDegrees(-158.59752174679778, 16.644652310740476, 501741.82097554376));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:43:30+00:00\", Cesium.Cartesian3.fromDegrees(-158.98292379923365, 14.751297845159367, 501376.227211997));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:44:00+00:00\", Cesium.Cartesian3.fromDegrees(-159.36388272347386, 12.857273934321597, 501050.9690697095));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:44:30+00:00\", Cesium.Cartesian3.fromDegrees(-159.74105097299213, 10.962667966691134, 500767.4936903933));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:45:00+00:00\", Cesium.Cartesian3.fromDegrees(-160.1150459300038, 9.06756665026388, 500527.0628076465));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:45:30+00:00\", Cesium.Cartesian3.fromDegrees(-160.48645619266784, 7.172056200260941, 500330.7469257952));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:46:00+00:00\", Cesium.Cartesian3.fromDegrees(-160.85584730175177, 5.2762224834022495, 500179.4203744899));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:46:30+00:00\", Cesium.Cartesian3.fromDegrees(-161.22376702796555, 3.3801511277748517, 500073.75726517633));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:47:00+00:00\", Cesium.Cartesian3.fromDegrees(-161.5907503266743, 1.4839276064098703, 500014.22837074933));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:47:30+00:00\", Cesium.Cartesian3.fromDegrees(-161.95732405598213, -0.41236269798181335, 500001.09894505603));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:48:00+00:00\", Cesium.Cartesian3.fromDegrees(-162.32401154677652, -2.308634440128287, 500034.4274937818));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:48:30+00:00\", Cesium.Cartesian3.fromDegrees(-162.69133710859748, -4.204802264466732, 500114.0655033297));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:49:00+00:00\", Cesium.Cartesian3.fromDegrees(-163.05983055331401, -6.10078075598479, 500239.65812902915));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:49:30+00:00\", Cesium.Cartesian3.fromDegrees(-163.43003181902174, -7.996484383019531, 500410.6458391872));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:50:00+00:00\", Cesium.Cartesian3.fromDegrees(-163.80249577980234, -9.891827425207591, 500626.2670060124));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:50:30+00:00\", Cesium.Cartesian3.fromDegrees(-164.17779733276518, -11.786723879421537, 500885.56142980413));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:51:00+00:00\", Cesium.Cartesian3.fromDegrees(-164.55653703068967, -13.6810873359798, 501187.3747776679));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:51:30+00:00\", Cesium.Cartesian3.fromDegrees(-164.93934636423123, -15.574830816657336, 501530.36391323386));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:52:00+00:00\", Cesium.Cartesian3.fromDegrees(-165.3268953438948, -17.467866565001803, 501913.0030894203));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:52:30+00:00\", Cesium.Cartesian3.fromDegrees(-165.71989916977046, -19.360105778134816, 502333.5909717588));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:53:00+00:00\", Cesium.Cartesian3.fromDegrees(-166.11912668752834, -21.251458267492346, 502790.2584557664));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:53:30+00:00\", Cesium.Cartesian3.fromDegrees(-166.5254098336956, -23.14183203375625, 503280.97723775444));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:54:00+00:00\", Cesium.Cartesian3.fromDegrees(-166.93965449395094, -25.031132738399243, 503803.5690952676));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:54:30+00:00\", Cesium.Cartesian3.fromDegrees(-167.36285308604894, -26.919263050642854, 504355.71582969144));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:55:00+00:00\", Cesium.Cartesian3.fromDegrees(-167.7960992505605, -28.80612184397096, 504934.9698208067));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:55:30+00:00\", Cesium.Cartesian3.fromDegrees(-168.24060512429895, -30.691603210336158, 505538.76514047914));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:56:00+00:00\", Cesium.Cartesian3.fromDegrees(-168.69772178934673, -32.57559525241569, 506164.4291703355));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:56:30+00:00\", Cesium.Cartesian3.fromDegrees(-169.1689636436393, -34.45797860413529, 506809.1946664192));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:57:00+00:00\", Cesium.Cartesian3.fromDegrees(-169.65603763850487, -36.33862461638469, 507470.2122123029));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:57:30+00:00\", Cesium.Cartesian3.fromDegrees(-170.16087859048807, -38.21739312729571, 508144.5630008639));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:58:00+00:00\", Cesium.Cartesian3.fromDegrees(-170.68569212130916, -40.094129713093096, 508829.271884173));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:58:30+00:00\", Cesium.Cartesian3.fromDegrees(-171.23300724203722, -41.96866228418769, 509521.3206303791));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:59:00+00:00\", Cesium.Cartesian3.fromDegrees(-171.8057412193713, -43.84079684874571, 510217.6613263583));\n", + " widget.property_99affc87.addSample(\"2023-01-01T00:59:30+00:00\", Cesium.Cartesian3.fromDegrees(-172.40728020619724, -45.710312207958474, 510915.22986498737));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:00:00+00:00\", Cesium.Cartesian3.fromDegrees(-173.04158027603893, -47.57695326711263, 511610.95945635554));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:00:30+00:00\", Cesium.Cartesian3.fromDegrees(-173.71329510397612, -49.440422534655035, 512301.7941030726));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:01:00+00:00\", Cesium.Cartesian3.fromDegrees(-174.4279387806934, -51.30036922329144, 512984.7019805861));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:01:30+00:00\", Cesium.Cartesian3.fromDegrees(-175.1920954234289, -53.15637514079682, 513656.68866496097));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:02:00+00:00\", Cesium.Cartesian3.fromDegrees(-176.01369196707364, -55.0079362298119, 514314.8101518461));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:02:30+00:00\", Cesium.Cartesian3.fromDegrees(-176.90235594253622, -56.85443813254697, 514956.1856120419));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:03:00+00:00\", Cesium.Cartesian3.fromDegrees(-177.8698932722313, -58.695123433869405, 515578.009831105));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:03:30+00:00\", Cesium.Cartesian3.fromDegrees(-178.93092964496495, -60.52904713870872, 516177.5652822965));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:04:00+00:00\", Cesium.Cartesian3.fromDegrees(179.89621337587832, -62.35501524326767, 516752.2337844397));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:04:30+00:00\", Cesium.Cartesian3.fromDegrees(178.58830681702977, -64.1714985895305, 517299.5076985581));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:05:00+00:00\", Cesium.Cartesian3.fromDegrees(177.11551460120486, -65.97650991085136, 517817.0006195834));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:05:30+00:00\", Cesium.Cartesian3.fromDegrees(175.4389744793243, -67.76742497901446, 518302.45752199605));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:06:00+00:00\", Cesium.Cartesian3.fromDegrees(173.5073070768232, -69.54071711705829, 518753.7643207166));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:06:30+00:00\", Cesium.Cartesian3.fromDegrees(171.251517088181, -71.29155464768192, 519168.95681146363));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:07:00+00:00\", Cesium.Cartesian3.fromDegrees(168.5774888235921, -73.013177195508, 519546.2289572532));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:07:30+00:00\", Cesium.Cartesian3.fromDegrees(165.3549628840619, -74.69590938062527, 519883.94049077114));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:08:00+00:00\", Cesium.Cartesian3.fromDegrees(161.40171773519558, -76.32557553771517, 520180.6238048203));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:08:30+00:00\", Cesium.Cartesian3.fromDegrees(156.46252288175037, -77.88093780038403, 520434.9901061781));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:09:00+00:00\", Cesium.Cartesian3.fromDegrees(150.1871573672711, -79.32963873752848, 520645.9348108238));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:09:30+00:00\", Cesium.Cartesian3.fromDegrees(142.12842263406904, -80.62229067913985, 520812.54216151265));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:10:00+00:00\", Cesium.Cartesian3.fromDegrees(131.82412513542155, -81.68594313725679, 520934.08905134036));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:10:30+00:00\", Cesium.Cartesian3.fromDegrees(119.0842521598398, -82.42365260045183, 521010.0480400166));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:11:00+00:00\", Cesium.Cartesian3.fromDegrees(104.49741098318235, -82.73551520425212, 521040.08955236647));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:11:30+00:00\", Cesium.Cartesian3.fromDegrees(89.62558141939809, -82.56776147148199, 521024.0832513269));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:12:00+00:00\", Cesium.Cartesian3.fromDegrees(76.21151200295154, -81.95030552915767, 520962.09858080413));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:12:30+00:00\", Cesium.Cartesian3.fromDegrees(65.1595723865476, -80.97492694431195, 520854.404476465));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:13:00+00:00\", Cesium.Cartesian3.fromDegrees(56.46073158350803, -79.7431515679702, 520701.4682454272));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:13:30+00:00\", Cesium.Cartesian3.fromDegrees(49.69257969636662, -78.33582607442469, 520503.9536188246));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:14:00+00:00\", Cesium.Cartesian3.fromDegrees(44.387912711807594, -76.80890246584512, 520262.7179838526));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:14:30+00:00\", Cesium.Cartesian3.fromDegrees(40.165093304537244, -75.1992237719078, 519978.80880506634));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:15:00+00:00\", Cesium.Cartesian3.fromDegrees(36.741995096200995, -73.53090480046316, 519653.4592473066));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:15:30+00:00\", Cesium.Cartesian3.fromDegrees(33.91657197969568, -71.81994502469261, 519288.0830156669));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:16:00+00:00\", Cesium.Cartesian3.fromDegrees(31.544648094398568, -70.07718780054088, 518884.26843080233));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:16:30+00:00\", Cesium.Cartesian3.fromDegrees(29.522452573063212, -68.31015585690093, 518443.77176046453));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:17:00+00:00\", Cesium.Cartesian3.fromDegrees(27.77426384329059, -66.52418955622221, 517968.50983149046));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:17:30+00:00\", Cesium.Cartesian3.fromDegrees(26.243964341330372, -64.72316265474306, 517460.5519487355));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:18:00+00:00\", Cesium.Cartesian3.fromDegrees(24.889306933482526, -62.90994130055134, 516922.1111507197));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:18:30+00:00\", Cesium.Cartesian3.fromDegrees(23.67800099609904, -61.086684758570414, 516355.5348342103));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:19:00+00:00\", Cesium.Cartesian3.fromDegrees(22.585010940237943, -59.25504671102925, 515763.2947829343));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:19:30+00:00\", Cesium.Cartesian3.fromDegrees(21.590666281359734, -57.41631280936791, 515147.9766381164));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:20:00+00:00\", Cesium.Cartesian3.fromDegrees(20.67932040325302, -55.571496504915686, 514512.2688512626));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:20:30+00:00\", Cesium.Cartesian3.fromDegrees(19.838384997074957, -53.72140702772875, 513858.95116215356));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:21:00+00:00\", Cesium.Cartesian3.fromDegrees(19.05762522980383, -51.86669841944499, 513190.88264741626));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:21:30+00:00\", Cesium.Cartesian3.fromDegrees(18.328638371334513, -50.00790544866275, 512510.98938747443));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:22:00+00:00\", Cesium.Cartesian3.fromDegrees(17.644463261997537, -48.14547029312339, 511822.2518017856));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:22:30+00:00\", Cesium.Cartesian3.fromDegrees(16.999284313268543, -46.27976262193474, 511127.69170452695));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:23:00+00:00\", Cesium.Cartesian3.fromDegrees(16.388204659561097, -44.411094891840044, 510430.35913457273));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:23:30+00:00\", Cesium.Cartesian3.fromDegrees(15.807070489976029, -42.53973412608288, 509733.3190156438));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:24:00+00:00\", Cesium.Cartesian3.fromDegrees(15.252333679663362, -40.66591107552644, 509039.63770376967));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:24:30+00:00\", Cesium.Cartesian3.fromDegrees(14.72094321315295, -38.789827408499, 508352.36948073783));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:25:00+00:00\", Cesium.Cartesian3.fromDegrees(14.210259560457075, -36.911661399655635, 507674.5430530753));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:25:30+00:00\", Cesium.Cartesian3.fromDegrees(13.717984410973417, -35.03157246395762, 507009.1481171805));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:26:00+00:00\", Cesium.Cartesian3.fromDegrees(13.242105330354534, -33.14970479325459, 