diff --git a/_autosummary/ostk.astrodynamics.trajectory.Orbit.rst b/_autosummary/ostk.astrodynamics.trajectory.Orbit.rst index e45abc46d..8201c91e4 100644 --- a/_autosummary/ostk.astrodynamics.trajectory.Orbit.rst +++ b/_autosummary/ostk.astrodynamics.trajectory.Orbit.rst @@ -26,6 +26,7 @@ ostk.astrodynamics.trajectory.Orbit ~Orbit.compute_passes ~Orbit.compute_passes_with_model ~Orbit.equatorial + ~Orbit.frozen ~Orbit.geo_synchronous ~Orbit.get_orbital_frame ~Orbit.get_pass_at diff --git a/_autosummary/ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.rst b/_autosummary/ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.rst index 66ffaa6e5..1cd69ca46 100644 --- a/_autosummary/ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.rst +++ b/_autosummary/ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.rst @@ -25,6 +25,7 @@ ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean ~BrouwerLyddaneMean.eccentric_anomaly_from_mean_anomaly ~BrouwerLyddaneMean.eccentric_anomaly_from_true_anomaly ~BrouwerLyddaneMean.from_SI_vector + ~BrouwerLyddaneMean.frozen_orbit ~BrouwerLyddaneMean.get_SI_vector ~BrouwerLyddaneMean.get_angular_momentum ~BrouwerLyddaneMean.get_aop diff --git a/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.rst b/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.rst index 352d093cc..bd55e0f8b 100644 --- a/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.rst +++ b/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.rst @@ -26,6 +26,7 @@ ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanL ~BrouwerLyddaneMeanLong.eccentric_anomaly_from_mean_anomaly ~BrouwerLyddaneMeanLong.eccentric_anomaly_from_true_anomaly ~BrouwerLyddaneMeanLong.from_SI_vector + ~BrouwerLyddaneMeanLong.frozen_orbit ~BrouwerLyddaneMeanLong.get_SI_vector ~BrouwerLyddaneMeanLong.get_angular_momentum ~BrouwerLyddaneMeanLong.get_aop diff --git a/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.rst b/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.rst index 9acdb86d8..6c3b42753 100644 --- a/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.rst +++ b/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.rst @@ -26,6 +26,7 @@ ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanS ~BrouwerLyddaneMeanShort.eccentric_anomaly_from_mean_anomaly ~BrouwerLyddaneMeanShort.eccentric_anomaly_from_true_anomaly ~BrouwerLyddaneMeanShort.from_SI_vector + ~BrouwerLyddaneMeanShort.frozen_orbit ~BrouwerLyddaneMeanShort.get_SI_vector ~BrouwerLyddaneMeanShort.get_angular_momentum ~BrouwerLyddaneMeanShort.get_aop diff --git a/_autosummary/ostk.astrodynamics.trajectory.orbit.model.kepler.COE.rst b/_autosummary/ostk.astrodynamics.trajectory.orbit.model.kepler.COE.rst index 825288cbf..f55268fc6 100644 --- a/_autosummary/ostk.astrodynamics.trajectory.orbit.model.kepler.COE.rst +++ b/_autosummary/ostk.astrodynamics.trajectory.orbit.model.kepler.COE.rst @@ -25,6 +25,7 @@ ostk.astrodynamics.trajectory.orbit.model.kepler.COE ~COE.eccentric_anomaly_from_mean_anomaly ~COE.eccentric_anomaly_from_true_anomaly ~COE.from_SI_vector + ~COE.frozen_orbit ~COE.get_SI_vector ~COE.get_angular_momentum ~COE.get_aop diff --git a/_build/html/.doctrees/_autosummary/ostk.astrodynamics.trajectory.Orbit.doctree b/_build/html/.doctrees/_autosummary/ostk.astrodynamics.trajectory.Orbit.doctree index fa4e66ae5..990eae3eb 100644 Binary files a/_build/html/.doctrees/_autosummary/ostk.astrodynamics.trajectory.Orbit.doctree and 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b/_build/html/.doctrees/environment.pickle differ diff --git a/_build/html/_autosummary/ostk.astrodynamics.Dynamics.html b/_build/html/_autosummary/ostk.astrodynamics.Dynamics.html index 922eb2785..3d96f6de6 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 01675f2ca..3dd9e0151 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.conjunction.message.ccsds.CDM.html b/_build/html/_autosummary/ostk.astrodynamics.conjunction.message.ccsds.CDM.html index 7567877aa..b1a6e91c9 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(
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.]]),
)

Bases: pybind11_object

Conjunction Data Message data.

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

Constructor.

Parameters:

  • 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(
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.]]),
)

Bases: pybind11_object

Conjunction Data Message data.

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

Constructor.

Parameters:

  • 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.dynamics.AtmosphericDrag.html b/_build/html/_autosummary/ostk.astrodynamics.dynamics.AtmosphericDrag.html index b521674ac..63b79f640 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 4e4905464..5d8433e46 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 3087bff95..bd46ad79a 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 8b97287c1..216b6dbe6 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 1264b37a6..e9e1b1de7 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 8251fe8dd..62afbfe5c 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.flight.Maneuver.html b/_build/html/_autosummary/ostk.astrodynamics.flight.Maneuver.html index 6c88acd14..e7a8ab691 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 60db401c2..f3acd360f 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

access_model

Access the profile model.

align_and_constrain

Generate a function that provides a quaternion that aligns to the alignment_target and constrains to the clocking_target for a given state.

custom_pointing

Overloaded function.

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.

class Axis(self: ostk.astrodynamics.flight.Profile.Axis, value: int)

Bases: pybind11_object

The axis of the profile.

Members:

X : X axis

Y : Y axis

Z : Z axis

property name
class CustomTarget(
self: ostk.astrodynamics.flight.Profile.CustomTarget,
orientation_generator: Callable[[ostk.astrodynamics.trajectory.State], numpy.ndarray[numpy.float64[3, 1]]],
axis: ostk.astrodynamics.flight.Profile.Axis,
anti_direction: bool = False,
)

Bases: Target

The custom target.

Constructor.

Parameters:

  • orientation_generator (Callable[np.ndarray, State]]) -- The orientation generator, accepts a state and returns a size 3 array of directions.

  • axis (Profile.Axis) -- The axis.

  • anti_direction (bool) -- True if the direction is flipped, False otherwise. Defaults to False.

property anti_direction

True if the direction is flipped, False otherwise.

property axis

The axis of the target.

property orientation_generator

The orientation generator of the target

property type

The type of the target.

class OrientationProfileTarget(
self: ostk.astrodynamics.flight.Profile.OrientationProfileTarget,
orientation_profile: list[tuple[ostk.physics.time.Instant, numpy.ndarray[numpy.float64[3, 1]]]],
axis: ostk.astrodynamics.flight.Profile.Axis,
anti_direction: bool = False,
)

Bases: Target

The alignment profile target.

Constructor.

Parameters:

  • orientation_profile (list[Tuple[Instant, Vector3d]]) -- The orientation profile.

  • axis (Profile.Axis) -- The axis.

  • anti_direction (bool) -- True if the direction is flipped, False otherwise. Defaults to False.

property anti_direction

True if the direction is flipped, False otherwise.

property axis

The axis of the target.

property orientation_profile

The orientation profile of the target

property type

The type of the target.

class Target(
self: ostk.astrodynamics.flight.Profile.Target,
type: ostk.astrodynamics.flight.Profile.TargetType,
axis: ostk.astrodynamics.flight.Profile.Axis,
anti_direction: bool = False,
)

Bases: pybind11_object

The target of the profile.

Constructor.

Parameters:

  • type (Profile.TargetType) -- The target type.

  • axis (Profile.Axis) -- The axis.

  • anti_direction (bool) -- True if the direction is flipped, False otherwise. Defaults to False.

property anti_direction

True if the direction is flipped, False otherwise.

property axis

The axis of the target.

property type

The type of the target.

class TargetType(self: ostk.astrodynamics.flight.Profile.TargetType, value: int)

Bases: pybind11_object

The target type of the profile.

Members:

GeocentricNadir : Geocentric nadir

GeodeticNadir : Geodetic nadir

Trajectory : Trajectory

Sun : Sun

Moon : Moon

VelocityECI : Velocity in ECI

VelocityECEF : Velocity in ECEF

OrbitalMomentum : Orbital momentum

OrientationProfile : Orientation profile

property name
class TrajectoryTarget(
self: ostk.astrodynamics.flight.Profile.TrajectoryTarget,
trajectory: ostk.astrodynamics.Trajectory,
axis: ostk.astrodynamics.flight.Profile.Axis,
anti_direction: bool = False,
)

Bases: Target

The trajectory target.

Constructor.

Parameters:

  • trajectory (Trajectory) -- The trajectory, required only if the target type is Trajectory.

  • axis (Profile.Axis) -- The axis.

  • anti_direction (bool) -- True if the direction is flipped, False otherwise. Defaults to False.

property anti_direction

True if the direction is flipped, False otherwise.

property axis

The axis of the target.

property trajectory

The trajectory of the target. Required only if the target type is Trajectory.

property type

The type of the target.

access_model(
self: ostk.astrodynamics.flight.Profile,
) → ostk::astrodynamics::flight::profile::Model

Access the profile model.

Returns:

The profile model.

Return type:

Model

static align_and_constrain(
alignment_target: ostk.astrodynamics.flight.Profile.Target,
clocking_target: ostk.astrodynamics.flight.Profile.Target,
angular_offset: ostk.physics.unit.Angle = Angle.Zero(),
) → Callable[[ostk.astrodynamics.trajectory.State], ostk.mathematics.geometry.d3.transformation.rotation.Quaternion]

Generate a function that provides a quaternion that aligns to the alignment_target and constrains to the clocking_target for a given state.

Parameters:
Returns:

The custom orientation.

Return type:

callable[Quaternion, State]

static custom_pointing(*args, **kwargs)

Overloaded function.

  1. custom_pointing(orbit: ostk.astrodynamics.trajectory.Orbit, orientation_generator: Callable[[ostk.astrodynamics.trajectory.State], ostk.mathematics.geometry.d3.transformation.rotation.Quaternion]) -> ostk.astrodynamics.flight.Profile

    Create a custom pointing profile.

    Args:

    orbit (Orbit): The orbit. orientation_generator (callable[Quaternion, State]): The orientation generator. Typically used in conjunction with align_and_constrain.

    Returns:

    Profile: The custom pointing profile.

  2. custom_pointing(orbit: ostk.astrodynamics.trajectory.Orbit, alignment_target: ostk.astrodynamics.flight.Profile.Target, clocking_target: ostk.astrodynamics.flight.Profile.Target, angular_offset: ostk.physics.unit.Angle = Angle.Zero()) -> ostk.astrodynamics.flight.Profile

    Create a custom pointing profile.

    Args:

    orbit (Orbit): The orbit. alignment_target (Profile.Target): The alignment target. clocking_target (Profile.Target): The clocking target. angular_offset (Angle): The angular offset. Defaults to Angle.Zero().

    Returns:

    Profile: The custom pointing 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

access_model

Access the profile model.

align_and_constrain

Generate a function that provides a quaternion that aligns to the alignment_target and constrains to the clocking_target for a given state.

custom_pointing

Overloaded function.