506359.122051495));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:26:30+00:00\", Cesium.Cartesian3.fromDegrees(12.780849950652167, -31.266190289021132, 505727.33679699904));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:27:00+00:00\", Cesium.Cartesian3.fromDegrees(12.332648516080507, -29.38115093816642, 505116.58598727523));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:27:30+00:00\", Cesium.Cartesian3.fromDegrees(11.89610293544671, -27.49470074449376, 504529.5723887815));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:28:00+00:00\", Cesium.Cartesian3.fromDegrees(11.469961038524506, -25.60694730286095, 503968.89571150363));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:28:30+00:00\", Cesium.Cartesian3.fromDegrees(11.053095018555702, -23.717993083957783, 503437.0408488948));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:29:00+00:00\", Cesium.Cartesian3.fromDegrees(10.644483259697004, -21.827936483155813, 502936.3666045627));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:29:30+00:00\", Cesium.Cartesian3.fromDegrees(10.243194914014595, -19.936872675884867, 502469.0949615631));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:30:00+00:00\", Cesium.Cartesian3.fromDegrees(9.848376720256306, -18.044894313558864, 502037.3009477118));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:30:30+00:00\", Cesium.Cartesian3.fromDegrees(9.459241655716186, -16.152092087579025, 501642.9031481749));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:31:00+00:00\", Cesium.Cartesian3.fromDegrees(9.07505908952084, -14.258555183913842, 501287.65491341887));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:31:30+00:00\", Cesium.Cartesian3.fromDegrees(8.695146166087302, -12.364371646842592, 500973.1363076525));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:32:00+00:00\", Cesium.Cartesian3.fromDegrees(8.318860194833796, -10.469628667401853, 500700.7468394011));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:32:30+00:00\", Cesium.Cartesian3.fromDegrees(7.945591859381568, -8.574412809693486, 500471.6990118566));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:33:00+00:00\", Cesium.Cartesian3.fromDegrees(7.574759088814816, -6.678810186356989, 500287.0127268138));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:33:30+00:00\", Cesium.Cartesian3.fromDegrees(7.2058014562829324, -4.782906593069165, 500147.5105716122));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:34:00+00:00\", Cesium.Cartesian3.fromDegrees(6.838174987960179, -2.8867876108253196, 500053.8140139325));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:34:30+00:00\", Cesium.Cartesian3.fromDegrees(6.471347278768828, -0.9905386839228563, 500006.3405246064));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:35:00+00:00\", Cesium.Cartesian3.fromDegrees(6.1047928210641205, 0.9057548190420274, 500005.3016437287));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:35:30+00:00\", Cesium.Cartesian3.fromDegrees(5.737988459225639, 2.8020075542670195, 500050.7020003768));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:36:00+00:00\", Cesium.Cartesian3.fromDegrees(5.370408718880848, 4.698134155270786, 500142.3392911794));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:36:30+00:00\", Cesium.Cartesian3.fromDegrees(5.001521937543872, 6.5940491822800915, 500279.8052177833));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:37:00+00:00\", Cesium.Cartesian3.fromDegrees(4.630784592175432, 8.48966706182752, 500462.4873782902));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:37:30+00:00\", Cesium.Cartesian3.fromDegrees(4.257637098730488, 10.384902009679097, 500689.5721025413));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:38:00+00:00\", Cesium.Cartesian3.fromDegrees(3.881498468860959, 12.279667929801029, 500960.04821628));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:38:30+00:00\", Cesium.Cartesian3.fromDegrees(3.50176072923468, 14.173878281478657, 501272.71171409386));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:39:00+00:00\", Cesium.Cartesian3.fromDegrees(3.1177828190721746, 16.067445905873832, 501626.17131660075));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:39:30+00:00\", Cesium.Cartesian3.fromDegrees(2.72888383211098, 17.96028280221575, 502018.85488258937));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:40:00+00:00\", Cesium.Cartesian3.fromDegrees(2.3343354466444906, 19.85229984239388, 502449.01664263016));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:40:30+00:00\", Cesium.Cartesian3.fromDegrees(1.9333533584266476, 21.7434064108876, 502914.7452165162));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:41:00+00:00\", Cesium.Cartesian3.fromDegrees(1.5250874943062667, 23.633509954613018, 503413.97237311426));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:41:30+00:00\", Cesium.Cartesian3.fromDegrees(1.1086107377408885, 25.522515424252465, 503944.48248771887));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:42:00+00:00\", Cesium.Cartesian3.fromDegrees(0.6829058375670721, 27.410324584763647, 504503.92264887743));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:42:30+00:00\", Cesium.Cartesian3.fromDegrees(0.24685009514204756, 29.296835167794068, 505089.81336355855));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:43:00+00:00\", Cesium.Cartesian3.fromDegrees(-0.2008026728434789, 31.181939832304185, 505699.55980740604));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:43:30+00:00\", Cesium.Cartesian3.fromDegrees(-0.6614435249207059, 33.06552489137243, 506330.4635642186));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:44:00+00:00\", Cesium.Cartesian3.fromDegrees(-1.136633931530598, 34.94746875228285, 506979.7347973979));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:44:30+00:00\", Cesium.Cartesian3.fromDegrees(-1.6281364646493215, 36.827640002715036, 507644.5047943661));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:45:00+00:00\", Cesium.Cartesian3.fromDegrees(-2.1379519286206956, 38.705895056961644, 508321.83882393147));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:45:30+00:00\", Cesium.Cartesian3.fromDegrees(-2.668364593668249, 40.58207525090352, 509008.7492459364));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:46:00+00:00\", Cesium.Cartesian3.fromDegrees(-3.2219976924632503, 42.45600324058878, 509702.20881196647));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:46:30+00:00\", Cesium.Cartesian3.fromDegrees(-3.8018820128016215, 44.327478513275416, 510399.1640958789));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:47:00+00:00\", Cesium.Cartesian3.fromDegrees(-4.411541503223743, 46.19627175676522, 511096.54899312154));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:47:30+00:00\", Cesium.Cartesian3.fromDegrees(-5.055099890199524, 48.0621177455532, 511791.298228331));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:48:00+00:00\", Cesium.Cartesian3.fromDegrees(-5.737417583374546, 49.92470628000877, 512480.36081152194));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:48:30+00:00\", Cesium.Cartesian3.fromDegrees(-6.4642647157296125, 51.783670541410004, 513160.71338427346));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:49:00+00:00\", Cesium.Cartesian3.fromDegrees(-7.24254553352347, 53.638571976600886, 513829.37339845696));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:49:30+00:00\", Cesium.Cartesian3.fromDegrees(-8.080590828509507, 55.488880463416024, 514483.4120718708));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:50:00+00:00\", Cesium.Cartesian3.fromDegrees(-8.988543567041054, 57.33394797218925, 515119.96706659946));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:50:30+00:00\", Cesium.Cartesian3.fromDegrees(-9.978873436987506, 59.172973134468506, 515736.2548379796));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:51:00+00:00\", Cesium.Cartesian3.fromDegrees(-11.067072050394119, 61.00495290291618, 516329.5826041209));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:51:30+00:00\", Cesium.Cartesian3.fromDegrees(-12.272604735017042, 62.82861558082195, 516897.3598881027));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:52:00+00:00\", Cesium.Cartesian3.fromDegrees(-13.620231807503009, 64.64232648603164, 517437.1095873548));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:52:30+00:00\", Cesium.Cartesian3.fromDegrees(-15.141869173827256, 66.44395265747539, 517946.47852712875));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:53:00+00:00\", Cesium.Cartesian3.fromDegrees(-16.87924620204164, 68.23066503687464, 518423.24745757657));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:53:30+00:00\", Cesium.Cartesian3.fromDegrees(-18.887754283020456, 69.99864322467181, 518865.3404565907));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:54:00+00:00\", Cesium.Cartesian3.fromDegrees(-21.24208235934019, 71.74262528396027, 519270.8337030503));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:54:30+00:00\", Cesium.Cartesian3.fromDegrees(-24.044517336030477, 73.4552063655887, 519637.96358820423));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:55:00+00:00\", Cesium.Cartesian3.fromDegrees(-27.43709658339608, 75.12572421230743, 519965.1341352664));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:55:30+00:00\", Cesium.Cartesian3.fromDegrees(-31.618829600092294, 76.7384627275978, 520250.9237005726));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:56:00+00:00\", Cesium.Cartesian3.fromDegrees(-36.86776657704847, 78.26975425042454, 520494.09093199205));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:56:30+00:00\", Cesium.Cartesian3.fromDegrees(-43.56094193606876, 79.68345020256388, 520693.5799635584));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:57:00+00:00\", Cesium.Cartesian3.fromDegrees(-52.163192552605835, 80.92460061186564, 520848.5248278875));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:57:30+00:00\", Cesium.Cartesian3.fromDegrees(-63.104697351166074, 81.91351292073773, 520958.2530708835));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:58:00+00:00\", Cesium.Cartesian3.fromDegrees(-76.42431760661306, 82.54918237431579, 521022.28855611547));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:58:30+00:00\", Cesium.Cartesian3.fromDegrees(-91.26461427537956, 82.73831271064938, 521040.35344916524));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:59:00+00:00\", Cesium.Cartesian3.fromDegrees(-105.90321814567902, 82.44730197482923, 521012.3693749638));\n", + " widget.property_99affc87.addSample(\"2023-01-01T01:59:30+00:00\", Cesium.Cartesian3.fromDegrees(-118.74590143183833, 81.72663570004366, 520938.45774420054));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:00:00+00:00\", Cesium.Cartesian3.fromDegrees(-129.15878740200174, 80.67534523908161, 520818.93924770784));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:00:30+00:00\", Cesium.Cartesian3.fromDegrees(-137.30861605394608, 79.39118279801033, 520654.3325204021));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:01:00+00:00\", Cesium.Cartesian3.fromDegrees(-143.6535591628729, 77.94825452457741, 520445.3519796203));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:01:30+00:00\", Cesium.Cartesian3.fromDegrees(-148.64425141594637, 76.39687054233647, 520192.9048451947));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:02:00+00:00\", Cesium.Cartesian3.fromDegrees(-152.6355056008026, 74.77001009508037, 519898.08735166804));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:02:30+00:00\", Cesium.Cartesian3.fromDegrees(-155.88636158653563, 73.08930840544613, 519562.1801659232));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:03:00+00:00\", Cesium.Cartesian3.fromDegrees(-158.58182029054137, 71.36919316871214, 519186.64302635984));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:03:30+00:00\", Cesium.Cartesian3.fromDegrees(-160.8540862886609, 69.61950153228285, 518773.1086224584));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:04:00+00:00\", Cesium.Cartesian3.fromDegrees(-162.79862473625218, 67.8470997683861, 518323.3757367888));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:04:30+00:00\", Cesium.Cartesian3.fromDegrees(-164.48537220928205, 66.05689043218273, 517839.40167388436));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:05:00+00:00\", Cesium.Cartesian3.fromDegrees(-165.96637234011504, 64.25244870600984, 517323.29400369804));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:05:30+00:00\", Cesium.Cartesian3.fromDegrees(-167.28096286892207, 62.43643272224014, 516777.301649807));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:06:00+00:00\", Cesium.Cartesian3.fromDegrees(-168.45932538062794, 60.61085391489719, 516203.8053554825));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:06:30+00:00\", Cesium.Cartesian3.fromDegrees(-169.5249436581278, 58.77725898013542, 515605.30756343156));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:07:00+00:00\", Cesium.Cartesian3.fromDegrees(-170.49632988024686, 56.93685485709969, 514984.42174760846));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:07:30+00:00\", Cesium.Cartesian3.fromDegrees(-171.38825425919032, 55.090596221523654, 514343.86123826203));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:08:00+00:00\", Cesium.Cartesian3.fromDegrees(-172.2126335122648, 53.239247828539305, 513686.4275837223));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:08:30+00:00\", Cesium.Cartesian3.fromDegrees(-172.97918170462953, 51.383429666142874, 513014.99849498365));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:09:00+00:00\", Cesium.Cartesian3.fromDegrees(-173.69589329364916, 49.523650154872115, 512332.51542145945));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:09:30+00:00\", Cesium.Cartesian3.fromDegrees(-174.3694062580661, 47.66033089872983, 511641.9708083982));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:10:00+00:00\", Cesium.Cartesian3.fromDegrees(-175.00527734056382, 45.7938253736752, 510946.3950885711));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:10:30+00:00\", Cesium.Cartesian3.fromDegrees(-175.60819509846073, 43.924433204188915, 510248.8434626312));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:11:00+00:00\", Cesium.Cartesian3.fromDegrees(-176.18214386104668, 42.0524111864549, 509552.3825243892));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:11:30+00:00\", Cesium.Cartesian3.fromDegrees(-176.73053294889854, 40.177981882684634, 508860.076788529));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:12:00+00:00\", Cesium.Cartesian3.fromDegrees(-177.25629875272168, 38.30134038101089, 508174.9751797051));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:12:30+00:00\", Cesium.Cartesian3.fromDegrees(-177.76198616734908, 36.42265965471515, 507500.0975429317));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:13:00+00:00\", Cesium.Cartesian3.fromDegrees(-178.24981408140377, 34.5420948409269, 506838.42123584123));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:13:30+00:00\", Cesium.Cartesian3.fromDegrees(-178.7217284491364, 32.659786677626386, 506192.867863982));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:14:00+00:00\", Cesium.Cartesian3.fromDegrees(-179.17944561474482, 30.775864278937437, 505566.2902203723));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:14:30+00:00\", Cesium.Cartesian3.fromDegrees(-179.62448792925528, 28.89044738567743, 504961.4594904507));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:15:00+00:00\", Cesium.Cartesian3.fromDegrees(179.94178676823708, 27.00364819636468, 504381.0527829646));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:15:30+00:00\", Cesium.Cartesian3.fromDegrees(179.51816058415264, 25.115572860221544, 503827.6410467364));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:16:00+00:00\", Cesium.Cartesian3.fromDegrees(179.10353496318635, 23.226322695933373, 503303.6774317281));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:16:30+00:00\", Cesium.Cartesian3.fromDegrees(178.6969132864886, 21.335995186466025, 502811.4861516829));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:17:00+00:00\", Cesium.Cartesian3.fromDegrees(178.29738607627567, 19.44468478998351, 502353.25190337683));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:17:30+00:00\", Cesium.Cartesian3.fromDegrees(177.90411832738144, 17.552483599034368, 501931.0098956087));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:18:00+00:00\", Cesium.Cartesian3.fromDegrees(177.5163385789333, 15.659481874103067, 501546.63653810596));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:18:30+00:00\", Cesium.Cartesian3.fromDegrees(177.13332941165427, 13.765768472909262, 501201.84083804535));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:19:00+00:00\", Cesium.Cartesian3.fromDegrees(176.75441911299356, 11.871431193177534, 500898.15654807707));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:19:30+00:00\", Cesium.Cartesian3.fromDegrees(176.3789742966597, 9.976557043738131, 500636.9351067115));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:20:00+00:00\", Cesium.Cartesian3.fromDegrees(176.006393298206, 8.081232456590053, 500419.3394077307));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:20:30+00:00\", Cesium.Cartesian3.fromDegrees(175.63610019562216, 6.18554345081802, 500246.33843120496));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:21:00+00:00\", Cesium.Cartesian3.fromDegrees(175.2675391572243, 4.289575757908757, 500118.70276443317));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:21:30+00:00\", Cesium.Cartesian3.fromDegrees(174.9001700123255, 2.393414916979529, 500037.0010364557));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:22:00+00:00\", Cesium.Cartesian3.fromDegrees(174.5334624224442, 0.49714634766264787, 500001.5972850214));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:22:30+00:00\", Cesium.Cartesian3.fromDegrees(174.1668919233058, -1.399144592171316, 500012.64927008236));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:23:00+00:00\", Cesium.Cartesian3.fromDegrees(173.799935230314, -3.2953725570313095, 500070.10774259723));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:23:30+00:00\", Cesium.Cartesian3.fromDegrees(173.43206573358242, -5.191452166144861, 500173.7166728911));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:24:00+00:00\", Cesium.Cartesian3.fromDegrees(173.06274893248445, -7.087297950941766, 500323.01443696476));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:24:30+00:00\", Cesium.Cartesian3.fromDegrees(172.69143772595686, -8.982824290986935, 500517.33595468244));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:25:00+00:00\", Cesium.Cartesian3.fromDegrees(172.31756747030133, -10.877945331392024, 500755.8157684324));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:25:30+00:00\", Cesium.Cartesian3.fromDegrees(171.94055070884522, -12.772574874280426, 501037.39204579405));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:26:00+00:00\", Cesium.Cartesian3.fromDegrees(171.55977146728233, -14.666626236225897, 501360.81148515246));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:26:30+00:00\", Cesium.Cartesian3.fromDegrees(171.1745789942984, -16.560012062696096, 501724.63509830233));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:27:00+00:00\", Cesium.Cartesian3.fromDegrees(170.7842808083441, -18.45264408935846, 502127.2448397432));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:27:30+00:00\", Cesium.Cartesian3.fromDegrees(170.38813488735812, -20.344432838583682, 502566.8510479958));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:28:00+00:00\", Cesium.Cartesian3.fromDegrees(169.98534080745478, -22.23528723752406, 503041.5006603348));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:28:30+00:00\", Cesium.Cartesian3.fromDegrees(169.5750295973613, -24.1251141416318, 503549.0861585852));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:29:00+00:00\", Cesium.Cartesian3.fromDegrees(169.1562520255705, -26.013817744268547, 504087.3552002067));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:29:30+00:00\", Cesium.Cartesian3.fromDegrees(168.72796497349185, -27.901298848926928, 504653.92088583193));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:30:00+00:00\", Cesium.Cartesian3.fromDegrees(168.28901546661467, -29.787453975274207, 505246.27261145914));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:30:30+00:00\", Cesium.Cartesian3.fromDegrees(167.83812183114048, -31.67217426335989, 505861.7874514589));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:31:00+00:00\", Cesium.Cartesian3.fromDegrees(167.37385130851197, -33.55534413140548, 506497.7420160348));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:31:30+00:00\", Cesium.Cartesian3.fromDegrees(166.89459328479367, -35.43683963093145, 507151.3247254321));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:32:00+00:00\", Cesium.Cartesian3.fromDegrees(166.39852689411745, -37.31652642762592, 507819.6484415539));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:32:30+00:00\", Cesium.Cartesian3.fromDegrees(165.88358262940872, -39.19425731601344, 508499.7633968974));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:33:00+00:00\", Cesium.Cartesian3.fromDegrees(165.347393661357, -41.06986914878751, 509188.6703597659));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:33:30+00:00\", Cesium.Cartesian3.fromDegrees(164.78723791130707, -42.94317902502271, 509883.3339746536));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:34:00+00:00\", Cesium.Cartesian3.fromDegrees(164.19996531206436, -44.81397953160567, 510580.6962165304));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:34:30+00:00\", Cesium.Cartesian3.fromDegrees(163.58190722692711, -46.68203276369342, 511277.68989809585));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:35:00+00:00\", Cesium.Cartesian3.fromDegrees(162.92876245129924, -48.547062754801374, 511971.2521697295));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:35:30+00:00\", Cesium.Cartesian3.fromDegrees(162.23545248215694, -50.40874581334991, 512658.3379526461));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:36:00+00:00\", Cesium.Cartesian3.fromDegrees(161.49593605548333, -52.266698072210616, 513335.9332469342));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:36:30+00:00\", Cesium.Cartesian3.fromDegrees(160.7029691268167, -54.12045928354186, 514001.0682575881));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:37:00+00:00\", Cesium.Cartesian3.fromDegrees(159.84779095597753, -55.96947149037744, 514650.830283107));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:37:30+00:00\", Cesium.Cartesian3.fromDegrees(158.91970890835387, -57.81305061181537, 515282.37631305796));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:38:00+00:00\", Cesium.Cartesian3.fromDegrees(157.90554268726797, -59.65034808244533, 515892.9452830966));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:38:30+00:00\", Cesium.Cartesian3.fromDegrees(156.78887090073331, -61.48029831299158, 516479.86993778346));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:39:00+00:00\", Cesium.Cartesian3.fromDegrees(155.54899587834583, -63.30154559605312, 517040.5882540407));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:39:30+00:00\", Cesium.Cartesian3.fromDegrees(154.159501322441, -65.11234067500604, 517572.65438032994));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:40:00+00:00\", Cesium.Cartesian3.fromDegrees(152.58621358519062, -66.91039167835258, 518073.74904919224));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:40:30+00:00\", Cesium.Cartesian3.fromDegrees(150.78427871592663, -68.69264502015265, 518541.68942321173));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:41:00+00:00\", Cesium.Cartesian3.fromDegrees(148.69391637507454, -70.45495658603429, 518974.43833732343));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:41:30+00:00\", Cesium.Cartesian3.fromDegrees(146.23418843935872, -72.19158751697027, 519370.1129028848));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:42:00+00:00\", Cesium.Cartesian3.fromDegrees(143.29382130344996, -73.89441441369763, 519726.99244178727));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:42:30+00:00\", Cesium.Cartesian3.fromDegrees(139.71783569178402, -75.5516687243367, 520043.52572161594));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:43:00+00:00\", Cesium.Cartesian3.fromDegrees(135.28891317119, -77.1459007631398, 520318.33746571833));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:43:30+00:00\", Cesium.Cartesian3.fromDegrees(129.7047040479027, -78.65070842154365, 520550.234114851));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:44:00+00:00\", Cesium.Cartesian3.fromDegrees(122.56171566360003, -80.02571608625895, 520738.2088199259));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:44:30+00:00\", Cesium.Cartesian3.fromDegrees(113.384977829587, -81.20996561735971, 520881.4456482458));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:45:00+00:00\", Cesium.Cartesian3.fromDegrees(101.80044842306854, -82.11715280723617, 520979.32298847125));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:45:30+00:00\", Cesium.Cartesian3.fromDegrees(87.9586904062353, -82.64414952846583, 521031.4161424525));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:46:00+00:00\", Cesium.Cartesian3.fromDegrees(72.98790359032388, -82.7081101100689, 521037.49909495556));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:46:30+00:00\", Cesium.Cartesian3.fromDegrees(58.69557917028935, -82.29749711830864, 520997.5454550519));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:47:00+00:00\", Cesium.Cartesian3.fromDegrees(46.46556426924445, -81.48061980562845, 520911.7285660751));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:47:30+00:00\", Cesium.Cartesian3.fromDegrees(36.677365297833475, -80.36014187630758, 520780.42078358866));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:48:00+00:00\", Cesium.Cartesian3.fromDegrees(29.04402211908452, -79.02859730464526, 520604.19192401005));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:48:30+00:00\", Cesium.Cartesian3.fromDegrees(23.091410387351104, -77.55343343110597, 520383.8068891903));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:49:00+00:00\", Cesium.Cartesian3.fromDegrees(18.39071477434518, -75.97978922965925, 520120.22247514414));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:49:30+00:00\", Cesium.Cartesian3.fromDegrees(14.613616782573732, -74.33718989119004, 519814.58337620005));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:50:00+00:00\", Cesium.Cartesian3.fromDegrees(11.522593834814476, -72.64506850025201, 519468.21739836136));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:50:30+00:00\", Cesium.Cartesian3.fromDegrees(8.948234665510743, -70.91645523532945, 519082.6298989306));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:51:00+00:00\", Cesium.Cartesian3.fromDegrees(6.7692229187467765, -69.16028866561427, 518659.4974719566));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:51:30+00:00\", Cesium.Cartesian3.fromDegrees(4.897647396640505, -67.38284554349102, 518200.66090216));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:52:00+00:00\", Cesium.Cartesian3.fromDegrees(3.268845583507671, -65.5886329526647, 517708.1174127873));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:52:30+00:00\", Cesium.Cartesian3.fromDegrees(1.834500851053595, -63.78095483692992, 517184.0122354818));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:53:00+00:00\", Cesium.Cartesian3.fromDegrees(0.5579473694726861, -61.962279348558816, 