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.

class Axis(self: ostk.astrodynamics.flight.Profile.Axis, value: int)

Bases: pybind11_object

The axis of the profile.

Members:

X : X axis

Y : Y axis

Z : Z axis

property name
class CustomTarget(
self: ostk.astrodynamics.flight.Profile.CustomTarget,
orientation_generator: Callable[[ostk.astrodynamics.trajectory.State], numpy.ndarray[numpy.float64[3, 1]]],
axis: ostk.astrodynamics.flight.Profile.Axis,
anti_direction: bool = False,
)

Bases: Target

The custom target.

Constructor.

Parameters:

  • orientation_generator (Callable[np.ndarray, State]]) -- The orientation generator, accepts a state and returns a size 3 array of directions.

  • axis (Profile.Axis) -- The axis.

  • anti_direction (bool) -- True if the direction is flipped, False otherwise. Defaults to False.

property anti_direction

True if the direction is flipped, False otherwise.

property axis

The axis of the target.

property orientation_generator

The orientation generator of the target

property type

The type of the target.

class OrientationProfileTarget(
self: ostk.astrodynamics.flight.Profile.OrientationProfileTarget,
orientation_profile: list[tuple[ostk.physics.time.Instant, numpy.ndarray[numpy.float64[3, 1]]]],
axis: ostk.astrodynamics.flight.Profile.Axis,
anti_direction: bool = False,
)

Bases: Target

The alignment profile target.

Constructor.

Parameters:

  • orientation_profile (list[Tuple[Instant, Vector3d]]) -- The orientation profile.

  • axis (Profile.Axis) -- The axis.

  • anti_direction (bool) -- True if the direction is flipped, False otherwise. Defaults to False.

property anti_direction

True if the direction is flipped, False otherwise.

property axis

The axis of the target.

property orientation_profile

The orientation profile of the target

property type

The type of the target.

class Target(
self: ostk.astrodynamics.flight.Profile.Target,
type: ostk.astrodynamics.flight.Profile.TargetType,
axis: ostk.astrodynamics.flight.Profile.Axis,
anti_direction: bool = False,
)

Bases: pybind11_object

The target of the profile.

Constructor.

Parameters:

  • type (Profile.TargetType) -- The target type.

  • axis (Profile.Axis) -- The axis.

  • anti_direction (bool) -- True if the direction is flipped, False otherwise. Defaults to False.

property anti_direction

True if the direction is flipped, False otherwise.

property axis

The axis of the target.

property type

The type of the target.

class TargetType(self: ostk.astrodynamics.flight.Profile.TargetType, value: int)

Bases: pybind11_object

The target type of the profile.

Members:

GeocentricNadir : Geocentric nadir

GeodeticNadir : Geodetic nadir

Trajectory : Trajectory

Sun : Sun

Moon : Moon

VelocityECI : Velocity in ECI

VelocityECEF : Velocity in ECEF

OrbitalMomentum : Orbital momentum

OrientationProfile : Orientation profile

property name
class TrajectoryTarget(
self: ostk.astrodynamics.flight.Profile.TrajectoryTarget,
trajectory: ostk.astrodynamics.Trajectory,
axis: ostk.astrodynamics.flight.Profile.Axis,
anti_direction: bool = False,
)

Bases: Target

The trajectory target.

Constructor.

Parameters:

  • trajectory (Trajectory) -- The trajectory, required only if the target type is Trajectory.

  • axis (Profile.Axis) -- The axis.

  • anti_direction (bool) -- True if the direction is flipped, False otherwise. Defaults to False.

property anti_direction

True if the direction is flipped, False otherwise.

property axis

The axis of the target.

property trajectory

The trajectory of the target. Required only if the target type is Trajectory.

property type

The type of the target.

access_model(
self: ostk.astrodynamics.flight.Profile,
) → ostk::astrodynamics::flight::profile::Model

Access the profile model.

Returns:

The profile model.

Return type:

Model

static align_and_constrain(
alignment_target: ostk.astrodynamics.flight.Profile.Target,
clocking_target: ostk.astrodynamics.flight.Profile.Target,
angular_offset: ostk.physics.unit.Angle = Angle.Zero(),
) → Callable[[ostk.astrodynamics.trajectory.State], ostk.mathematics.geometry.d3.transformation.rotation.Quaternion]

Generate a function that provides a quaternion that aligns to the alignment_target and constrains to the clocking_target for a given state.

Parameters:
Returns:

The custom orientation.

Return type:

callable[Quaternion, State]

static custom_pointing(*args, **kwargs)

Overloaded function.

  1. custom_pointing(orbit: ostk.astrodynamics.trajectory.Orbit, orientation_generator: Callable[[ostk.astrodynamics.trajectory.State], ostk.mathematics.geometry.d3.transformation.rotation.Quaternion]) -> ostk.astrodynamics.flight.Profile

    Create a custom pointing profile.

    Args:

    orbit (Orbit): The orbit. orientation_generator (callable[Quaternion, State]): The orientation generator. Typically used in conjunction with align_and_constrain.

    Returns:

    Profile: The custom pointing profile.

  2. custom_pointing(orbit: ostk.astrodynamics.trajectory.Orbit, alignment_target: ostk.astrodynamics.flight.Profile.Target, clocking_target: ostk.astrodynamics.flight.Profile.Target, angular_offset: ostk.physics.unit.Angle = Angle.Zero()) -> ostk.astrodynamics.flight.Profile

    Create a custom pointing profile.

    Args:

    orbit (Orbit): The orbit. alignment_target (Profile.Target): The alignment target. clocking_target (Profile.Target): The clocking target. angular_offset (Angle): The angular offset. Defaults to Angle.Zero().

    Returns:

    Profile: The custom pointing 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.profile.Model.html b/_build/html/_autosummary/ostk.astrodynamics.flight.profile.Model.html index ee8417913..fb51aa0d3 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

as_tabulated

Cast the model to a tabulated model.

as_transform

Cast the model to a transform model.

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.

is_tabulated

Check if the model is a tabulated model.

is_transform

Check if the model is a transform model.

as_tabulated(
self: ostk.astrodynamics.flight.profile.Model,
) → ostk::astrodynamics::flight::profile::model::Tabulated

Cast the model to a tabulated model.

Returns:

The tabulated model.

Return type:

Tabulated

as_transform(
self: ostk.astrodynamics.flight.profile.Model,
) → ostk::astrodynamics::flight::profile::model::Transform

Cast the model to a transform model.

Returns:

The transform model.

Return type:

Transform

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

is_tabulated(self: ostk.astrodynamics.flight.profile.Model) → bool

Check if the model is a tabulated model.

Returns:

True if the model is a tabulated model, False otherwise.

Return type:

bool

is_transform(self: ostk.astrodynamics.flight.profile.Model) → bool

Check if the model is a transform model.

Returns:

True if the model is a transform model, 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

as_tabulated

Cast the model to a tabulated model.

as_transform

Cast the model to a transform model.

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.

is_tabulated

Check if the model is a tabulated model.

is_transform

Check if the model is a transform model.

as_tabulated(
self: ostk.astrodynamics.flight.profile.Model,
) → ostk::astrodynamics::flight::profile::model::Tabulated

Cast the model to a tabulated model.

Returns:

The tabulated model.

Return type:

Tabulated

as_transform(
self: ostk.astrodynamics.flight.profile.Model,
) → ostk::astrodynamics::flight::profile::model::Transform

Cast the model to a transform model.

Returns:

The transform model.

Return type:

Transform

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

is_tabulated(self: ostk.astrodynamics.flight.profile.Model) → bool

Check if the model is a tabulated model.

Returns:

True if the model is a tabulated model, False otherwise.

Return type:

bool

is_transform(self: ostk.astrodynamics.flight.profile.Model) → bool

Check if the model is a transform model.

Returns:

True if the model is a transform model, 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 ef72693be..63ee118c6 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

as_tabulated

Cast the model to a tabulated model.

as_transform

Cast the model to a transform model.

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.

is_tabulated

Check if the model is a tabulated model.

is_transform

Check if the model is a transform model.

as_tabulated(
self: ostk.astrodynamics.flight.profile.Model,
) → ostk::astrodynamics::flight::profile::model::Tabulated

Cast the model to a tabulated model.

Returns:

The tabulated model.

Return type:

Tabulated

as_transform(
self: ostk.astrodynamics.flight.profile.Model,
) → ostk::astrodynamics::flight::profile::model::Transform

Cast the model to a transform model.

Returns:

The transform model.

Return type:

Transform

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

is_tabulated(self: ostk.astrodynamics.flight.profile.Model) → bool

Check if the model is a tabulated model.

Returns:

True if the model is a tabulated model, False otherwise.

Return type:

bool

is_transform(self: ostk.astrodynamics.flight.profile.Model) → bool

Check if the model is a transform model.

Returns:

True if the model is a transform model, 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

as_tabulated

Cast the model to a tabulated model.

as_transform

Cast the model to a transform model.

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.

is_tabulated

Check if the model is a tabulated model.

is_transform

Check if the model is a transform model.

as_tabulated(
self: ostk.astrodynamics.flight.profile.Model,
) → ostk::astrodynamics::flight::profile::model::Tabulated

Cast the model to a tabulated model.

Returns:

The tabulated model.

Return type:

Tabulated

as_transform(
self: ostk.astrodynamics.flight.profile.Model,
) → ostk::astrodynamics::flight::profile::model::Transform

Cast the model to a transform model.

Returns:

The transform model.

Return type:

Transform

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

is_tabulated(self: ostk.astrodynamics.flight.profile.Model) → bool

Check if the model is a tabulated model.

Returns:

True if the model is a tabulated model, False otherwise.

Return type:

bool

is_transform(self: ostk.astrodynamics.flight.profile.Model) → bool

Check if the model is a transform model.

Returns:

True if the model is a transform model, 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 87f2c8c84..4f73b1ebe 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

as_tabulated

Cast the model to a tabulated model.

as_transform

Cast the model to a transform model.

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.

is_tabulated

Check if the model is a tabulated model.

is_transform

Check if the model is a transform model.

nadir_pointing

Create a transform for nadir pointing.

undefined

Get an undefined transform.

as_tabulated(
self: ostk.astrodynamics.flight.profile.Model,
) → ostk::astrodynamics::flight::profile::model::Tabulated

Cast the model to a tabulated model.

Returns:

The tabulated model.

Return type:

Tabulated

as_transform(
self: ostk.astrodynamics.flight.profile.Model,
) → ostk::astrodynamics::flight::profile::model::Transform

Cast the model to a transform model.

Returns:

The transform model.

Return type:

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

is_tabulated(self: ostk.astrodynamics.flight.profile.Model) → bool

Check if the model is a tabulated model.

Returns:

True if the model is a tabulated model, False otherwise.

Return type:

bool

is_transform(self: ostk.astrodynamics.flight.profile.Model) → bool

Check if the model is a transform model.

Returns:

True if the model is a transform model, 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

as_tabulated

Cast the model to a tabulated model.

as_transform

Cast the model to a transform model.