516630.62953335344));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:53:30+00:00\", Cesium.Cartesian3.fromDegrees(-0.5890519737559708, -60.13448224558599, 516050.38271094096));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:54:00+00:00\", Cesium.Cartesian3.fromDegrees(-1.6285447935683612, -58.299011596840316, 515445.8041475929));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:54:30+00:00\", Cesium.Cartesian3.fromDegrees(-2.5779675661283123, -56.45700148707586, 514819.5343933315));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:55:00+00:00\", Cesium.Cartesian3.fromDegrees(-3.4512733696043796, -54.609351994417985, 514174.31086910976));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:55:30+00:00\", Cesium.Cartesian3.fromDegrees(-4.259751191367272, -52.7567864276439, 513512.95611549553));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:56:00+00:00\", Cesium.Cartesian3.fromDegrees(-5.012626777387922, -50.89989294955182, 512838.3656365703));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:56:30+00:00\", Cesium.Cartesian3.fromDegrees(-5.717510708048135, -49.039155295041596, 512153.49538790097));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:57:00+00:00\", Cesium.Cartesian3.fromDegrees(-6.380735999547074, -47.17497575032658, 511461.3489596675));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:57:30+00:00\", Cesium.Cartesian3.fromDegrees(-7.007615486926174, -45.3076925581469, 510764.9645080608));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:58:00+00:00\", Cesium.Cartesian3.fromDegrees(-7.602640163621876, -43.43759325222386, 510067.40148983285));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:58:30+00:00\", Cesium.Cartesian3.fromDegrees(-8.169633566456284, -41.5649249800242, 509371.7272565973));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:59:00+00:00\", Cesium.Cartesian3.fromDegrees(-8.711873087096642, -39.689902570157315, 508681.0035667502));\n", + " widget.property_99affc87.addSample(\"2023-01-01T02:59:30+00:00\", Cesium.Cartesian3.fromDegrees(-9.23218614609716, -37.8127148914289, 507998.2730743476));\n", + " widget.property_99affc87.addSample(\"2023-01-01T03:00:00+00:00\", Cesium.Cartesian3.fromDegrees(-9.733027080406703, -35.93352990392803, 507326.54585491726));\n", + " widget.property_e41ee1cf = new Cesium.SampledProperty(Cesium.Quaternion);\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:00:00+00:00\", new Cesium.Quaternion(0.225870746218323, -0.6695369062609688, 0.13911886637469034, 0.693792964922454));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:00:30+00:00\", new Cesium.Quaternion(0.22740326811385295, -0.6811959792253213, 0.13461027180213792, 0.6827443637729641));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:01:00+00:00\", new Cesium.Quaternion(0.22884831234911612, -0.6926718542220105, 0.13008915274085728, 0.6714990429202183));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:01:30+00:00\", new Cesium.Quaternion(0.2302058867199159, -0.7039611994206347, 0.12555717248812823, 0.660060054742404));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:02:00+00:00\", new Cesium.Quaternion(0.23147603017609403, -0.7150607340957256, 0.12101599059291675, 0.648430508249892));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:02:30+00:00\", new Cesium.Quaternion(0.23265881269839941, -0.725967229592505, 0.11646726227910868, 0.636613568225469));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:03:00+00:00\", new Cesium.Quaternion(0.23375433516463806, -0.7366775102781513, 0.11191263787169166, 0.6246124543480717));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:03:30+00:00\", new Cesium.Quaternion(0.23476272920535185, -0.7471884544782379, 0.10735376222625476, 0.6124304403002397));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:04:00+00:00\", new Cesium.Quaternion(0.23568415704916315, -0.7574969953980396, 0.10279227416203772, 0.6000708528595307));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:04:30+00:00\", new Cesium.Quaternion(0.2365188113575476, -0.767600122028534, 0.09822980589846257, 0.5875370709742008));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:05:00+00:00\", new Cesium.Quaternion(0.23726691504946898, -0.7774948800367182, 0.09366798249563026, 0.5748325248233572));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:05:30+00:00\", new Cesium.Quaternion(0.23792872111579602, -0.7871783726400192, 0.08910842129883272, 0.5619606948618767));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:06:00+00:00\", new Cesium.Quaternion(0.23850451125486227, -0.7966477618144392, 0.08455273058195828, 0.5489251109744016));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:06:30+00:00\", new Cesium.Quaternion(0.23899460032774378, -0.8059002677375983, 0.08000251224096304, 0.5357293509877765));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:07:00+00:00\", new Cesium.Quaternion(0.2393993291716508, -0.8149331717108688, 0.07545935636216387, 0.5223770404361541));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:07:30+00:00\", new Cesium.Quaternion(0.23971906900775275, -0.8237438155704697, 0.0709248439633663, 0.5088718510315073));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:08:00+00:00\", new Cesium.Quaternion(0.23995422005096206, -0.8323296028276064, 0.06640054563674273, 0.4952174997672402));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:08:30+00:00\", new Cesium.Quaternion(0.24010521126510204, -0.8406879994420968, 0.061888021021368776, 0.48141774787750036));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:09:00+00:00\", new Cesium.Quaternion(0.24017250010839575, -0.8488165345784013, 0.05738881828095242, 0.46747639978325356));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:09:30+00:00\", new Cesium.Quaternion(0.24015657226952447, -0.8567128013437878, 0.05290447358701884, 0.4533973020254009));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:10:00+00:00\", new Cesium.Quaternion(0.24005794139451492, -0.864374457508369, 0.048436510607798966, 0.43918434218523916));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:10:30+00:00\", new Cesium.Quaternion(0.23987714880411865, -0.8717992262069187, 0.04398644000274705, 0.424841447792596));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:11:00+00:00\", new Cesium.Quaternion(0.23961476320253516, -0.878984896622055, 0.039555758923237705, 0.4103725852219116));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:11:30+00:00\", new Cesium.Quaternion(0.23927138037680068, -0.8859293246487991, 0.03514595051918822, 0.39578175857662523));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:12:00+00:00\", new Cesium.Quaternion(0.23884762288745642, -0.8926304335401783, 0.030758483452027932, 0.38107300856215987));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:12:30+00:00\", new Cesium.Quaternion(0.23834413975060548, -0.8990862145336801, 0.026394811414147373, 0.3662504113478276));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:13:00+00:00\", new Cesium.Quaternion(0.2377616061112025, -0.9052947274584419, 0.022056372654859286, 0.351318077417996));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:13:30+00:00\", new Cesium.Quaternion(0.2371007229080448, -0.9112541013229063, 0.017744589513172027, 0.33628015041282816));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:14:00+00:00\", new Cesium.Quaternion(0.2363622165302961, -0.9169625348828384, 0.013460867957399262, 0.32114080595894146));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:14:30+00:00\", new Cesium.Quaternion(0.23554683846602725, -0.9224182971894435, 0.009206597131886684, 0.3059042504903098));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:15:00+00:00\", new Cesium.Quaternion(0.2346553649425145, -0.9276197281175199, 0.004983148910851656, 0.29057472005975704));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:15:30+00:00\", new Cesium.Quaternion(0.23368859655870333, -0.9325652388734175, 0.0007918774595805631, 0.27515647914137664));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:16:00+00:00\", new Cesium.Quaternion(0.23264735790996727, -0.9372533124826465, -0.0033658811968886706, 0.25965381942422233));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:16:30+00:00\", new Cesium.Quaternion(0.23153249720518881, -0.9416825042570238, -0.007488809597500302, 0.24407105859761796));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:17:00+00:00\", new Cesium.Quaternion(0.23034488448898166, -0.9458514425790615, -0.011575609596212696, 0.2284125391114558));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:17:30+00:00\", new Cesium.Quaternion(0.22908541678815741, -0.9497588279742954, -0.015625001406813038, 0.2126826270077702));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:18:00+00:00\", new Cesium.Quaternion(0.22775500939963012, -0.953403435548934, -0.019635726082516066, 0.1968857105990089));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:18:30+00:00\", new Cesium.Quaternion(0.22635460101062027, -0.9567841140167468, -0.023606544498680836, 0.18102619927331925));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:19:00+00:00\", new Cesium.Quaternion(0.2248851518985464, -0.959899786401397, -0.027536238094606723, 0.16510852223225012));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:19:30+00:00\", new Cesium.Quaternion(0.2233476435058086, -0.962749450377826, -0.03142360924889237, 0.1491371272331917));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:20:00+00:00\", new Cesium.Quaternion(0.22174307800784354, -0.9653321785923245, -0.035267481646353564, 0.13311647932592077));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:20:30+00:00\", new Cesium.Quaternion(0.22007247787504552, -0.9676471189610811, -0.03906670063631043, 0.11705105958362941));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:21:00+00:00\", new Cesium.Quaternion(0.21833688542831226, -0.9696934949472129, -0.04282013358220184, 0.1009453638287878));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:21:30+00:00\", new Cesium.Quaternion(0.21653736238864885, -0.9714706058161258, -0.046526670202374484, 0.0848039013542212));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:22:00+00:00\", new Cesium.Quaternion(0.21467498942106394, -0.9729778268691063, -0.05018522290194801, 0.06863119363977042));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:22:30+00:00\", new Cesium.Quaternion(0.21275086567251977, -0.9742146096551647, -0.05379472709569319, 0.052431773064891773));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:23:00+00:00\", new Cesium.Quaternion(0.21076610830465997, -0.975180482160933, -0.05735414152177461, 0.03621018161759086));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:23:30+00:00\", new Cesium.Quaternion(0.2087218520209978, -0.9758750489786628, -0.06086244854630584, 0.019970969600042462));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:24:00+00:00\", new Cesium.Quaternion(0.20661924858909725, -0.9762979914521912, -0.06431865445860062, 0.0037186943312858926));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:24:30+00:00\", new Cesium.Quaternion(0.20445946635778905, -0.9764490678008515, -0.06772178975704693, -0.012542081152632261));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:25:00+00:00\", new Cesium.Quaternion(0.20224368976947948, -0.9763281132213086, -0.07107090942551754, -0.02880678940070158));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:25:30+00:00\", new Cesium.Quaternion(0.19997311886799124, -0.9759350399672306, -0.0743650932002339, -0.04507085985078382));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:26:00+00:00\", new Cesium.Quaternion(0.19764896880191757, -0.9752698374068023, -0.0776034458270106, -0.06132972013487677));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:26:30+00:00\", new Cesium.Quaternion(0.19527246932374265, -0.9743325720580457, -0.08078509730880433, -0.07757879738542352));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:27:00+00:00\", new Cesium.Quaternion(0.19284486428497621, -0.9731233876019122, -0.08390920314350428, -0.0938135195422803));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:27:30+00:00\", new Cesium.Quaternion(0.19036741112729327, -0.971642504873179, -0.0869749445518833, -0.11002931665998487));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:28:00+00:00\", new Cesium.Quaternion(-0.18784138037012765, 0.9698902218290841, 0.08998152869566532, 0.126221622214921));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:28:30+00:00\", new Cesium.Quaternion(-0.185268053674913, 0.9678669137675237, 0.09292818867676562, 0.14238587454833526));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:29:00+00:00\", new Cesium.Quaternion(-0.18264872900842966, 0.9655730321602907, 0.09581418454722124, 0.15851751763113997));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:29:30+00:00\", new Cesium.Quaternion(-0.17998471159192286, 0.9630091061971893, 0.09863880231505157, 0.17461200317365205));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:30:00+00:00\", new Cesium.Quaternion(-0.1772773190643528, 0.9601757415673247, 0.10140135488658962, 0.1906647913962041));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:30:30+00:00\", new Cesium.Quaternion(-0.17452787953168974, 0.9570736205922783, 0.1041011820491199, 0.20667135246215365));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:31:00+00:00\", new Cesium.Quaternion(-0.171737731036317, 0.9537035020616265, 0.10673765062845715, 0.22262716777654146));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:31:30+00:00\", new Cesium.Quaternion(-0.16890822102423464, 0.9500662210463423, 0.10931015463632031, 0.23852773128199373));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:32:00+00:00\", new Cesium.Quaternion(-0.16604070581003688, 0.9461626886901706, 0.11181811540742567, 0.25436855075151094));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:32:30+00:00\", new Cesium.Quaternion(-0.1631365500400233, 0.9419938919789986, 