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.

is_tabulated

Check if the model is a tabulated model.

is_transform

Check if the model is a transform model.

nadir_pointing

Create a transform for nadir pointing.

undefined

Get an undefined transform.

as_tabulated(
self: ostk.astrodynamics.flight.profile.Model,
) → ostk::astrodynamics::flight::profile::model::Tabulated

Cast the model to a tabulated model.

Returns:

The tabulated model.

Return type:

Tabulated

as_transform(
self: ostk.astrodynamics.flight.profile.Model,
) → ostk::astrodynamics::flight::profile::model::Transform

Cast the model to a transform model.

Returns:

The transform model.

Return type:

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

is_tabulated(self: ostk.astrodynamics.flight.profile.Model) → bool

Check if the model is a tabulated model.

Returns:

True if the model is a tabulated model, False otherwise.

Return type:

bool

is_transform(self: ostk.astrodynamics.flight.profile.Model) → bool

Check if the model is a transform model.

Returns:

True if the model is a transform model, 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.SatelliteSystem.html b/_build/html/_autosummary/ostk.astrodynamics.flight.system.SatelliteSystem.html index 5f27f6e14..76bc9b87e 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 b8478c7d1..35f9491a4 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 f616bf3a0..a42ffd836 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 49e10c032..8619b3343 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 13dd16d00..0bd90af5f 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.trajectory.LocalOrbitalFrameDirection.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection.html index 326d41487..5e2b161f6 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection

class LocalOrbitalFrameDirection(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection,
vector: numpy.ndarray[numpy.float64[3, 1]],
local_orbital_frame_factory: ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory,
)

Bases: pybind11_object

A local orbital frame direction.

Construct a new LocalOrbitalFrameDirection object.

Parameters:

  • vector (numpy.ndarray) -- The vector expressed in the local orbital frame.

  • local_orbital_frame_factory (LocalOrbitalFrameFactory) -- The local orbital frame factory that defines the frame.

Returns:

The new LocalOrbitalFrameDirection object.

Return type:

LocalOrbitalFrameDirection

Methods

get_local_orbital_frame_factory

Get the local orbital frame factory that defines the frame.

get_value

Get the vector expressed in the local orbital frame.

is_defined

Check if the local orbital frame direction is defined.

undefined

Get an undefined local orbital frame direction.

get_local_orbital_frame_factory(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get the local orbital frame factory that defines the frame.

Returns:

The local orbital frame factory that defines the frame.

Return type:

LocalOrbitalFrameFactory

get_value(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection,
) → numpy.ndarray[numpy.float64[3, 1]]

Get the vector expressed in the local orbital frame.

Returns:

The vector expressed in the local orbital frame.

Return type:

Vector3d

is_defined(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection,
) → bool

Check if the local orbital frame direction is defined.

Returns:

True if the local orbital frame direction is defined, False otherwise.

Return type:

bool

static undefined() → ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection

Get an undefined local orbital frame direction.

Returns:

The undefined local orbital frame direction.

Return type:

LocalOrbitalFrameDirection

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

ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection

class LocalOrbitalFrameDirection(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection,
vector: numpy.ndarray[numpy.float64[3, 1]],
local_orbital_frame_factory: ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory,
)

Bases: pybind11_object

A local orbital frame direction.

Construct a new LocalOrbitalFrameDirection object.

Parameters:

  • vector (numpy.ndarray) -- The vector expressed in the local orbital frame.

  • local_orbital_frame_factory (LocalOrbitalFrameFactory) -- The local orbital frame factory that defines the frame.

Returns:

The new LocalOrbitalFrameDirection object.

Return type:

LocalOrbitalFrameDirection

Methods

get_local_orbital_frame_factory

Get the local orbital frame factory that defines the frame.

get_value

Get the vector expressed in the local orbital frame.

is_defined

Check if the local orbital frame direction is defined.

undefined

Get an undefined local orbital frame direction.

get_local_orbital_frame_factory(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection,
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

Get the local orbital frame factory that defines the frame.

Returns:

The local orbital frame factory that defines the frame.

Return type:

LocalOrbitalFrameFactory

get_value(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection,
) → numpy.ndarray[numpy.float64[3, 1]]

Get the vector expressed in the local orbital frame.

Returns:

The vector expressed in the local orbital frame.

Return type:

Vector3d

is_defined(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection,
) → bool

Check if the local orbital frame direction is defined.

Returns:

True if the local orbital frame direction is defined, False otherwise.

Return type:

bool

static undefined() → ostk.astrodynamics.trajectory.LocalOrbitalFrameDirection

Get an undefined local orbital frame direction.

Returns:

The undefined local orbital frame direction.

Return type:

LocalOrbitalFrameDirection

\ 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 98447d80e..daf6c1391 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 Tangent-Normal-Wideband (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.

construct

Overloaded function.

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 Tangent-Normal-Wideband (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

static construct(*args, **kwargs)

Overloaded function.

  1. construct(type: ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider.Type, parent_frame: ostk.physics.coordinate.Frame) -> ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

    Construct a local orbital frame factory for the provided type.

    Args:

    type (LocalOrbitalFrameTransformProvider.Type): The type of local orbital frame transform provider. parent_frame (Frame): The parent frame.

    Returns:

    LocalOrbitalFrameFactory: The local orbital frame factory.

  2. construct(transform_generator: Callable[[ostk.physics.time.Instant, numpy.ndarray[numpy.float64[3, 1]], numpy.ndarray[numpy.float64[3, 1]]], ostk.physics.coordinate.Transform], parent_frame: ostk.physics.coordinate.Frame) -> ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

    Construct a local orbital frame factory for a custom type, using the provided transform generator.

    Args:

    transform_generator (callable[[Instant, np.array, np.array], Transform]): The transform generator. parent_frame (Frame): The parent frame.

    Returns:

    LocalOrbitalFrameFactory: The local orbital frame factory.

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 Tangent-Normal-Wideband (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.

construct

Overloaded function.

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 Tangent-Normal-Wideband (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

static construct(*args, **kwargs)

Overloaded function.

  1. construct(type: ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider.Type, parent_frame: ostk.physics.coordinate.Frame) -> ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

    Construct a local orbital frame factory for the provided type.

    Args:

    type (LocalOrbitalFrameTransformProvider.Type): The type of local orbital frame transform provider. parent_frame (Frame): The parent frame.

    Returns:

    LocalOrbitalFrameFactory: The local orbital frame factory.

  2. construct(transform_generator: Callable[[ostk.physics.time.Instant, numpy.ndarray[numpy.float64[3, 1]], numpy.ndarray[numpy.float64[3, 1]]], ostk.physics.coordinate.Transform], parent_frame: ostk.physics.coordinate.Frame) -> ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory

    Construct a local orbital frame factory for a custom type, using the provided transform generator.

    Args:

    transform_generator (callable[[Instant, np.array, np.array], Transform]): The transform generator. parent_frame (Frame): The parent frame.

    Returns:

    LocalOrbitalFrameFactory: The local orbital frame factory.

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 40c620154..bb36f5ce4 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(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider,
transform: ostk.physics.coordinate.Transform,
)

Bases: pybind11_object

Local orbital frame transform provider, frame provider. Generates a specific transform based on instant, position, velocity and a LOF type.

Constructs a local orbital frame transform provider.

Parameters:

transform (Transform) -- The transform.

Returns:

The provider.

Return type:

LocalOrbitalFrameTransformProvider

Methods

construct

Constructs a local orbital frame transform provider for the provided type.

get_transform_at

Returns the transform at a given instant.

get_transform_generator

Returns the transform generator function for a given type.

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 : Tangent-Normal-Wideband

VNC : Velocity-Normal-Conormal

property name
static construct(
type: ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider.Type,
instant: ostk.physics.time.Instant,
position: numpy.ndarray[numpy.float64[3, 1]],
velocity: numpy.ndarray[numpy.float64[3, 1]],
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider

Constructs a local orbital frame transform provider for the provided type.

Parameters:

  • type (LocalOrbitalFrameTransformProvider.Type) -- The local orbital frame provider type.

  • instant (Instant) -- The instant.

  • position (Vector3d) -- The position vector.

  • velocity (Vector3d) -- The velocity vector.

Returns:

The provider.

Return type:

LocalOrbitalFrameTransformProvider

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

static get_transform_generator(
type: ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider.Type,
) → Callable[[ostk.physics.time.Instant, numpy.ndarray[numpy.float64[3, 1]], numpy.ndarray[numpy.float64[3, 1]]], ostk.physics.coordinate.Transform]

Returns the transform generator function for a given type.

Parameters:

type (LocalOrbitalFrameTransformProvider.Type) -- The local orbital frame provider type.

Returns:

The transform generator function.

Return type:

callable[[Instant, np.array, np.array], 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(
self: ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider,
transform: ostk.physics.coordinate.Transform,
)

Bases: pybind11_object

Local orbital frame transform provider, frame provider. Generates a specific transform based on instant, position, velocity and a LOF type.

Constructs a local orbital frame transform provider.

Parameters:

transform (Transform) -- The transform.

Returns:

The provider.

Return type:

LocalOrbitalFrameTransformProvider

Methods

construct

Constructs a local orbital frame transform provider for the provided type.

get_transform_at

Returns the transform at a given instant.

get_transform_generator

Returns the transform generator function for a given type.

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 : Tangent-Normal-Wideband

VNC : Velocity-Normal-Conormal

property name
static construct(
type: ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider.Type,
instant: ostk.physics.time.Instant,
position: numpy.ndarray[numpy.float64[3, 1]],
velocity: numpy.ndarray[numpy.float64[3, 1]],
) → ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider

Constructs a local orbital frame transform provider for the provided type.

Parameters:

  • type (LocalOrbitalFrameTransformProvider.Type) -- The local orbital frame provider type.

  • instant (Instant) -- The instant.

  • position (Vector3d) -- The position vector.

  • velocity (Vector3d) -- The velocity vector.

Returns:

The provider.

Return type:

LocalOrbitalFrameTransformProvider

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

static get_transform_generator(
type: ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider.Type,
) → Callable[[ostk.physics.time.Instant, numpy.ndarray[numpy.float64[3, 1]], numpy.ndarray[numpy.float64[3, 1]]], ostk.physics.coordinate.Transform]

Returns the transform generator function for a given type.

Parameters:

type (LocalOrbitalFrameTransformProvider.Type) -- The local orbital frame provider type.

Returns:

The transform generator function.

Return type:

callable[[Instant, np.array, np.array], 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.Orbit.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.Orbit.html index 66e327178..7f96a04d1 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.

compute_passes_with_model

Compute passes with the given model for the provided interval.

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_passes_within_interval

Get the passes within a given interval.

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.

ground_strip

Overloaded function.

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 : Tangent-Normal-Wideband

VNC : Velocity-Normal-Conormal

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 compute_passes_with_model(
model: ostk::astrodynamics::trajectory::orbit::Model,
start_instant: ostk.physics.time.Instant,
end_instant: ostk.physics.time.Instant,
initial_revolution_number: ostk.core.type.Integer,
) → list[ostk::astrodynamics::trajectory::orbit::Pass]

Compute passes with the given model for the provided interval.

Parameters:

  • model (orbit.Model) -- The model.

  • start_instant (Instant) -- The start instant.