0.11426098172630411, 0.2701451490777488));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:33:00+00:00\", new Cesium.Quaternion(-0.16019712615342158, 0.9375608934883168, 0.11663822994376316, 0.2858530655584436));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:33:30+00:00\", new Cesium.Quaternion(-0.157223813842174, 0.9328648311087933, 0.11894936408303322, 0.30148785717757554));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:34:00+00:00\", new Cesium.Quaternion(-0.15421799950936155, 0.9279069177500543, 0.12119391593555542, 0.3170450998819104));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:34:30+00:00\", new Cesium.Quaternion(-0.15118107572633765, 0.9226884410227688, 0.12337144514634889, 0.3325203898525647));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:35:00+00:00\", new Cesium.Quaternion(-0.14811444068902802, 0.9172107628990802, 0.1254815392890299, 0.3479093447711911));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:35:30+00:00\", new Cesium.Quaternion(-0.14501949767338773, 0.9114753193515078, 0.1275238139304084, 0.3632076050804385));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:36:00+00:00\", new Cesium.Quaternion(-0.14189765449027675, 0.9054836199704069, 0.12949791268467922, 0.3784108352383124));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:36:30+00:00\", new Cesium.Quaternion(-0.1387503229400221, 0.8992372475600767, 0.13140350725723382, 0.39351472496606127));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:37:00+00:00\", new Cesium.Quaternion(-0.1355789182666441, 0.8927378577136662, 0.1332402974780079, 0.40851499048925083));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:37:30+00:00\", new Cesium.Quaternion(-0.13238485861227522, 0.8859871783669324, 0.135008011324509, 0.4234073757716212));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:38:00+00:00\", new Cesium.Quaternion(-0.12916956447167688, 0.8789870093310306, 0.13670640493441402, 0.4381876537414038));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:38:30+00:00\", new Cesium.Quaternion(-0.12593445814703108, 0.8717392218044558, 0.13833526260772736, 0.45285162750974733));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:39:00+00:00\", new Cesium.Quaternion(-0.12268096320370009, 0.8642457578642027, 0.13989439679876697, 0.4673951315808196));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:39:30+00:00\", new Cesium.Quaternion(-0.11941050266989589, 0.8565086301115724, 0.1413836473908103, 0.4818140332607507));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:40:00+00:00\", new Cesium.Quaternion(-0.11612450353153703, 0.8485299204168331, 0.14280288447355902, 0.49610423302264695));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:40:30+00:00\", new Cesium.Quaternion(-0.11282438861728467, 0.8403117804145525, 0.1441520041264144, 0.5102616669278611));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:41:00+00:00\", new Cesium.Quaternion(-0.10951158111850468, 0.831856430198268, 0.14543093113302277, 0.524282306976405));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:41:30+00:00\", new Cesium.Quaternion(-0.10618750278291306, 0.8231661578902336, 0.14663961823613303, 0.5381621624756998));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:42:00+00:00\", new Cesium.Quaternion(-0.1028535733776369, 0.814243319011426, 0.14777804606783507, 0.5518972811937755));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:42:30+00:00\", new Cesium.Quaternion(-0.0995112101544039, 0.8050903358319115, 0.14884622306978462, 0.5654837505017505));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:43:00+00:00\", new Cesium.Quaternion(-0.09616182731660988, 0.7957096967018064, 0.14984418540317265, 0.5789176985053314));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:43:30+00:00\", new Cesium.Quaternion(-0.09280683548893809, 0.7861039553629652, 0.15077199684880893, 0.592195295164909));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:44:00+00:00\", new Cesium.Quaternion(-0.08944764118929072, 0.7762757302416378, 0.15162974869708581, 0.6053127534040091));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:44:30+00:00\", new Cesium.Quaternion(-0.08608564630352761, 0.7662277037222582, 0.15241755962808876, 0.6182663302057109));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:45:00+00:00\", new Cesium.Quaternion(-0.08272224756308427, 0.7559626214025876, 0.15313557558184415, 0.6310523276967268));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:45:30+00:00\", new Cesium.Quaternion(-0.07935883602549243, 0.7454832913304303, 0.15378396961862928, 0.6436670942188705));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:46:00+00:00\", new Cesium.Quaternion(-0.07599679655835079, 0.7347925832221107, 0.15436294176970541, 0.6561070253875115));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:46:30+00:00\", new Cesium.Quaternion(-0.07263750732659563, 0.7238934276629582, 0.1548727188782841, 0.668368565136782));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:47:00+00:00\", new Cesium.Quaternion(-0.06928233928332767, 0.7127888152900206, 0.15531355443084446, 0.6804482067512092));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:47:30+00:00\", new Cesium.Quaternion(-0.06593265566455508, 0.7014817959572243, 0.15568572837905104, 0.6923424938834326));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:48:00+00:00\", new Cesium.Quaternion(-0.0625898114877288, 0.6899754778832415, 0.1559895469520746, 0.7040480215577696));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:48:30+00:00\", new Cesium.Quaternion(-0.05925515305457113, 0.6782730267822767, 0.15622534245970685, 0.7155614371592672));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:49:00+00:00\", new Cesium.Quaternion(-0.05593001745801113, 0.6663776649780566, 0.15639347308600224, 0.7268794414080216));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:49:30+00:00\", new Cesium.Quaternion(-0.05261573209378584, 0.6542926705012361, 0.15649432267392532, 0.7379987893184009));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:50:00+00:00\", new Cesium.Quaternion(-0.049313614176583365, 0.6420213761705056, 0.15652830050080127, 0.7489162911429452));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:50:30+00:00\", new Cesium.Quaternion(-0.04602497026095098, 0.6295671686576558, 0.15649584104471007, 0.7596288133006608));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:51:00+00:00\", new Cesium.Quaternion(-0.04275109486230805, 0.616933487599568, 0.156397402612387, 0.7701332795188158));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:51:30+00:00\", new Cesium.Quaternion(-0.039493273626741154, 0.6041238243763544, 0.15623347159172207, 0.7804266708112492));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:52:00+00:00\", new Cesium.Quaternion(-0.03625277738131119, 0.5911417215205433, 0.15600455545907296, 0.7905060277353277));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:52:30+00:00\", new Cesium.Quaternion(-0.03303086535173355, 0.5779907714554255, 0.15571118698371175, 0.800368450336844));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:53:00+00:00\", new Cesium.Quaternion(-0.02982878378629411, 0.5646746155514932, 0.1553539228364606, 0.8100110992257618));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:53:30+00:00\", new Cesium.Quaternion(-0.02664776550911077, 0.5511969431009803, 0.15493334330434222, 0.8194311964051926));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:54:00+00:00\", new Cesium.Quaternion(-0.023489029479239754, 0.5375614902783228, 0.15445005199685857, 0.828626026082961));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:54:30+00:00\", new Cesium.Quaternion(-0.020353780355933326, 0.5237720390868303, 0.15390467554423867, 0.8375929354654736));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:55:00+00:00\", new Cesium.Quaternion(-0.017243208070122917, 0.5098324162918704, 0.15329786328767664, 0.8463293355336778));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:55:30+00:00\", new Cesium.Quaternion(-0.014158487402205433, 0.4957464923408763, 0.15263028696157055, 0.8548327018009008));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:56:00+00:00\", new Cesium.Quaternion(-0.011100777566423276, 0.4815181802704841, 0.15190264036811918, 0.8631005750523032));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:56:30+00:00\", new Cesium.Quaternion(-0.008071221801865897, 0.4671514346011112, 0.1511156390442269, 0.8711305620657583));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:57:00+00:00\", new Cesium.Quaternion(-0.005070946970274409, 0.45265025021929967, 0.15027001992091765, 0.878920336313933));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:57:30+00:00\", new Cesium.Quaternion(-0.0021010631607767394, 0.4380186612481371, 0.1493665409753721, 0.8864676386473658));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:58:00+00:00\", new Cesium.Quaternion(0.0008373366982878661, 0.42326073990608687, 0.14840598087578247, 0.8937702779583258));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:58:30+00:00\", new Cesium.Quaternion(0.0037431772203752045, 0.40838059535455135, 0.14738913861905617, 0.9008261318252773));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:59:00+00:00\", new Cesium.Quaternion(0.006615400934413818, 0.39338237253449926, 0.14631683316157013, 0.907633147137749));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T00:59:30+00:00\", new Cesium.Quaternion(0.009452968650999483, 0.3782702509924954, 0.14518990304318427, 0.9141893407014046));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:00:00+00:00\", new Cesium.Quaternion(0.012254859821044128, 0.3630484436964664, 0.1440092060045305, 0.9204927998231627));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:00:30+00:00\", new Cesium.Quaternion(0.01502007288670032, 0.34772119584154426, 0.14277561859785984, 0.9265416828761691));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:01:00+00:00\", new Cesium.Quaternion(0.017747625624494723, 0.3322927836463344, 0.14149003579147668, 0.9323342198444666));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:01:30+00:00\", new Cesium.Quaternion(0.02043655548056017, 0.31676751313994905, 0.1401533705678863, 0.9378687128472104));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:02:00+00:00\", new Cesium.Quaternion(0.0230859203394968, 0.3011497189062998, 0.13876655213263275, 0.9431435368457741));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:02:30+00:00\", new Cesium.Quaternion(0.02569479705333598, 0.285443762985348, 0.1373305310271914, 0.9481571393102213));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:03:00+00:00\", new Cesium.Quaternion(0.028262284471860966, 0.26965403344291283, 0.13584627043089068, 0.952908041908776));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:03:30+00:00\", new Cesium.Quaternion(0.03078750190908515, 0.25378494324815515, 0.13431475124715148, 0.9573948401282226));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:04:00+00:00\", new Cesium.Quaternion(0.03326958990187326, 0.23784092898977577, 0.13273697029726783, 0.961616203899115));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:04:30+00:00\", new Cesium.Quaternion(0.03570771049533475, 0.22182644961508857, 0.13111393988472755, 0.9655708779940759));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:05:00+00:00\", new Cesium.Quaternion(0.03810104751957534, 0.20574598516236353, 0.12944668735443426, 0.9692576824046548));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:05:30+00:00\", new Cesium.Quaternion(0.04044880685769847, 0.1896040354868055, 0.12773625464708588, 0.9726755126966248));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:06:00+00:00\", new Cesium.Quaternion(0.0427502167050144, 0.1734051189805279, 0.12598369784866423, 0.97582334034363));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:06:30+00:00\", new Cesium.Quaternion(0.04500452781931572, 0.15715377128689983, 0.12419008673547902, 0.9787002130390592));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:07:00+00:00\", new Cesium.Quaternion(0.047211013762171045, 0.14085454400964095, 0.1223565043148014, 0.981305254986055));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:07:30+00:00\", new Cesium.Quaternion(0.049368971131177025, 0.12451200341701958, 0.1204840463611352, 0.9836376671655968));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:08:00+00:00\", new Cesium.Quaternion(0.05147771978304065, 0.1081307291415524, 0.11857382094863599, 0.9856967275825237));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:08:30+00:00\", new Cesium.Quaternion(0.053536603047486475, 0.09171531287555917, 0.11662694797943221, 0.9874817914894823));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:09:00+00:00\", new Cesium.Quaternion(0.05554498793186094, 0.07527035706296949, 0.11464455870846563, 0.9889922915886675));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:09:30+00:00\", new Cesium.Quaternion(0.05750226531642033, 0.05880047358774371, 0.11262779526461351, 0.9902277382113518));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:10:00+00:00\", new Cesium.Quaternion(0.05940785014020989, 0.042310282459294406, 0.11057781016853577, 0.9911877194751075));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:10:30+00:00\", new Cesium.Quaternion(0.06126118157748072, 0.025804410495298493, 0.10849576584750262, 0.9918719014186685));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:11:00+00:00\", new Cesium.Quaternion(0.0630617232046135, 0.009287490002255046, 0.10638283414695822, 0.9922800281144348));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:11:30+00:00\", new Cesium.Quaternion(0.0648089631574687, -0.007235842545796234, 0.10424019583956515, 0.9924119217585183));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:12:00+00:00\", new Cesium.Quaternion(0.06650241427913803, -0.02376094783004655, 0.10206904013139696, 