  • end_instant (Instant) -- The end instant.

  • initial_revolution_number (int) -- The initial revolution number.

Returns:

List of passes.

Return type:

list[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,
step_duration: ostk.physics.time.Duration = Duration.minutes(10.0),
) → ostk::astrodynamics::trajectory::orbit::Pass

Get the pass with a given revolution number.

Parameters:

  • revolution_number (int) -- The revolution number.

  • step_duration (Duration) -- The initial step duration used for the pass computation algorithm.

Returns:

The pass.

Return type:

Pass

get_passes_within_interval(
self: ostk.astrodynamics.trajectory.Orbit,
interval: ostk.physics.time.Interval,
) → list[ostk::astrodynamics::trajectory::orbit::Pass]

Get the passes within a given interval.

Parameters:

interval (Interval) -- The interval.

Returns:

The passes.

Return type:

list[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]

static ground_strip(*args, **kwargs)

Overloaded function.

  1. ground_strip(start_lla: ostk.physics.coordinate.spherical.LLA, end_lla: ostk.physics.coordinate.spherical.LLA, ground_speed: ostk.physics.unit.Derived, start_instant: ostk.physics.time.Instant, celestial_object: ostk.physics.environment.object.Celestial = Earth.WGS84(), step_size: ostk.physics.time.Duration = Duration.Seconds(1.0)) -> ostk.astrodynamics.Trajectory

    Create a Trajectory object representing a ground strip. Computes the duration as the geodetic distance / ground speed. Instants are generated at a 1 second interval.

    Args:

    start_lla (LLA): The start LLA. end_lla (LLA): The end LLA. ground_speed (Derived): The ground speed. start_instant (Instant): The start instant. celestial_object (Celestial): The celestial object. Defaults to Earth.WGS84(). step_size (Duration): The step size. Defaults to 1 second.

    Returns:

    Trajectory: The Trajectory object representing the ground strip.

  2. ground_strip(start_lla: ostk.physics.coordinate.spherical.LLA, end_lla: ostk.physics.coordinate.spherical.LLA, instants: list[ostk.physics.time.Instant], celestial_object: ostk.physics.environment.object.Celestial = Earth.WGS84()) -> ostk.astrodynamics.Trajectory

    Create a Trajectory object representing a ground strip. This method computes the duration as the geodetic distance / ground speed.

    Args:

    start_lla (LLA): The start LLA. end_lla (LLA): The end LLA. instants (list[Instant]): The instants. celestial_object (Celestial): The celestial object. Defaults to Earth.WGS84().

    Returns:

    Trajectory: The Trajectory object representing the ground strip.

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. Must be in the ITRF frame.

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.

compute_passes_with_model

Compute passes with the given model for the provided interval.

equatorial

Create an equatorial Orbit object.

frozen

Create a frozen 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_passes_within_interval

Get the passes within a given interval.

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.

ground_strip

Overloaded function.

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 : Tangent-Normal-Wideband

VNC : Velocity-Normal-Conormal

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 (wrt. equatorial radius).

  • 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 (wrt. equatorial radius).

  • 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 compute_passes_with_model(
model: ostk::astrodynamics::trajectory::orbit::Model,
start_instant: ostk.physics.time.Instant,
end_instant: ostk.physics.time.Instant,
initial_revolution_number: ostk.core.type.Integer,
) → list[ostk::astrodynamics::trajectory::orbit::Pass]

Compute passes with the given model for the provided interval.

Parameters:

  • model (orbit.Model) -- The model.

  • start_instant (Instant) -- The start instant.

  • end_instant (Instant) -- The end instant.

  • initial_revolution_number (int) -- The initial revolution number.

Returns:

List of passes.

Return type:

list[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 (wrt. equatorial radius).

  • periapsis_altitude (Length) -- The periapsis altitude (wrt. equatorial radius).

  • celestial_object (Celestial) -- The celestial object.

Returns:

The equatorial Orbit object.

Return type:

Orbit

static frozen(
epoch: ostk.physics.time.Instant,
altitude: ostk.physics.unit.Length,
celestial_object: ostk.physics.environment.object.Celestial,
eccentricity: ostk.core.type.Real = Real.undefined(),
inclination: ostk.physics.unit.Angle = Angle.undefined(),
raan: ostk.physics.unit.Angle = Angle.degrees(0.0),
aop: ostk.physics.unit.Angle = Angle.undefined(),
true_anomaly: ostk.physics.unit.Angle = Angle.degrees(0.0),
) → ostk.astrodynamics.trajectory.Orbit

Create a frozen Orbit object.

The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.

At a minimum, an epoch, altitude, and celestial body with a defined J2 and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.

Additionally, the following combinations of inputs are supported: - AoP (inclination set to critical value, eccentricity derived) - AoP and eccentricity (inclination derived) - AoP and inclination, but at least one of them must be a critical value (eccentricity derived) - Inclination (AoP set to critical value, eccentricity derived) - Eccentricity (AoP set to critical value, inclination derived)

Note that inclination and eccentricity cannot both be provided.

RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting Orbit as they do not impact the frozen orbit condition.

Parameters:

  • epoch (Instant) -- The epoch.

  • altitude (Length) -- The altitude (wrt. equatorial radius).

  • celestial_object (Celestial) -- The celestial object.

  • 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.

Returns:

The frozen 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,
step_duration: ostk.physics.time.Duration = Duration.minutes(10.0),
) → ostk::astrodynamics::trajectory::orbit::Pass

Get the pass with a given revolution number.

Parameters:

  • revolution_number (int) -- The revolution number.

  • step_duration (Duration) -- The initial step duration used for the pass computation algorithm.

Returns:

The pass.

Return type:

Pass

get_passes_within_interval(
self: ostk.astrodynamics.trajectory.Orbit,
interval: ostk.physics.time.Interval,
) → list[ostk::astrodynamics::trajectory::orbit::Pass]

Get the passes within a given interval.

Parameters:

interval (Interval) -- The interval.

Returns:

The passes.

Return type:

list[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]

static ground_strip(*args, **kwargs)

Overloaded function.

  1. ground_strip(start_lla: ostk.physics.coordinate.spherical.LLA, end_lla: ostk.physics.coordinate.spherical.LLA, ground_speed: ostk.physics.unit.Derived, start_instant: ostk.physics.time.Instant, celestial_object: ostk.physics.environment.object.Celestial = Earth.WGS84(), step_size: ostk.physics.time.Duration = Duration.Seconds(1.0)) -> ostk.astrodynamics.Trajectory

    Create a Trajectory object representing a ground strip. Computes the duration as the geodetic distance / ground speed. Instants are generated at a 1 second interval.

    Args:

    start_lla (LLA): The start LLA. end_lla (LLA): The end LLA. ground_speed (Derived): The ground speed. start_instant (Instant): The start instant. celestial_object (Celestial): The celestial object. Defaults to Earth.WGS84(). step_size (Duration): The step size. Defaults to 1 second.

    Returns:

    Trajectory: The Trajectory object representing the ground strip.

  2. ground_strip(start_lla: ostk.physics.coordinate.spherical.LLA, end_lla: ostk.physics.coordinate.spherical.LLA, instants: list[ostk.physics.time.Instant], celestial_object: ostk.physics.environment.object.Celestial = Earth.WGS84()) -> ostk.astrodynamics.Trajectory

    Create a Trajectory object representing a ground strip. This method computes the duration as the geodetic distance / ground speed.

    Args:

    start_lla (LLA): The start LLA. end_lla (LLA): The end LLA. instants (list[Instant]): The instants. celestial_object (Celestial): The celestial object. Defaults to Earth.WGS84().

    Returns:

    Trajectory: The Trajectory object representing the ground strip.

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. Must be in the ITRF frame.

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 (wrt. equatorial radius).

  • 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.Segment.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.Segment.html index c365441c1..82fb5cef7 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_interval(
self: ostk.astrodynamics.trajectory.Segment.Solution,
) → ostk.physics.time.Interval

Get the time interval of the solution.

Returns:

The interval.

Return type:

Interval

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_interval(
self: ostk.astrodynamics.trajectory.Segment.Solution,
) → ostk.physics.time.Interval

Get the time interval of the solution.

Returns:

The interval.

Return type:

Interval

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.State.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.State.html index 3f1bcd95a..91b5544e0 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.

from_dict

Create a State from a dictionary.

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

Transform the state to the provided 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

static from_dict(data: dict) → State

Create a State from a dictionary.

Note: Implicit assumption that ECEF = ITRF, and ECI = GCRF.

The dictionary must contain the following: - 'timestamp': The timestamp of the state. - 'r_ITRF_x'/'rx'/'rx_eci'/'rx_ecef': The x-coordinate of the position. - 'r_ITRF_y'/'ry'/'ry_eci'/'ry_ecef': The y-coordinate of the position. - 'r_ITRF_z'/'rz'/'rz_eci'/'rz_ecef': The z-coordinate of the position. - 'v_ITRF_x'/'vx'/'vx_eci'/'vx_ecef': The x-coordinate of the velocity. - 'v_ITRF_y'/'vy'/'vy_eci'/'vy_ecef': The y-coordinate of the velocity. - 'v_ITRF_z'/'vz'/'vz_eci'/'vz_ecef': The z-coordinate of the velocity. - 'frame': The frame of the state. Required if 'rx', 'ry', 'rz', 'vx', 'vy', 'vz' are provided. - 'q_B_ECI_x': The x-coordinate of the quaternion. Optional. - 'q_B_ECI_y': The y-coordinate of the quaternion. Optional. - 'q_B_ECI_z': The z-coordinate of the quaternion. Optional. - 'q_B_ECI_s': The s-coordinate of the quaternion. Optional. - 'w_B_ECI_in_B_x': The x-coordinate of the angular velocity. Optional. - 'w_B_ECI_in_B_y': The y-coordinate of the angular velocity. Optional. - 'w_B_ECI_in_B_z': The z-coordinate of the angular velocity. Optional. - 'drag_coefficient'/'cd': The drag coefficient. Optional. - 'cross_sectional_area'/'surface_area': The cross-sectional area. Optional. - 'mass': The mass. Optional.

Parameters:

data (dict) -- The dictionary.

Returns:

The State.

Return type:

State

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

Transform the state to the provided reference frame.

Parameters:

frame (Frame) -- The reference frame to transform to.

Returns:

The transformed state.

Return type:

State

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.

from_dict

Create a State from a dictionary.

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

Transform the state to the provided 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

static from_dict(data: dict) → State

Create a State from a dictionary.

Note: Implicit assumption that ECEF = ITRF, and ECI = GCRF.