0.9922674827383587));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:12:30+00:00\", new Cesium.Quaternion(0.06814161425804281, -0.040283185010762626, 0.09987056416590963, 0.9918466896778352));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:13:00+00:00\", new Cesium.Quaternion(0.06972612575634768, -0.05679791305184917, 0.09764597252555278, 0.9911495994598917));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:13:30+00:00\", new Cesium.Quaternion(0.0712555364211099, -0.07330049215026788, 0.09539647527867796, 0.9901763473666058));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:14:00+00:00\", new Cesium.Quaternion(0.07272945939914033, -0.0897862846449053, 0.09312329328934651, 0.9889271464936733));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:14:30+00:00\", new Cesium.Quaternion(0.07414753286355577, -0.10625065696154741, 0.09082764899298519, 0.9874022885551231));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:15:00+00:00\", new Cesium.Quaternion(0.07550942046061247, -0.12268898052496918, 0.08851077170573554, 0.9856021432461993));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:15:30+00:00\", new Cesium.Quaternion(0.07681481130586766, -0.13909663318356313, 0.08617389566359789, 0.9835271582967094));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:16:00+00:00\", new Cesium.Quaternion(0.07806342005382624, -0.15546900053007473, 0.08381825951459049, 0.9811778593586509));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:16:30+00:00\", new Cesium.Quaternion(0.07925498695770822, -0.17180147722036612, 0.08144510580985849, 0.9785548498714085));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:17:00+00:00\", new Cesium.Quaternion(0.08038927791930743, -0.188089468289834, 0.07905568049389512, 0.9756588109045636));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:17:30+00:00\", new Cesium.Quaternion(0.08146608452903259, -0.20432839046704532, 0.07665123239461881, 0.9724905009783085));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:18:00+00:00\", new Cesium.Quaternion(0.08248522409597214, -0.22051367348429382, 0.07423301271259047, 0.9690507558615864));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:18:30+00:00\", new Cesium.Quaternion(0.08344653966812532, -0.2366407613846207, 0.07180227451039235, 0.9653404883479494));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:19:00+00:00\", new Cesium.Quaternion(0.08434990004271097, -0.25270511382496613, 0.06936027220184496, 0.9613606880092308));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:19:30+00:00\", new Cesium.Quaternion(0.08519519976658638, -0.26870220737506034, 0.06690826104141494, 0.9571124209270903));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:20:00+00:00\", new Cesium.Quaternion(0.08598235912683394, -0.28462753681165975, 0.06444749661416961, 0.9525968294024908));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:20:30+00:00\", new Cesium.Quaternion(0.08671132413138982, -0.3004766164077983, 0.06197923432595544, 0.9478151316432283));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:21:00+00:00\", new Cesium.Quaternion(0.0873820664799615, -0.31624498121660966, 0.05950472889480622, 0.9427686214295392));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:21:30+00:00\", new Cesium.Quaternion(0.08799458352500308, -0.3319281883494207, 0.05702523384288811, 0.9374586677579427));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:22:00+00:00\", new Cesium.Quaternion(0.08854889822292199, -0.34752181824770256, 0.05454200098970657, 0.9318867144633816));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:22:30+00:00\", new Cesium.Quaternion(0.08904505907555044, -0.3630214759485087, 0.052056279946736325, 0.9260542798197658));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:23:00+00:00\", new Cesium.Quaternion(0.08948314006179996, -0.37842279234305837, 0.04956931761334872, 0.9199629561190549));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:23:30+00:00\", new Cesium.Quaternion(0.08986324055969416, -0.3937214254280653, 0.0470823576746608, 0.9136144092289692));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:24:00+00:00\", new Cesium.Quaternion(0.09018548525859178, -0.4089130615494978, 0.04459664010091262, 0.9070103781294891));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:24:30+00:00\", new Cesium.Quaternion(0.09045002344000222, -0.42399341677101443, 0.04211339932890341, 0.9001526744900047));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:25:00+00:00\", new Cesium.Quaternion(0.09065703133651543, -0.4389582375710164, 0.039633869057941265, 0.893043181913));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:25:30+00:00\", new Cesium.Quaternion(0.09080670834959363, -0.4538033028565207, 0.03715927380250387, 0.8856838557892401));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:26:00+00:00\", new Cesium.Quaternion(0.09089927934532371, -0.46852442464325755, 0.034690833713553956, 0.8780767224926669));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:26:30+00:00\", new Cesium.Quaternion(0.09093499391914894, -0.4831174493883397, 0.03222976275958234, 0.8702238788782405));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:27:00+00:00\", new Cesium.Quaternion(0.09091412625117443, -0.4975782591808855, 0.02977726824132819, 0.8621274916940007));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:27:30+00:00\", new Cesium.Quaternion(0.09083697495202483, -0.5119027729225883, 0.02733455030938102, 0.8537897969729519));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:28:00+00:00\", new Cesium.Quaternion(0.0907038628995846, -0.5260869474978407, 0.024902801485330785, 0.8452130994049253));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:28:30+00:00\", new Cesium.Quaternion(0.09051513706649139, -0.5401267789331045, 0.022483206186279633, 0.836399771688616));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:29:00+00:00\", new Cesium.Quaternion(0.09027116833847515, -0.5540183035451924, 0.02007694025294285, 0.8273522538639717));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:29:30+00:00\", new Cesium.Quaternion(0.08997235132376769, -0.5677575990780953, 0.01768517048174883, 0.8180730526251192));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:30:00+00:00\", new Cesium.Quaternion(0.08961910415342511, -0.581340785828066, 0.015309054160736022, 0.808564740614039));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:30:30+00:00\", new Cesium.Quaternion(0.08921186827290126, -0.5947640277565917, 0.012949738609810671, 0.7988299556951732));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:31:00+00:00\", new Cesium.Quaternion(0.08875110822470905, -0.6080235335909671, 0.010608360725165389, 0.7888714002111912));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:31:30+00:00\", new Cesium.Quaternion(0.08823731142241417, -0.6211155579121246, 0.008286046528260217, 0.7786918402201131));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:32:00+00:00\", new Cesium.Quaternion(0.08767098791609612, -0.6340364022294016, 0.005983910719572964, 0.7682941047140168));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:32:30+00:00\", new Cesium.Quaternion(0.08705267014911072, -0.646782416041965, 0.0037030562369469665, 0.7576810848195531));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:33:00+00:00\", new Cesium.Quaternion(0.08638291270658732, -0.6593499978865389, 0.0014445738191367508, 0.7468557329804926));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:33:30+00:00\", new Cesium.Quaternion(0.08566229205550102, -0.6717355963711642, -0.0007904584256280043, 0.7358210621225464));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:34:00+00:00\", new Cesium.Quaternion(0.0848914062765202, -0.6839357111946778, -0.0030009754457678314, 0.7245801448006971));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:34:30+00:00\", new Cesium.Quaternion(0.08407087478778075, -0.6959468941516083, -0.0051859256669716, 0.7131361123292834));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:35:00+00:00\", new Cesium.Quaternion(0.08320133806059085, -0.7077657501222069, -0.007344271407266435, 0.7014921538950908));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:35:30+00:00\", new Cesium.Quaternion(0.08228345732729633, -0.7193889380473115, -0.009474989286266156, 0.6896515156537057));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:36:00+00:00\", new Cesium.Quaternion(0.08131791320920728, -0.7308131720070699, -0.011577071622627203, 0.6776174997924045));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:36:30+00:00\", new Cesium.Quaternion(0.08030540968068575, -0.7420352216860097, -0.013649522837392335, 0.6653934636587011));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:37:00+00:00\", new Cesium.Quaternion(0.0792466673714105, -0.7530519140208487, -0.015691365862673556, 0.652982818715336));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:37:30+00:00\", new Cesium.Quaternion(0.07814242748185779, -0.7638601336304794, -0.017701638497243474, 0.6403890296310375));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:38:00+00:00\", new Cesium.Quaternion(0.07699345039810684, -0.7744568238315762, -0.019679394796492382, 0.6276156132832779));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:38:30+00:00\", new Cesium.Quaternion(0.07580051535468152, -0.7848389875167134, -0.021623705444168393, 0.6146661377598158));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:39:00+00:00\", new Cesium.Quaternion(0.07456442009039155, -0.7950036880154254, -0.023533658117326342, 0.6015442213454242));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:39:30+00:00\", new Cesium.Quaternion(0.07328598049720197, -0.8049480499379753, -0.025408357844438716, 0.588253531494086));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:40:00+00:00\", new Cesium.Quaternion(0.07196603026224702, -0.8146692600015807, -0.02724692735654459, 0.5747977837869572));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:40:30+00:00\", new Cesium.Quaternion(0.07060542050341528, -0.8241645678388326, -0.029048507431098828, 0.5611807408764053));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:41:00+00:00\", new Cesium.Quaternion(0.06920501939814883, -0.8334312867881165, -0.030812257228763816, 0.5474062114164169));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:41:30+00:00\", new Cesium.Quaternion(0.06776571180603636, -0.8424667946657642, -0.03253735462269699, 0.5334780489796848));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:42:00+00:00\", new Cesium.Quaternion(0.06628839888516996, -0.8512685345197307, -0.03422299652034956, 0.5194001509617022));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:42:30+00:00\", new Cesium.Quaternion(0.0647739977022942, -0.8598340153645789, -0.03586839917772822, 0.5051764574721544));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:43:00+00:00\", new Cesium.Quaternion(0.06322344083720105, -0.8681608128975437, -0.037472798505814996, 0.4908109502139536));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:43:30+00:00\", new Cesium.Quaternion(0.06163767598115466, -0.8762465701954836, -0.039035450369258984, 0.4763076513502205));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:44:00+00:00\", new Cesium.Quaternion(0.06001766552981336, -0.8840889983925018, -0.04055563087704402, 0.4616706223595559));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:44:30+00:00\", new Cesium.Quaternion(0.05836438617060985, -0.891685877338048, -0.04203263666513984, 0.4469039628799233));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:45:00+00:00\", new Cesium.Quaternion(0.05667882846480682, -0.8990350562353079, -0.04346578517099982, 0.43201180954147844));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:45:30+00:00\", new Cesium.Quaternion(0.05496199642444349, -0.906134454259687, -0.0448544148997776, 0.41699833478868686));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:46:00+00:00\", new Cesium.Quaternion(0.05321490708415194, -0.9129820611572246, -0.04619788568225579, 0.4018677456920627));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:46:30+00:00\", new Cesium.Quaternion(0.05143859006824625, -0.9195759378227439, -0.04749557892427603, 0.3866242827498809));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:47:00+00:00\", new Cesium.Quaternion(0.04963408579480316, -0.9259142169303918, -0.048746898392301216, 0.37127221860869725));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:47:30+00:00\", new Cesium.Quaternion(0.04780245045763509, -0.9319951031768565, -0.04995126824450847, 0.3558158571303019));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:48:00+00:00\", new Cesium.Quaternion(0.04594474745734245, -0.9378168742426495, -0.0511081365900747, 0.3402595317417542));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:48:30+00:00\", new Cesium.Quaternion(0.04406205235607635, -0.9433778809883953, -0.0522169734577649, 0.3246076044810517));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:49:00+00:00\", new Cesium.Quaternion(0.042155451073987105, -0.9486765480047497, -0.05327727156900577, 0.3088644646842744));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:49:30+00:00\", new Cesium.Quaternion(0.04022603943050618, -0.9537113740657015, -0.05428854653497437, 0.2930345277344754));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:50:00+00:00\", new Cesium.Quaternion(0.038274922682208945, -0.9584809325605517, -0.055250337044593624, 0.27712223380303713));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:50:30+00:00\", new Cesium.Quaternion(0.03630321505702949, -0.9629838719044639, -0.056162205043508016, 0.26113204658383316));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:51:00+00:00\", new Cesium.Quaternion(0.03431203928514237, -0.9672189159274625, -0.05702373590392335, 0.24506845202057148));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:51:30+00:00\", new Cesium.Quaternion(0.03230252612686124, -0.971184864241753, -0.05783453858520557, 0.2289359570276972));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:52:00+00:00\", new Cesium.Quaternion(0.030275813897216952, -0.9748805925872839, -0.05859424578531517, 0.21273908820519427));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:52:30+00:00\", new Cesium.Quaternion(0.028233047988231952, -0.9783050531554099, -0.059302514082811876, 0.1964823905477101));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:53:00+00:00\", new Cesium.Quaternion(0.02617538038808276, -0.981457274890605, -0.05995902406962024, 0.18017042614831488));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:53:30+00:00\", new Cesium.Quaternion(0.024103969198164488, -0.9843363637701046, -0.06056348047430952, 0.16380777289732176));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:54:00+00:00\", new Cesium.Quaternion(0.022019978147730823, -0.9869415030614106, -0.061115612275961455, 0.14739902317651715));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:54:30+00:00\", new Cesium.Quaternion(0.01992457610647247, -0.9892719535575839, -0.06161517280853957, 0.1309487825491826));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:55:00+00:00\", new Cesium.Quaternion(0.017818936595281054, -0.9913270537902449, -0.062061939855719735, 0.1144616684463036));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:55:30+00:00\", new Cesium.Quaternion(0.015704237295158463, -0.9931062202202361, -0.06245571573617727, 0.09794230884931843));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:56:00+00:00\", new Cesium.Quaternion(0.013581659554823211, -0.9946089474058744, -0.06279632737925461, 0.08139534096982148));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:56:30+00:00\", new Cesium.Quaternion(0.011452387896688787, -0.995834808148757, -0.06308362639104226, 0.06482540992656723));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:57:00+00:00\", new Cesium.Quaternion(0.009317609521874881, -0.9967834536170728, -0.06331748911079332, 0.048237167420188035));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:57:30+00:00\", new Cesium.Quaternion(0.007178513814229792, -0.9974546134463793, -0.06349781665768055, 0.03163527040599664));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:58:00+00:00\", new Cesium.Quaternion(0.00503629184341603, -0.9978480958178245, -0.06362453496788081, 0.01502437976525345));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:58:30+00:00\", new Cesium.Quaternion(0.0028921344036878516, -0.9979637875180257, -0.06369759481962294, -0.0015908411181392093));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:59:00+00:00\", new Cesium.Quaternion(0.0007472373718296899, -0.9978016539519913, -0.0637169718358387, -0.018205727314558377));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T01:59:30+00:00\", new Cesium.Quaternion(-0.0013972075746157553, -0.9973617391884442, -0.06368266655125782, -0.03481561424011809));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:00:00+00:00\", new Cesium.Quaternion(-0.0035400075999667546, -0.9966441659212312, -0.063594704346886, -0.05141583861416663));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:00:30+00:00\", new Cesium.Quaternion(-0.005679970672185508, -0.9956491354419176, -0.06345313546059606, -0.06800173988321634));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:01:00+00:00\", new Cesium.Quaternion(-0.007815906060453293, -0.9943769275823984, -0.06325803496598277, -0.0845686615507566));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:01:30+00:00\", new Cesium.Quaternion(-0.009946624832426754, -0.9928279006349252, -0.0630095027415113, -0.1011119525059121));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:02:00+00:00\", new Cesium.Quaternion(-0.012070940350727033, -0.9910024912495746, -0.06270766342997951, -0.11762696835053943));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:02:30+00:00\", new Cesium.Quaternion(-0.014187668768417705, -0.9889012143091895, -0.06235266638832577, -0.1341090727243843));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:03:00+00:00\", new Cesium.Quaternion(0.016295629523699562, 0.9865246627818256, 0.06194468562775548, 0.15055363862793353));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:03:30+00:00\", new Cesium.Quaternion(0.01839364583307851, 0.9838735075507481, 0.06148391974426657, 0.16695604974254674));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:04:00+00:00\", new Cesium.Quaternion(0.020480545183344023, 0.9809484972220298, 0.06097059183953881, 0.18331170174751701));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:04:30+00:00\", new Cesium.Quaternion(0.022555159821708415, 0.9777504579098036, 0.0604049494322808, 0.1996160036336521));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:05:00+00:00\", new Cesium.Quaternion(0.024616327244364355, 0.9742802929992322, 0.05978726435999594, 0.21586437901301928));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:05:30+00:00\", new Cesium.Quaternion(0.026662890682906504, 0.9705389828872677, 0.059117832671267564, 0.23205226742445675));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:06:00+00:00\", new Cesium.Quaternion(0.02869369958867879, 0.96652758470127, 0.05839697450855715, 0.24817512563448216));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:06:30+00:00\", new Cesium.Quaternion(0.030707610114696693, 0.962247231995575, 0.05762503398159714, 0.26422842893322085));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:07:00+00:00\", new Cesium.Quaternion(0.032703485595193205, 0.9576991344260887, 0.0568023790313649, 0.2802076724249768));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:07:30+00:00\", new Cesium.Quaternion(0.03468019702231895, 0.9528845774030155, 0.05592940128476179, 0.29610837231307385));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:08:00+00:00\", new Cesium.Quaternion(0.036636623520054534, 0.9478049217218112, 0.055006515899989214, 0.3119260671785954));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:08:30+00:00\", new Cesium.Quaternion(0.038571652814969826, 0.9424616031724755, 0.05403416140273266, 0.32765631925264715));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:09:00+00:00\", new Cesium.Quaternion(0.040484181703968225, 0.9368561321272871, 0.05301279951311011, 0.3432947156817915));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:09:30+00:00\", new Cesium.Quaternion(0.04237311788397746, 0.9309900930449654, 0.05194291443724751, 0.35883686986245167));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:10:00+00:00\", new Cesium.Quaternion(0.04423737494100044, 0.924865144261564, 0.05082501475896752, 0.37427842238514974));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:10:30+00:00\", new Cesium.Quaternion(0.046075881027551224, 0.9184830171496102, 0.04965963014952865, 0.38961504273923475));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:11:00+00:00\", new Cesium.Quaternion(0.047887573826701835, 0.9118455158612584, 0.04844731319589113, 0.4048424302377493));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:11:30+00:00\", new Cesium.Quaternion(0.049671402375256024, 0.9049545167508176, 0.047188638679298026, 0.4199563153209683));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:12:00+00:00\", new Cesium.Quaternion(0.05142632750823295, 0.8978119678359348, 0.04588420334876526, 0.43495246077316485));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:12:30+00:00\", new Cesium.Quaternion(0.05315132229918079, 0.8904198882381898, 0.04453462568579653, 0.4498266629300273));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:13:00+00:00\", new Cesium.Quaternion(0.054845372495576195, 0.8827803676032846, 0.04314054566067797, 0.46457475287635924));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:13:30+00:00\", new Cesium.Quaternion(0.05650747694972508, 0.874895565500976, 0.041702624480167635, 0.4791925976337385));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:14:00+00:00\", new Cesium.Quaternion(0.05813664804466834, 0.8667677108049356, 0.040221544326826945, 0.4936761013377769));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:14:30+00:00\", new Cesium.Quaternion(0.059731912114958985, 0.8583991010527234, 0.03869800809008143, 0.5080212064046417));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:15:00+00:00\", new Cesium.Quaternion(0.06129230986225287, 0.8497921017860497, 0.03713273908905564, 0.5222238946865051));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:15:30+00:00\", new Cesium.Quaternion(0.06281689676549479, 0.8409491458715269, 0.035526480787313866, 0.5362801886155888));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:16:00+00:00\", new Cesium.Quaternion(0.06430474348556647, 0.8318727328021022, 0.033879996499597144, 0.5501861523364664));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:16:30+00:00\", new Cesium.Quaternion(0.06575493626418033, 0.8225654279793831, 0.03219406909070688, 0.5639378928263032));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:17:00+00:00\", new Cesium.Quaternion(0.06716657731703524, 0.8130298619770511, 0.030469500666531778, 0.5775315610027076));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:17:30+00:00\", new Cesium.Quaternion(0.06853878522086865, 0.8032687297855925, 0.02870711225747223, 0.5909633528188747));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:18:00+00:00\", new Cesium.Quaternion(0.06987069529436257, 0.7932847900385637, 0.026907743494315673, 0.604229510345695));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:18:30+00:00\", new Cesium.Quaternion(0.0711614599728776, 0.7830808642206011, 0.02507225227658651, 0.6173263228405413));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:19:00+00:00\", new Cesium.Quaternion(0.07241024917656796, 0.7726598358574335, 0.023201514433718384, 0.6302501278023938));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:19:30+00:00\", new Cesium.Quaternion(0.07361625067215144, 0.7620246496880985, 0.021296423378857506, 0.6429973120130242));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:20:00+00:00\", new Cesium.Quaternion(0.07477867042774633, 0.7511783108196426, 0.019357889755770845, 0.655564312563924));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:20:30+00:00\", new Cesium.Quaternion(0.07589673296097427, 0.7401238838645223, 0.01738684107873181, 0.6679476178686835));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:21:00+00:00\", new Cesium.Quaternion(0.076969682749334, 0.7288644919480506, 0.015384220367817867, 0.6801437686831011));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:21:30+00:00\", new Cesium.Quaternion(0.07799678027053741, 0.7174033162621128, 0.013350989748673419, 0.6921493589943457));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:22:00+00:00\", new Cesium.Quaternion(0.07897730879466908, 0.7057435944793555, 0.011288124139072295, 0.7039610371322629));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:22:30+00:00\", new Cesium.Quaternion(0.07991057037688123, 0.6938886202709771, 0.009196614799959835, 0.7155755066215603));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:23:00+00:00\", new Cesium.Quaternion(0.08079588725514178, 0.6818417422501943, 0.007077467962707396, 0.7269895271426616));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:23:30+00:00\", new Cesium.Quaternion(0.08163260215446791, 0.6696063630113668, 0.0049317044302753755, 0.7381999154508163));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:24:00+00:00\", new Cesium.Quaternion(0.08242007858353953, 0.6571859381536675, 0.0027603591723062344, 0.749203546278718));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:24:30+00:00\", new Cesium.Quaternion(0.08315770112351659, 0.6445839752896104, 0.0005644809143420833, 0.7599973532223597));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:25:00+00:00\", new Cesium.Quaternion(0.08384487570882865, 0.6318040330387263, -0.0016548682785514708, 0.7705783296098794));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:25:30+00:00\", new Cesium.Quaternion(0.08448102989991588, 0.6188497200066752, -0.0038966134236895645, 0.7809435293531383));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:26:00+00:00\", new Cesium.Quaternion(0.0850656131478855, 0.6057246937500799, -0.006159667048141186, 0.7910900677817935));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:26:30+00:00\", new Cesium.Quaternion(0.08559809705081364, 0.5924326597274064, -0.00844292962121703, 0.8010151224596211));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:27:00+00:00\", new Cesium.Quaternion(0.08607797560172803, 0.5789773702361753, -0.010745289992069314, 0.8107159339828578));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:27:30+00:00\", new Cesium.Quaternion(0.08650476542812482, 0.5653626233368233, -0.013065625832196672, 0.8201898067603275));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:28:00+00:00\", new Cesium.Quaternion(0.08687800602289028, 0.551592261763529, -0.01540280408263308, 0.8294341097751365));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:28:30+00:00\", new Cesium.Quaternion(0.0871972599666607, 0.5376701718223094, -0.017755681405840214, 0.8384462773277067));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:29:00+00:00\", new Cesium.Quaternion(0.08746211314132718, 0.5236002822767265, -0.020123104641841368, 0.8472238097599475));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:29:30+00:00\", new Cesium.Quaternion(0.08767217493482865, 0.509386563221505, -0.022503911268764776, 0.8557642741603487));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:30:00+00:00\", new Cesium.Quaternion(0.08782707843699156, 0.4950330249444044, -0.024896929867399515, 0.8640653050497937));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:30:30+00:00\", new Cesium.Quaternion(0.08792648062636008, 0.4805437167766799, -0.027300980589609915, 