The dictionary must contain the following: - 'timestamp': The timestamp of the state. - 'r_ITRF_x'/'rx'/'rx_eci'/'rx_ecef': The x-coordinate of the position. - 'r_ITRF_y'/'ry'/'ry_eci'/'ry_ecef': The y-coordinate of the position. - 'r_ITRF_z'/'rz'/'rz_eci'/'rz_ecef': The z-coordinate of the position. - 'v_ITRF_x'/'vx'/'vx_eci'/'vx_ecef': The x-coordinate of the velocity. - 'v_ITRF_y'/'vy'/'vy_eci'/'vy_ecef': The y-coordinate of the velocity. - 'v_ITRF_z'/'vz'/'vz_eci'/'vz_ecef': The z-coordinate of the velocity. - 'frame': The frame of the state. Required if 'rx', 'ry', 'rz', 'vx', 'vy', 'vz' are provided. - 'q_B_ECI_x': The x-coordinate of the quaternion. Optional. - 'q_B_ECI_y': The y-coordinate of the quaternion. Optional. - 'q_B_ECI_z': The z-coordinate of the quaternion. Optional. - 'q_B_ECI_s': The s-coordinate of the quaternion. Optional. - 'w_B_ECI_in_B_x': The x-coordinate of the angular velocity. Optional. - 'w_B_ECI_in_B_y': The y-coordinate of the angular velocity. Optional. - 'w_B_ECI_in_B_z': The z-coordinate of the angular velocity. Optional. - 'drag_coefficient'/'cd': The drag coefficient. Optional. - 'cross_sectional_area'/'surface_area': The cross-sectional area. Optional. - 'mass': The mass. Optional.

Parameters:

data (dict) -- The dictionary.

Returns:

The State.

Return type:

State

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

Transform the state to the provided reference frame.

Parameters:

frame (Frame) -- The reference frame to transform to.

Returns:

The transformed state.

Return type:

State

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 a467433ab..939deef31 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.model.BrouwerLyddaneMean.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.html index 7fde778ae..f5f0fb014 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_ltan

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

compute_mean_ltan

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

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_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Local Time of the Ascending Node (LTAN) in hours.

Return type:

float

static compute_mean_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Mean Local Time of the Ascending Node (MLTAN) in hours.

Return type:

float

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_ltan

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

compute_mean_ltan

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

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.

frozen_orbit

Overloaded function.

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_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Local Time of the Ascending Node (LTAN) in hours.

Return type:

float

static compute_mean_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Mean Local Time of the Ascending Node (MLTAN) in hours.

Return type:

float

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

static frozen_orbit(*args, **kwargs)

Overloaded function.

  1. frozen_orbit(semi_major_axis: ostk.physics.unit.Length, celestial_object: ostk.physics.environment.object.Celestial, eccentricity: ostk.core.type.Real = Real.undefined(), inclination: ostk.physics.unit.Angle = Angle.undefined(), raan: ostk.physics.unit.Angle = Angle.degrees(0.0), aop: ostk.physics.unit.Angle = Angle.undefined(), true_anomaly: ostk.physics.unit.Angle = Angle.degrees(0.0)) -> ostk.astrodynamics.trajectory.orbit.model.kepler.COE

    Build a COE model of a frozen orbit.

    The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.

    At a minimum, a semi-major axis and shared pointer to a central celestial body with a defined J2 and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.

    Additionally, the following combinations of inputs are supported: - AoP (inclination set to critical value, eccentricity derived) - AoP and eccentricity (inclination derived) - AoP and inclination, but at least one of them must be a critical value (eccentricity derived) - Inclination (AoP set to critical value, eccentricity derived) - Eccentricity (AoP set to critical value, inclination derived)

    Note that inclination and eccentricity cannot both be provided.

    RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting COE as they do not impact the frozen orbit condition.

    Args:

    semi_major_axis (Length): The semi-major axis. celestial_object (Celestial): The celestial object. 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.

    Returns:

    COE: The COE model.

  2. frozen_orbit(semi_major_axis: ostk.physics.unit.Length, equatorial_radius: ostk.physics.unit.Length, j2: ostk.core.type.Real, j3: ostk.core.type.Real, eccentricity: ostk.core.type.Real = Real.undefined(), inclination: ostk.physics.unit.Angle = Angle.undefined(), raan: ostk.physics.unit.Angle = Angle.degrees(0.0), aop: ostk.physics.unit.Angle = Angle.undefined(), true_anomaly: ostk.physics.unit.Angle = Angle.degrees(0.0)) -> ostk.astrodynamics.trajectory.orbit.model.kepler.COE

    Build a COE model of a frozen orbit.

    The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.

    At a minimum, a semi-major axis, equatorial radius, J2, and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.

    Additionally, the following combinations of inputs are supported: - AoP (inclination set to critical value, eccentricity derived) - AoP and eccentricity (inclination derived) - AoP and inclination, but at least one of them must be a critical value (eccentricity derived) - Inclination (AoP set to critical value, eccentricity derived) - Eccentricity (AoP set to critical value, inclination derived)

    Note that inclination and eccentricity cannot both be provided.

    RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting COE as they do not impact the frozen orbit condition.

    Args:

    semi_major_axis (Length): The semi-major axis. equatorial_radius (Length): The equatorial radius. j2 (float): The second zonal harmonic coefficient. j3 (float): The third zonal harmonic coefficient. 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.

    Returns:

    COE: The COE model.

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.brouwerLyddaneMean.BrouwerLyddaneMeanLong.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.html index 1311bfef3..117c40234 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_ltan

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

compute_mean_ltan

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

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_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Local Time of the Ascending Node (LTAN) in hours.

Return type:

float

static compute_mean_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Mean Local Time of the Ascending Node (MLTAN) in hours.

Return type:

float

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_ltan

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

compute_mean_ltan

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

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.

frozen_orbit

Overloaded function.

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_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Local Time of the Ascending Node (LTAN) in hours.

Return type:

float

static compute_mean_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Mean Local Time of the Ascending Node (MLTAN) in hours.

Return type:

float

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

static frozen_orbit(*args, **kwargs)

Overloaded function.

  1. frozen_orbit(semi_major_axis: ostk.physics.unit.Length, celestial_object: ostk.physics.environment.object.Celestial, eccentricity: ostk.core.type.Real = Real.undefined(), inclination: ostk.physics.unit.Angle = Angle.undefined(), raan: ostk.physics.unit.Angle = Angle.degrees(0.0), aop: ostk.physics.unit.Angle = Angle.undefined(), true_anomaly: ostk.physics.unit.Angle = Angle.degrees(0.0)) -> ostk.astrodynamics.trajectory.orbit.model.kepler.COE

    Build a COE model of a frozen orbit.

    The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.

    At a minimum, a semi-major axis and shared pointer to a central celestial body with a defined J2 and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.

    Additionally, the following combinations of inputs are supported: - AoP (inclination set to critical value, eccentricity derived) - AoP and eccentricity (inclination derived) - AoP and inclination, but at least one of them must be a critical value (eccentricity derived) - Inclination (AoP set to critical value, eccentricity derived) - Eccentricity (AoP set to critical value, inclination derived)

    Note that inclination and eccentricity cannot both be provided.

    RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting COE as they do not impact the frozen orbit condition.

    Args:

    semi_major_axis (Length): The semi-major axis. celestial_object (Celestial): The celestial object. 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.

    Returns:

    COE: The COE model.

  2. frozen_orbit(semi_major_axis: ostk.physics.unit.Length, equatorial_radius: ostk.physics.unit.Length, j2: ostk.core.type.Real, j3: ostk.core.type.Real, eccentricity: ostk.core.type.Real = Real.undefined(), inclination: ostk.physics.unit.Angle = Angle.undefined(), raan: ostk.physics.unit.Angle = Angle.degrees(0.0), aop: ostk.physics.unit.Angle = Angle.undefined(), true_anomaly: ostk.physics.unit.Angle = Angle.degrees(0.0)) -> ostk.astrodynamics.trajectory.orbit.model.kepler.COE

    Build a COE model of a frozen orbit.

    The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.

    At a minimum, a semi-major axis, equatorial radius, J2, and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.

    Additionally, the following combinations of inputs are supported: - AoP (inclination set to critical value, eccentricity derived) - AoP and eccentricity (inclination derived) - AoP and inclination, but at least one of them must be a critical value (eccentricity derived) - Inclination (AoP set to critical value, eccentricity derived) - Eccentricity (AoP set to critical value, inclination derived)

    Note that inclination and eccentricity cannot both be provided.

    RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting COE as they do not impact the frozen orbit condition.

    Args:

    semi_major_axis (Length): The semi-major axis. equatorial_radius (Length): The equatorial radius. j2 (float): The second zonal harmonic coefficient. j3 (float): The third zonal harmonic coefficient. 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.

    Returns:

    COE: The COE model.

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

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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_ltan

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

compute_mean_ltan

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

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_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Local Time of the Ascending Node (LTAN) in hours.

Return type:

float

static compute_mean_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Mean Local Time of the Ascending Node (MLTAN) in hours.

Return type:

float

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_ltan

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

compute_mean_ltan

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

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.

frozen_orbit

Overloaded function.

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_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Local Time of the Ascending Node (LTAN) in hours.

Return type:

float

static compute_mean_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Mean Local Time of the Ascending Node (MLTAN) in hours.

Return type:

float

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

static frozen_orbit(*args, **kwargs)

Overloaded function.

  1. frozen_orbit(semi_major_axis: ostk.physics.unit.Length, celestial_object: ostk.physics.environment.object.Celestial, eccentricity: ostk.core.type.Real = Real.undefined(), inclination: ostk.physics.unit.Angle = Angle.undefined(), raan: ostk.physics.unit.Angle = Angle.degrees(0.0), aop: ostk.physics.unit.Angle = Angle.undefined(), true_anomaly: ostk.physics.unit.Angle = Angle.degrees(0.0)) -> ostk.astrodynamics.trajectory.orbit.model.kepler.COE

    Build a COE model of a frozen orbit.

    The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.

    At a minimum, a semi-major axis and shared pointer to a central celestial body with a defined J2 and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.

    Additionally, the following combinations of inputs are supported: - AoP (inclination set to critical value, eccentricity derived) - AoP and eccentricity (inclination derived) - AoP and inclination, but at least one of them must be a critical value (eccentricity derived) - Inclination (AoP set to critical value, eccentricity derived) - Eccentricity (AoP set to critical value, inclination derived)

    Note that inclination and eccentricity cannot both be provided.

    RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting COE as they do not impact the frozen orbit condition.

    Args:

    semi_major_axis (Length): The semi-major axis. celestial_object (Celestial): The celestial object. 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.

    Returns:

    COE: The COE model.

  2. frozen_orbit(semi_major_axis: ostk.physics.unit.Length, equatorial_radius: ostk.physics.unit.Length, j2: ostk.core.type.Real, j3: ostk.core.type.Real, eccentricity: ostk.core.type.Real = Real.undefined(), inclination: ostk.physics.unit.Angle = Angle.undefined(), raan: ostk.physics.unit.Angle = Angle.degrees(0.0), aop: ostk.physics.unit.Angle = Angle.undefined(), true_anomaly: ostk.physics.unit.Angle = Angle.degrees(0.0)) -> ostk.astrodynamics.trajectory.orbit.model.kepler.COE

    Build a COE model of a frozen orbit.

    The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.

    At a minimum, a semi-major axis, equatorial radius, J2, and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.

    Additionally, the following combinations of inputs are supported: - AoP (inclination set to critical value, eccentricity derived) - AoP and eccentricity (inclination derived) - AoP and inclination, but at least one of them must be a critical value (eccentricity derived) - Inclination (AoP set to critical value, eccentricity derived) - Eccentricity (AoP set to critical value, inclination derived)

    Note that inclination and eccentricity cannot both be provided.

    RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting COE as they do not impact the frozen orbit condition.

    Args:

    semi_major_axis (Length): The semi-major axis. equatorial_radius (Length): The equatorial radius. j2 (float): The second zonal harmonic coefficient. j3 (float): The third zonal harmonic coefficient. 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.

    Returns:

    COE: The COE model.

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 diff --git a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.kepler.COE.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.kepler.COE.html index b777f7a21..0134ea193 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.kepler.COE.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.orbit.model.kepler.COE.html @@ -1 +1 @@ - 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_ltan

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

compute_mean_ltan

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

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_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Local Time of the Ascending Node (LTAN) in hours.

Return type:

float

static compute_mean_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Mean Local Time of the Ascending Node (MLTAN) in hours.

Return type:

float

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_ltan

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

compute_mean_ltan

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

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.

frozen_orbit

Overloaded function.

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_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Local Time of the Ascending Node (LTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Local Time of the Ascending Node (LTAN) in hours.

Return type:

float

static compute_mean_ltan(
raan: ostk.physics.unit.Angle,
instant: ostk.physics.time.Instant,
sun: ostk.physics.environment.object.celestial.Sun = Sun.default(),
) → ostk.physics.time.Time

Compute the Mean Local Time of the Ascending Node (MLTAN) from the RAAN and instant.

Parameters:

  • raan (Angle) -- The Right Ascension of the Ascending Node.

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

  • sun (Sun) -- The Sun model.

Returns:

The Mean Local Time of the Ascending Node (MLTAN) in hours.

Return type:

float

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

static frozen_orbit(*args, **kwargs)

Overloaded function.

  1. frozen_orbit(semi_major_axis: ostk.physics.unit.Length, celestial_object: ostk.physics.environment.object.Celestial, eccentricity: ostk.core.type.Real = Real.undefined(), inclination: ostk.physics.unit.Angle = Angle.undefined(), raan: ostk.physics.unit.Angle = Angle.degrees(0.0), aop: ostk.physics.unit.Angle = Angle.undefined(), true_anomaly: ostk.physics.unit.Angle = Angle.degrees(0.0)) -> ostk.astrodynamics.trajectory.orbit.model.kepler.COE

    Build a COE model of a frozen orbit.

    The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.

    At a minimum, a semi-major axis and shared pointer to a central celestial body with a defined J2 and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.

    Additionally, the following combinations of inputs are supported: - AoP (inclination set to critical value, eccentricity derived) - AoP and eccentricity (inclination derived) - AoP and inclination, but at least one of them must be a critical value (eccentricity derived) - Inclination (AoP set to critical value, eccentricity derived) - Eccentricity (AoP set to critical value, inclination derived)

    Note that inclination and eccentricity cannot both be provided.

    RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting COE as they do not impact the frozen orbit condition.

    Args:

    semi_major_axis (Length): The semi-major axis. celestial_object (Celestial): The celestial object. 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.

    Returns:

    COE: The COE model.

  2. frozen_orbit(semi_major_axis: ostk.physics.unit.Length, equatorial_radius: ostk.physics.unit.Length, j2: ostk.core.type.Real, j3: ostk.core.type.Real, eccentricity: ostk.core.type.Real = Real.undefined(), inclination: ostk.physics.unit.Angle = Angle.undefined(), raan: ostk.physics.unit.Angle = Angle.degrees(0.0), aop: ostk.physics.unit.Angle = Angle.undefined(), true_anomaly: ostk.physics.unit.Angle = Angle.degrees(0.0)) -> ostk.astrodynamics.trajectory.orbit.model.kepler.COE

    Build a COE model of a frozen orbit.

    The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.

    At a minimum, a semi-major axis, equatorial radius, J2, and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.

    Additionally, the following combinations of inputs are supported: - AoP (inclination set to critical value, eccentricity derived) - AoP and eccentricity (inclination derived) - AoP and inclination, but at least one of them must be a critical value (eccentricity derived) - Inclination (AoP set to critical value, eccentricity derived) - Eccentricity (AoP set to critical value, inclination derived)

    Note that inclination and eccentricity cannot both be provided.

    RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting COE as they do not impact the frozen orbit condition.

    Args:

    semi_major_axis (Length): The semi-major axis. equatorial_radius (Length): The equatorial radius. j2 (float): The second zonal harmonic coefficient. j3 (float): The third zonal harmonic coefficient. 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.

    Returns:

    COE: The COE model.

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.state.CoordinateBroker.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.CoordinateBroker.html index 0c649cc09..0aadb839a 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.CoordinateBroker.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.CoordinateBroker.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.state.CoordinateBroker — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.state.CoordinateBroker

class CoordinateBroker(*args, **kwargs)

Bases: pybind11_object

Class to manage the coordinate subsets of a state.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.state.CoordinateBroker) -> None

    Default constructor.

  2. __init__(self: ostk.astrodynamics.trajectory.state.CoordinateBroker, coordinate_subsets: list[ostk::astrodynamics::trajectory::state::CoordinateSubset]) -> None

    Create a broker for ther provided coordinate subsets.

    Args:

    list[CoordinateSubset]: The list of coordinate subsets.

Methods

access_subsets

Access the list of coordinate subsets.

add_subset

Add a coordinate subset.

extract_coordinate

Extract the coordinates of a subset from a full coordinates vector.

extract_coordinates

Extract the coordinates of multiple subsets from a full coordinates vector.

get_number_of_coordinates

Get the total number of coordinates.

get_number_of_subsets

Get the number of coordinate subsets.

get_subsets

Get the list of coordinate subsets.

has_subset

Check if the coordinate broker has a given coordinate subset.

access_subsets(
self: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → list[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Access the list of coordinate subsets.

Returns:

The list of coordinate subsets.

Return type:

list[CoordinateSubset]

add_subset(
self: ostk.astrodynamics.trajectory.state.CoordinateBroker,
coordinate_subset: ostk::astrodynamics::trajectory::state::CoordinateSubset,
) → int

Add a coordinate subset.

Parameters:

coordinate_subset (CoordinateSubset) -- The coordinate subset to add.

extract_coordinate(self: ostk.astrodynamics.trajectory.state.CoordinateBroker, coordinates: numpy.ndarray[numpy.float64[m, 1]], coordinate_subset: ostk::astrodynamics::trajectory::state::CoordinateSubset) → numpy.ndarray[numpy.float64[m, 1]]

Extract the coordinates of a subset from a full coordinates vector.

Parameters:
Returns:

The coordinates of the subset.

Return type:

numpy.ndarray

extract_coordinates(self: ostk.astrodynamics.trajectory.state.CoordinateBroker, coordinates: numpy.ndarray[numpy.float64[m, 1]], coordinate_subsets: list[ostk::astrodynamics::trajectory::state::CoordinateSubset]) → numpy.ndarray[numpy.float64[m, 1]]

Extract the coordinates of multiple subsets from a full coordinates vector.

Parameters:
Returns:

The coordinates of the subsets.

Return type:

numpy.ndarray

get_number_of_coordinates(
self: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → int

Get the total number of coordinates.

Returns:

The total number of coordinates.

Return type:

int

get_number_of_subsets(
self: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → int

Get the number of coordinate subsets.

Returns:

The number of coordinate subsets.

Return type:

int

get_subsets(
self: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → list[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the list of coordinate subsets.

Returns:

The list of coordinate subsets.

Return type:

list[CoordinateSubset]

has_subset(
self: ostk.astrodynamics.trajectory.state.CoordinateBroker,
coordinate_subset: ostk::astrodynamics::trajectory::state::CoordinateSubset,
) → bool

Check if the coordinate broker has a given coordinate subset.

Parameters:

coordinate_subset (CoordinateSubset) -- The coordinate subset to check.

Returns:

True if the coordinate broker has the coordinate subset, False otherwise.

Return type:

bool

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

ostk.astrodynamics.trajectory.state.CoordinateBroker

class CoordinateBroker(*args, **kwargs)

Bases: pybind11_object

Class to manage the coordinate subsets of a state.

Overloaded function.

  1. __init__(self: ostk.astrodynamics.trajectory.state.CoordinateBroker) -> None

    Default constructor.

  2. __init__(self: ostk.astrodynamics.trajectory.state.CoordinateBroker, coordinate_subsets: list[ostk::astrodynamics::trajectory::state::CoordinateSubset]) -> None

    Create a broker for ther provided coordinate subsets.

    Args:

    list[CoordinateSubset]: The list of coordinate subsets.

Methods

access_subsets

Access the list of coordinate subsets.

add_subset

Add a coordinate subset.

extract_coordinate

Extract the coordinates of a subset from a full coordinates vector.

extract_coordinates

Extract the coordinates of multiple subsets from a full coordinates vector.

get_number_of_coordinates

Get the total number of coordinates.

get_number_of_subsets

Get the number of coordinate subsets.

get_subsets

Get the list of coordinate subsets.

has_subset

Check if the coordinate broker has a given coordinate subset.

access_subsets(
self: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → list[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Access the list of coordinate subsets.

Returns:

The list of coordinate subsets.

Return type:

list[CoordinateSubset]

add_subset(
self: ostk.astrodynamics.trajectory.state.CoordinateBroker,
coordinate_subset: ostk::astrodynamics::trajectory::state::CoordinateSubset,
) → int

Add a coordinate subset.

Parameters:

coordinate_subset (CoordinateSubset) -- The coordinate subset to add.

extract_coordinate(self: ostk.astrodynamics.trajectory.state.CoordinateBroker, coordinates: numpy.ndarray[numpy.float64[m, 1]], coordinate_subset: ostk::astrodynamics::trajectory::state::CoordinateSubset) → numpy.ndarray[numpy.float64[m, 1]]

Extract the coordinates of a subset from a full coordinates vector.

Parameters:
Returns:

The coordinates of the subset.

Return type:

numpy.ndarray

extract_coordinates(self: ostk.astrodynamics.trajectory.state.CoordinateBroker, coordinates: numpy.ndarray[numpy.float64[m, 1]], coordinate_subsets: list[ostk::astrodynamics::trajectory::state::CoordinateSubset]) → numpy.ndarray[numpy.float64[m, 1]]

Extract the coordinates of multiple subsets from a full coordinates vector.

Parameters:
Returns:

The coordinates of the subsets.

Return type:

numpy.ndarray

get_number_of_coordinates(
self: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → int

Get the total number of coordinates.

Returns:

The total number of coordinates.

Return type:

int

get_number_of_subsets(
self: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → int

Get the number of coordinate subsets.

Returns:

The number of coordinate subsets.

Return type:

int

get_subsets(
self: ostk.astrodynamics.trajectory.state.CoordinateBroker,
) → list[ostk::astrodynamics::trajectory::state::CoordinateSubset]

Get the list of coordinate subsets.

Returns:

The list of coordinate subsets.

Return type:

list[CoordinateSubset]

has_subset(
self: ostk.astrodynamics.trajectory.state.CoordinateBroker,
coordinate_subset: ostk::astrodynamics::trajectory::state::CoordinateSubset,
) → bool

Check if the coordinate broker has a given coordinate subset.

Parameters:

coordinate_subset (CoordinateSubset) -- The coordinate subset to check.