0.8721246050479039));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:31:00+00:00\", new Cesium.Quaternion(0.08797006254800557, 0.4659227259324513, -0.02971487563055066, 0.8799399455197126));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:31:30+00:00\", new Cesium.Quaternion(0.08795752948220345, 0.4511741763373269, -0.03213741970444886, 0.8875091672024927));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:32:00+00:00\", new Cesium.Quaternion(0.08788861174394527, 0.4363022273176918, -0.0345674118364574, 0.8948301807618427));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:32:30+00:00\", new Cesium.Quaternion(0.08776306225101049, 0.42131107292475817, -0.03700364060471043, 0.901900967577545));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:33:00+00:00\", new Cesium.Quaternion(0.08758066057082856, 0.40620493995897783, -0.03944489247025209, 0.9087195800162506));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:33:30+00:00\", new Cesium.Quaternion(0.08734121042624299, 0.39098808727519774, -0.041889947046581284, 0.9152841421693024));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:34:00+00:00\", new Cesium.Quaternion(0.0870445404793425, 0.3756648044337088, -0.044337578892422555, 0.9215928503306012));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:34:30+00:00\", new Cesium.Quaternion(0.08669050444406848, 0.3602394104716268, -0.04678655800534633, 0.9276439735007718));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:35:00+00:00\", new Cesium.Quaternion(0.08627898118916556, 0.344716252666, -0.04923565031745996, 0.9334358538703593));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:35:30+00:00\", new Cesium.Quaternion(0.08580987483162503, 0.32909970528895305, -0.05168361819344719, 0.9389669072819018));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:36:00+00:00\", new Cesium.Quaternion(0.08528311482043585, 0.3133941683552601, -0.05412922093042658, 0.9442356236707575));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:36:30+00:00\", new Cesium.Quaternion(0.08469865601068834, 0.2976040663626972, -0.05657121525965214, 0.9492405674845639));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:37:00+00:00\", new Cesium.Quaternion(0.0840564787279637, 0.2817338470255407, -0.05900835584979824, 0.9539803780811995));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:37:30+00:00\", new Cesium.Quaternion(0.0833565888229853, 0.26578798000158205, -0.06143939581166291, 0.9584537701051482));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:38:00+00:00\", new Cesium.Quaternion(0.08259901771648073, 0.24977095561303292, -0.06386308720403047, 0.962659533842155));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:38:30+00:00\", new Cesium.Quaternion(0.08178382243428654, 0.23368728356167648, -0.0662781815407054, 0.9665965355520675));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:39:00+00:00\", new Cesium.Quaternion(0.08091108563260087, 0.2175414916386555, -0.06868343029827736, 0.9702637177797822));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:39:30+00:00\", new Cesium.Quaternion(0.07998091561340684, 0.2013381244292713, -0.07107758542456348, 0.9736600996442026));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:40:00+00:00\", new Cesium.Quaternion(0.07899344633005712, 0.18508174201315147, -0.07345939984756794, 0.9767847771051272));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:40:30+00:00\", new Cesium.Quaternion(0.07794883738300885, 0.1687769186601733, -0.07582762798481656, 0.9796369232079868));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:41:00+00:00\", new Cesium.Quaternion(0.07684727400563893, 0.15242824152254467, -0.07818102625251529, 0.9822157883063939));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:41:30+00:00\", new Cesium.Quaternion(0.07568896704024763, 0.13604030932337358, -0.08051835357495445, 0.9845207002623967));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:42:00+00:00\", new Cesium.Quaternion(0.07447415290415077, 0.11961773104215098, -0.0828383718934346, 0.9865510646244229));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:42:30+00:00\", new Cesium.Quaternion(0.07320309354590564, 0.10316512459750946, -0.08513984667474038, 0.9883063647828499));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:43:00+00:00\", new Cesium.Quaternion(0.07187607639169061, 0.08668711552763118, -0.08742154741910563, 0.9897861621031507));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:43:30+00:00\", new Cesium.Quaternion(0.07049341438476456, 0.07018833556530739, -0.08968224962082855, 0.9909900959050486));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:44:00+00:00\", new Cesium.Quaternion(0.06905544547608485, 0.05367342173054926, -0.09192072946095504, 0.9919178840736769));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:44:30+00:00\", new Cesium.Quaternion(0.06756253323156552, 0.037147014379598026, -0.09413577302965961, 0.9925693223458621));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:45:00+00:00\", new Cesium.Quaternion(0.06601506625465295, 0.02061375629960043, -0.09632617101983185, 0.992944284869636));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:45:30+00:00\", new Cesium.Quaternion(0.0644134582107496, 0.004078291277636502, -0.09849072068075541, 0.9930427240966887));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:46:00+00:00\", new Cesium.Quaternion(0.06275814771472926, -0.012454737224857616, -0.1006282263181498, 0.9928646707805345));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:46:30+00:00\", new Cesium.Quaternion(0.061049598208730474, -0.02898068739732253, -0.10273749979225384, 0.9924102339521534));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:47:00+00:00\", new Cesium.Quaternion(0.0592882978302664, -0.045494920404574694, -0.10481736101369112, 0.9916796008731331));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:47:30+00:00\", new Cesium.Quaternion(0.057474759270683046, -0.061992801710202064, -0.10686663843714815, 0.9906730369663044));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:48:00+00:00\", new Cesium.Quaternion(0.055609519624015155, -0.0784697023984552, -0.10888416955239473, 0.9893908857239233));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:48:30+00:00\", new Cesium.Quaternion(0.053693140226277705, -0.09492100049426398, -0.11086880137269522, 0.98783356859341));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:49:00+00:00\", new Cesium.Quaternion(0.05172620648525081, -0.11134208228099021, -0.1128193909202645, 0.9860015848406933));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:49:30+00:00\", new Cesium.Quaternion(0.049709327700800165, -0.1277283436155446, -0.11473480570872249, 0.9838955113911976));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:50:00+00:00\", new Cesium.Quaternion(0.04764313687577963, -0.1440751912404774, -0.11661392422238558, 0.9815160026485108));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:50:30+00:00\", new Cesium.Quaternion(0.04552829051762225, -0.1603780440926605, -0.1184556363918583, 0.978863790290843));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:51:00+00:00\", new Cesium.Quaternion(0.04336546843060535, -0.17663233460820224, -0.12025884406635999, 0.9759396830452554));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:51:30+00:00\", new Cesium.Quaternion(0.041155373498922426, -0.19283351002319427, -0.12202246148206125, 0.9727445664398017));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:52:00+00:00\", new Cesium.Quaternion(0.03889873146060803, -0.20897703366992507, -0.12374541572647958, 0.9692794025336323));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:52:30+00:00\", new Cesium.Quaternion(0.0365962906723565, -0.2250583862681911, -0.12542664719888463, 0.9655452296251218));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:53:00+00:00\", new Cesium.Quaternion(0.03424882186538089, -0.24107306721131758, -0.1270651100661905, 0.9615431619381567));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:53:30+00:00\", new Cesium.Quaternion(0.031857117892300287, -0.2570165958465333, -0.12865977271459406, 0.9572743892866271));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:54:00+00:00\", new Cesium.Quaternion(0.02942199346524102, -0.2728845127493156, -0.1302096181963307, 0.9527401767172758));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:54:30+00:00\", new Cesium.Quaternion(0.026944284461648815, -0.2886723810308747, -0.1317136460624514, 0.9479418639377366));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:55:00+00:00\", new Cesium.Quaternion(0.02442484931578709, -0.3043757874375613, -0.13317086723008323, 0.9428808656870991));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:55:30+00:00\", new Cesium.Quaternion(0.021864566259250484, -0.31999034385311265, -0.1345803127796993, 0.9375586701615959));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:56:00+00:00\", new Cesium.Quaternion(0.019264334649042106, -0.3355116883761894, -0.13594102879796816, 0.9319768393382094));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:56:30+00:00\", new Cesium.Quaternion(0.016625074262489173, -0.350935486602285, -0.13725207819645066, 0.926137008319903));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:57:00+00:00\", new Cesium.Quaternion(0.013947724984157459, -0.3662574328542791, -0.13851254112711872, 0.9200408848509224));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:57:30+00:00\", new Cesium.Quaternion(0.01123324648459019, -0.3814732514044341, -0.13972151539206243, 0.9136902488113201));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:58:00+00:00\", new Cesium.Quaternion(0.00848261789097228, -0.3965786976874882, -0.14087811684724086, 0.9070869516908435));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:58:30+00:00\", new Cesium.Quaternion(0.005696837449862588, -0.41156955950448676, -0.14198147980005707, 0.9002329160423644));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:59:00+00:00\", new Cesium.Quaternion(0.002876922182056832, -0.426441658217016, -0.14303075740071855, 0.8931301349149838));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T02:59:30+00:00\", new Cesium.Quaternion(2.390752968020604e-05, -0.44119084993148505, -0.14402512202726078, 0.8857806712669885));\n", + " widget.property_e41ee1cf.addSample(\"2023-01-01T03:00:00+00:00\", new Cesium.Quaternion(-0.002861153004257433, -0.4558130266731231, -0.14496376566383687, 0.8781866573588631));\n", " widget.Payload_position = new Cesium.SampledProperty(Cesium.Cartesian3);\n", " widget.Payload_position.addSample(\"2023-01-01T00:00:00+00:00\", Cesium.Cartesian3.fromDegrees(29.98055060896214, -0.08103079020036194, 500000.0424350213));\n", " widget.Payload_position.addSample(\"2023-01-01T00:00:30+00:00\", Cesium.Cartesian3.fromDegrees(29.61394459855244, 1.8152541965297813, 500021.2891134799));\n", @@ -1641,7 +1635,7 @@ " widget.Payload_orientation.addSample(\"2023-01-01T02:59:00+00:00\", new Cesium.Quaternion(0.002876922182056832, -0.426441658217016, -0.14303075740071855, 0.8931301349149838));\n", " widget.Payload_orientation.addSample(\"2023-01-01T02:59:30+00:00\", new Cesium.Quaternion(2.390752968020604e-05, -0.44119084993148505, -0.14402512202726078, 0.8857806712669885));\n", " widget.Payload_orientation.addSample(\"2023-01-01T03:00:00+00:00\", new Cesium.Quaternion(-0.002861153004257433, -0.4558130266731231, -0.14496376566383687, 0.8781866573588631));\n", - " widget.entities.add({position: widget.property_9bfe1ee8, orientation: widget.property_84f93f67, model: {uri: await Cesium.IonResource.fromAssetId(669199), availability: new Cesium.TimeIntervalCollection({intervals: [new Cesium.TimeInterval({start: Cesium.JulianDate.fromIso8601(\"2023-01-01T00:00:00+00:00\"), stop: Cesium.JulianDate.fromIso8601(\"2023-01-01T03:00:00+00:00\")})]})}});\n", + " widget.entities.add({position: widget.property_99affc87, orientation: widget.property_e41ee1cf, model: {uri: await Cesium.IonResource.fromAssetId(669199), availability: new Cesium.TimeIntervalCollection({intervals: [new Cesium.TimeInterval({start: Cesium.JulianDate.fromIso8601(\"2023-01-01T00:00:00+00:00\"), stop: Cesium.JulianDate.fromIso8601(\"2023-01-01T03:00:00+00:00\")})]})}});\n", " widget.entities.add({position: widget.Payload_position, orientation: widget.Payload_orientation, conicSensor: new CesiumSensorVolumes.ConicSensorGraphics({radius: 1.0, innerHalfAngle: 0.13962634015954636, outerHalfAngle: 0.13962634015954636, lateralSurfaceMaterial: Cesium.Color.RED, showIntersection: true, intersectionColor: Cesium.Color.WHITE, intersectionWidth: 1.0, show: true})});\n", " widget.entities.add({polyline: {positions: Cesium.Cartesian3.fromDegreesArrayHeights([29.98055060896214, -0.08103079020036194, 500000.0424350213, 29.61394459855244, 1.8152541965297813, 500021.2891134799, 29.246837283092006, 3.711457477700564, 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a/_build/jupyter_execute/d578584f85e6a5a5245b581dc521d9f955ac98d1e6a1a90bd3c1eaffde43f943.svg +++ b/_build/jupyter_execute/c09ff20d60d705a86280b5ec46c7cafd06658f5752af67451ed84e96eb1f4504.svg @@ -1 +1 @@ - \ No newline at end of file + \ No newline at end of file diff --git a/conf.py b/conf.py index 1fab3ca65..b1a1bb3a6 100644 --- a/conf.py +++ b/conf.py @@ -172,6 +172,10 @@ def setup(app): intersphinx_mapping = { "python": ("https://docs.python.org/3", None), "numpy": ("https://numpy.org/doc/stable/", None), + "ostk.physics": ( + "https://open-space-collective.github.io/open-space-toolkit-physics/_build/html/", + None, + ), } # -- Breathe configuration ------------------------------------------------- diff --git a/dev/bench/data.js b/dev/bench/data.js deleted file mode 100644 index f1bbd2fe9..000000000 --- a/dev/bench/data.js +++ /dev/null @@ -1,62 +0,0 @@ -window.BENCHMARK_DATA = { - "lastUpdate": 1715363886539, - "repoUrl": 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