Returns:

True if the coordinate broker has the coordinate subset, False otherwise.

Return type:

bool

\ 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 ddd991a75..41ed54f5e 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.NumericalSolver.html b/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.NumericalSolver.html index 0a961e97f..45e469fbf 100644 --- a/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.NumericalSolver.html +++ b/_build/html/_autosummary/ostk.astrodynamics.trajectory.state.NumericalSolver.html @@ -1 +1 @@ - ostk.astrodynamics.trajectory.state.NumericalSolver — Open Space Toolkit Astrodynamics Skip to content

ostk.astrodynamics.trajectory.state.NumericalSolver

class NumericalSolver(
self: ostk.astrodynamics.trajectory.state.NumericalSolver,
log_type: ostk.mathematics.solver.NumericalSolver.LogType,
stepper_type: ostk.mathematics.solver.NumericalSolver.StepperType,
time_step: ostk.core.type.Real,
relative_tolerance: ostk.core.type.Real,
absolute_tolerance: ostk.core.type.Real,
root_solver: ostk.astrodynamics.RootSolver = RootSolver.default(),
)

Bases: NumericalSolver

A numerical solver is used to integrate the trajectory of a dynamical system.

The numerical solver can be used to integrate the trajectory of a dynamical system to a given instant, or to a set of instants, or until an Event Condition is met.

Constructor.

Parameters:

Methods

conditional

Return a conditional numerical solver.

default

Return the default numerical solver.

default_conditional

Return the default conditional numerical solver.

fixed_step_size

Return a Numerical Solver using a fixed stepper.

get_absolute_tolerance

get_log_type

get_observed_state_vectors

get_observed_states

Get the observed states.

get_relative_tolerance

get_root_solver

Get the root solver.

get_stepper_type

get_time_step

integrate_duration

Overloaded function.

integrate_time

Overloaded function.

is_defined

Check if the numerical solver is defined.

string_from_log_type

string_from_stepper_type

undefined

Return an undefined numerical solver.

class ConditionSolution

Bases: pybind11_object

The solution to an event condition.

property condition_is_satisfied

Whether the event condition is satisfied.

Type:

bool

property iteration_count

The number of iterations required to find the solution.

Type:

int

property root_solver_has_converged

Whether the root solver has converged.

Type:

bool

property state

The state of the trajectory.

Type:

State

class LogType(
self: ostk.mathematics.solver.NumericalSolver.LogType,
value: int,
)

Bases: pybind11_object

Members:

NoLog

LogConstant

LogAdaptive

property name
class StepperType(
self: ostk.mathematics.solver.NumericalSolver.StepperType,
value: int,
)

Bases: pybind11_object

Members:

RungeKutta4

RungeKuttaCashKarp54

RungeKuttaFehlberg78

RungeKuttaDopri5

property name
static conditional(
arg0: ostk.core.type.Real,
arg1: ostk.core.type.Real,
arg2: ostk.core.type.Real,
arg3: Callable[[ostk.astrodynamics.trajectory.State], None],
) → ostk.astrodynamics.trajectory.state.NumericalSolver

Return a conditional numerical solver.

Returns:

The conditional numerical solver.

Return type:

NumericalSolver

static default() → ostk.astrodynamics.trajectory.state.NumericalSolver

Return the default numerical solver.

Returns:

The default numerical solver.

Return type:

NumericalSolver

static default_conditional(
state_logger: Callable[[ostk.astrodynamics.trajectory.State], None] = None,
) → ostk.astrodynamics.trajectory.state.NumericalSolver

Return the default conditional numerical solver.

Parameters:

state_logger (StateLogger, optional) -- The state logger. Defaults to None.

Returns:

The default conditional numerical solver.

Return type:

NumericalSolver

static fixed_step_size(
stepper_type: ostk.mathematics.solver.NumericalSolver.StepperType,
time_step: ostk.core.type.Real,
) → ostk.astrodynamics.trajectory.state.NumericalSolver

Return a Numerical Solver using a fixed stepper.

Returns:

The numerical solver.

Return type:

NumericalSolver

get_absolute_tolerance(
self: ostk.mathematics.solver.NumericalSolver,
) → ostk.core.type.Real
get_log_type(
self: ostk.mathematics.solver.NumericalSolver,
) → ostk::mathematics::solver::NumericalSolver::LogType
get_observed_state_vectors(
self: ostk.mathematics.solver.NumericalSolver,
) → list[tuple[numpy.ndarray[numpy.float64[m, 1]], float]]
get_observed_states(
self: ostk.astrodynamics.trajectory.state.NumericalSolver,
) → list[ostk.astrodynamics.trajectory.State]

Get the observed states.

Returns:

The observed states.

Return type:

list[State]

get_relative_tolerance(
self: ostk.mathematics.solver.NumericalSolver,
) → ostk.core.type.Real
get_root_solver(
self: ostk.astrodynamics.trajectory.state.NumericalSolver,
) → ostk.astrodynamics.RootSolver

Get the root solver.

Returns:

The root solver.

Return type:

RootSolver

get_stepper_type(
self: ostk.mathematics.solver.NumericalSolver,
) → ostk::mathematics::solver::NumericalSolver::StepperType
get_time_step(
self: ostk.mathematics.solver.NumericalSolver,
) → ostk.core.type.Real
integrate_duration(*args, **kwargs)

Overloaded function.

  1. integrate_duration(self: ostk.mathematics.solver.NumericalSolver, arg0: numpy.ndarray[numpy.float64[m, 1]], arg1: ostk.core.type.Real, arg2: object) -> tuple[numpy.ndarray[numpy.float64[m, 1]], float]

  2. integrate_duration(self: ostk.mathematics.solver.NumericalSolver, arg0: numpy.ndarray[numpy.float64[m, 1]], arg1: list[ostk.core.type.Real], arg2: object) -> list[tuple[numpy.ndarray[numpy.float64[m, 1]], float]]

integrate_time(*args, **kwargs)

Overloaded function.

  1. integrate_time(self: ostk.astrodynamics.trajectory.state.NumericalSolver, state: ostk.astrodynamics.trajectory.State, instant: ostk.physics.time.Instant, system_of_equations: object) -> ostk.astrodynamics.trajectory.State

    Integrate the trajectory to a given instant.

    Args:

    state (State): The initial state of the trajectory. instant (Instant): The instant to integrate to. system_of_equations (callable): The system of equations.

    Returns:

    State: The state at the requested time.

  2. integrate_time(self: ostk.astrodynamics.trajectory.state.NumericalSolver, state: ostk.astrodynamics.trajectory.State, instants: list[ostk.physics.time.Instant], system_of_equations: object) -> list[ostk.astrodynamics.trajectory.State]

    Integrate the trajectory to a set of instants.

    Args:

    state (State): The initial state of the trajectory. instants (list[Instant]): The instants to integrate to. system_of_equations (callable): The system of equations.

    Returns:

    list[State]: The states at the requested times.

  3. integrate_time(self: ostk.astrodynamics.trajectory.state.NumericalSolver, state: ostk.astrodynamics.trajectory.State, instant: ostk.physics.time.Instant, system_of_equations: object, event_condition: ostk::astrodynamics::EventCondition) -> ostk.astrodynamics.trajectory.state.NumericalSolver.ConditionSolution

    Integrate the trajectory to a given instant, with an event condition.

    Args:

    state (State): The initial state of the trajectory. instant (Instant): The instant to integrate to. system_of_equations (callable): The system of equations. event_condition (EventCondition): The event condition.

    Returns:

    ConditionSolution: The solution to the event condition.

is_defined(
self: ostk.astrodynamics.trajectory.state.NumericalSolver,
) → bool

Check if the numerical solver is defined.

Returns:

True if the numerical solver is defined, False otherwise.

Return type:

bool

static string_from_log_type(
log_type: ostk::mathematics::solver::NumericalSolver::LogType,
) → ostk.core.type.String
static string_from_stepper_type(
stepper_type: ostk::mathematics::solver::NumericalSolver::StepperType,
) → ostk.core.type.String
static undefined() → ostk.astrodynamics.trajectory.state.NumericalSolver

Return an undefined numerical solver.

Returns:

The undefined numerical solver.

Return type:

NumericalSolver

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

ostk.astrodynamics.trajectory.state.NumericalSolver

class NumericalSolver(
self: ostk.astrodynamics.trajectory.state.NumericalSolver,
log_type: ostk.mathematics.solver.NumericalSolver.LogType,
stepper_type: ostk.mathematics.solver.NumericalSolver.StepperType,
time_step: ostk.core.type.Real,
relative_tolerance: ostk.core.type.Real,
absolute_tolerance: ostk.core.type.Real,
root_solver: ostk.astrodynamics.RootSolver = RootSolver.default(),
)

Bases: NumericalSolver

A numerical solver is used to integrate the trajectory of a dynamical system.

The numerical solver can be used to integrate the trajectory of a dynamical system to a given instant, or to a set of instants, or until an Event Condition is met.

Constructor.

Parameters:

Methods

conditional

Return a conditional numerical solver.

default

Return the default numerical solver.

default_conditional

Return the default conditional numerical solver.

fixed_step_size

Return a Numerical Solver using a fixed stepper.

get_absolute_tolerance

get_log_type

get_observed_state_vectors

get_observed_states

Get the observed states.

get_relative_tolerance

get_root_solver

Get the root solver.

get_stepper_type

get_time_step

integrate_duration

Overloaded function.

integrate_time

Overloaded function.

is_defined

Check if the numerical solver is defined.

string_from_log_type

string_from_stepper_type

undefined

Return an undefined numerical solver.

class ConditionSolution

Bases: pybind11_object

The solution to an event condition.

property condition_is_satisfied

Whether the event condition is satisfied.

Type:

bool

property iteration_count

The number of iterations required to find the solution.

Type:

int

property root_solver_has_converged

Whether the root solver has converged.

Type:

bool

property state

The state of the trajectory.

Type:

State

class LogType(
self: ostk.mathematics.solver.NumericalSolver.LogType,
value: int,
)

Bases: pybind11_object

Members:

NoLog

LogConstant

LogAdaptive

property name
class StepperType(
self: ostk.mathematics.solver.NumericalSolver.StepperType,
value: int,
)

Bases: pybind11_object

Members:

RungeKutta4

RungeKuttaCashKarp54

RungeKuttaFehlberg78

RungeKuttaDopri5

property name
static conditional(
arg0: ostk.core.type.Real,
arg1: ostk.core.type.Real,
arg2: ostk.core.type.Real,
arg3: Callable[[ostk.astrodynamics.trajectory.State], None],
) → ostk.astrodynamics.trajectory.state.NumericalSolver

Return a conditional numerical solver.

Returns:

The conditional numerical solver.

Return type:

NumericalSolver

static default() → ostk.astrodynamics.trajectory.state.NumericalSolver

Return the default numerical solver.

Returns:

The default numerical solver.

Return type:

NumericalSolver

static default_conditional(
state_logger: Callable[[ostk.astrodynamics.trajectory.State], None] = None,
) → ostk.astrodynamics.trajectory.state.NumericalSolver

Return the default conditional numerical solver.

Parameters:

state_logger (StateLogger, optional) -- The state logger. Defaults to None.

Returns:

The default conditional numerical solver.

Return type:

NumericalSolver

static fixed_step_size(
stepper_type: ostk.mathematics.solver.NumericalSolver.StepperType,
time_step: ostk.core.type.Real,
) → ostk.astrodynamics.trajectory.state.NumericalSolver

Return a Numerical Solver using a fixed stepper.

Returns:

The numerical solver.

Return type:

NumericalSolver

get_absolute_tolerance(
self: ostk.mathematics.solver.NumericalSolver,
) → ostk.core.type.Real
get_log_type(
self: ostk.mathematics.solver.NumericalSolver,
) → ostk::mathematics::solver::NumericalSolver::LogType
get_observed_state_vectors(
self: ostk.mathematics.solver.NumericalSolver,
) → list[tuple[numpy.ndarray[numpy.float64[m, 1]], float]]
get_observed_states(
self: ostk.astrodynamics.trajectory.state.NumericalSolver,
) → list[ostk.astrodynamics.trajectory.State]

Get the observed states.

Returns:

The observed states.

Return type:

list[State]

get_relative_tolerance(
self: ostk.mathematics.solver.NumericalSolver,
) → ostk.core.type.Real
get_root_solver(
self: ostk.astrodynamics.trajectory.state.NumericalSolver,
) → ostk.astrodynamics.RootSolver

Get the root solver.

Returns:

The root solver.

Return type:

RootSolver

get_stepper_type(
self: ostk.mathematics.solver.NumericalSolver,
) → ostk::mathematics::solver::NumericalSolver::StepperType
get_time_step(
self: ostk.mathematics.solver.NumericalSolver,
) → ostk.core.type.Real
integrate_duration(*args, **kwargs)

Overloaded function.

  1. integrate_duration(self: ostk.mathematics.solver.NumericalSolver, arg0: numpy.ndarray[numpy.float64[m, 1]], arg1: ostk.core.type.Real, arg2: object) -> tuple[numpy.ndarray[numpy.float64[m, 1]], float]

  2. integrate_duration(self: ostk.mathematics.solver.NumericalSolver, arg0: numpy.ndarray[numpy.float64[m, 1]], arg1: list[ostk.core.type.Real], arg2: object) -> list[tuple[numpy.ndarray[numpy.float64[m, 1]], float]]

integrate_time(*args, **kwargs)

Overloaded function.

  1. integrate_time(self: ostk.astrodynamics.trajectory.state.NumericalSolver, state: ostk.astrodynamics.trajectory.State, instant: ostk.physics.time.Instant, system_of_equations: object) -> ostk.astrodynamics.trajectory.State

    Integrate the trajectory to a given instant.

    Args:

    state (State): The initial state of the trajectory. instant (Instant): The instant to integrate to. system_of_equations (callable): The system of equations.

    Returns:

    State: The state at the requested time.

  2. integrate_time(self: ostk.astrodynamics.trajectory.state.NumericalSolver, state: ostk.astrodynamics.trajectory.State, instants: list[ostk.physics.time.Instant], system_of_equations: object) -> list[ostk.astrodynamics.trajectory.State]

    Integrate the trajectory to a set of instants.

    Args:

    state (State): The initial state of the trajectory. instants (list[Instant]): The instants to integrate to. system_of_equations (callable): The system of equations.

    Returns:

    list[State]: The states at the requested times.

  3. integrate_time(self: ostk.astrodynamics.trajectory.state.NumericalSolver, state: ostk.astrodynamics.trajectory.State, instant: ostk.physics.time.Instant, system_of_equations: object, event_condition: ostk::astrodynamics::EventCondition) -> ostk.astrodynamics.trajectory.state.NumericalSolver.ConditionSolution

    Integrate the trajectory to a given instant, with an event condition.

    Args:

    state (State): The initial state of the trajectory. instant (Instant): The instant to integrate to. system_of_equations (callable): The system of equations. event_condition (EventCondition): The event condition.

    Returns:

    ConditionSolution: The solution to the event condition.

is_defined(
self: ostk.astrodynamics.trajectory.state.NumericalSolver,
) → bool

Check if the numerical solver is defined.

Returns:

True if the numerical solver is defined, False otherwise.

Return type:

bool

static string_from_log_type(
log_type: ostk::mathematics::solver::NumericalSolver::LogType,
) → ostk.core.type.String
static string_from_stepper_type(
stepper_type: ostk::mathematics::solver::NumericalSolver::StepperType,
) → ostk.core.type.String
static undefined() → ostk.astrodynamics.trajectory.state.NumericalSolver

Return an undefined numerical solver.

Returns:

The undefined numerical solver.

Return type:

NumericalSolver

\ 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 495554b32..dcc947439 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 f4f237065..5f5243bad 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 9d084e8ea..de9e65f58 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 3d532e191..86954d5ab 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/jupyter_execute/e9fa94379369910e6951b960eb663b9c39043a2399cc7d16ae7cfd15a226ea65.svg b/_build/html/_images/06c29e4ad2630ddc63a367944d0633cd30498361a708ac7068040706074d8202.svg similarity index 99% rename from _build/jupyter_execute/e9fa94379369910e6951b960eb663b9c39043a2399cc7d16ae7cfd15a226ea65.svg rename to _build/html/_images/06c29e4ad2630ddc63a367944d0633cd30498361a708ac7068040706074d8202.svg index 7ccedf658..47143e156 100644 --- a/_build/jupyter_execute/e9fa94379369910e6951b960eb663b9c39043a2399cc7d16ae7cfd15a226ea65.svg +++ b/_build/html/_images/06c29e4ad2630ddc63a367944d0633cd30498361a708ac7068040706074d8202.svg @@ -1 +1 @@ - \ No newline at end of file + \ No newline at end of file diff --git a/_build/jupyter_execute/6156a06b98da8747f1993132ee86b2969db2579a8dfabd644f38210523787c98.svg b/_build/html/_images/69a1697a287fb6cf4c98702ee6a4057b6efe55ebc985bea282aa9caf9158b957.svg similarity index 99% rename from _build/jupyter_execute/6156a06b98da8747f1993132ee86b2969db2579a8dfabd644f38210523787c98.svg rename to _build/html/_images/69a1697a287fb6cf4c98702ee6a4057b6efe55ebc985bea282aa9caf9158b957.svg index f8259a886..50bb56021 100644 --- a/_build/jupyter_execute/6156a06b98da8747f1993132ee86b2969db2579a8dfabd644f38210523787c98.svg +++ b/_build/html/_images/69a1697a287fb6cf4c98702ee6a4057b6efe55ebc985bea282aa9caf9158b957.svg @@ -1 +1 @@ -trace 1 \ No newline at end of file +trace 1 \ No newline at end of file diff --git a/_build/html/_images/4110cc3455897c13329d02154786349abf4a64698d3dca52d0f74442a94382a8.svg b/_build/html/_images/727ee7d5dbdc254c026e620fc6f3f680dcd959ffb2b6505ebc9df24461667380.svg similarity index 99% rename from _build/html/_images/4110cc3455897c13329d02154786349abf4a64698d3dca52d0f74442a94382a8.svg rename to _build/html/_images/727ee7d5dbdc254c026e620fc6f3f680dcd959ffb2b6505ebc9df24461667380.svg index f64d70432..84e88753f 100644 --- a/_build/html/_images/4110cc3455897c13329d02154786349abf4a64698d3dca52d0f74442a94382a8.svg +++ b/_build/html/_images/727ee7d5dbdc254c026e620fc6f3f680dcd959ffb2b6505ebc9df24461667380.svg @@ -1 +1 @@ - \ No newline at end of file + \ No newline at end of file diff --git a/_build/html/_notebooks/Access Computation.html b/_build/html/_notebooks/Access Computation.html index 398669a0c..476be676a 100644 --- a/_build/html/_notebooks/Access Computation.html +++ b/_build/html/_notebooks/Access Computation.html @@ -59,12 +59,6 @@ Fetching Data Manifest from [https://github.com/open-space-collective/open-space-toolkit-data/raw/v1/data/manifest.json]... Unlocking local repository [/var/cache/open-space-toolkit-data/data/manifest]... Data Manifest [/var/cache/open-space-toolkit-data/data/manifest/manifest.json] has been successfully fetched from [https://github.com/open-space-collective/open-space-toolkit-data/raw/v1/data/manifest.json]. -Fetching latest Bulletin A... -Locking local repository [/var/cache/open-space-toolkit-data/data/coordinate/frame/provider/iers]... -Creating temporary directory [/var/cache/open-space-toolkit-data/data/coordinate/frame/provider/iers/bulletin-A/tmp]... -Fetching Bulletin A from [https://github.com/open-space-collective/open-space-toolkit-data/raw/v1/data//coordinate/frame/provider/iers/bulletin-A/ser7.dat]... -Unlocking local repository [/var/cache/open-space-toolkit-data/data/coordinate/frame/provider/iers]... -Bulletin A [/var/cache/open-space-toolkit-data/data/coordinate/frame/provider/iers/bulletin-A/ser7.dat] has been successfully fetched from [https://github.com/open-space-collective/open-space-toolkit-data/raw/v1/data//coordinate/frame/provider/iers/bulletin-A/ser7.dat].

Below, we select which orbital model to use:

orbital_model = keplerian_model
 # orbital_model = sgp4_model

We then obtain the satellite orbit (which is a Trajectory object):

satellite_orbit = Orbit(orbital_model, earth)
diff --git a/_build/html/_notebooks/Area Coverage.html b/_build/html/_notebooks/Area Coverage.html
index 701b09cbd..692d2ffeb 100644
--- a/_build/html/_notebooks/Area Coverage.html	
+++ b/_build/html/_notebooks/Area Coverage.html	
@@ -202,7 +202,7 @@
     Two-Line Elements - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 
 ----------------------------------------------------------------------------------------------------
 , -- Frame -------------------------------------------------------------------------------------------
-    Name:                                    VVLH @ Orbit [0x29976f0]                 
+    Name:                                    VVLH @ Orbit [0x2806340]                 
     Quasi-inertial:                          false                                    
     Parent frame:                            GCRF                                     
 ----------------------------------------------------------------------------------------------------
diff --git a/_build/html/_notebooks/Custom Window Generation.html b/_build/html/_notebooks/Custom Window Generation.html
index 296961631..49d58826e 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/6156a06b98da8747f1993132ee86b2969db2579a8dfabd644f38210523787c98.svg
\ No newline at end of file +
../_images/69a1697a287fb6cf4c98702ee6a4057b6efe55ebc985bea282aa9caf9158b957.svg
\ No newline at end of file diff --git a/_build/html/_notebooks/Sensor Modeling.html b/_build/html/_notebooks/Sensor Modeling.html index e0ef4a139..febe27179 100644 --- a/_build/html/_notebooks/Sensor Modeling.html +++ b/_build/html/_notebooks/Sensor Modeling.html @@ -305,7 +305,7 @@ ) figure.show("svg") -
../_images/4110cc3455897c13329d02154786349abf4a64698d3dca52d0f74442a94382a8.svg

3D plot:

data = []
+
../_images/727ee7d5dbdc254c026e620fc6f3f680dcd959ffb2b6505ebc9df24461667380.svg

3D plot:

data = []
 
 data.append(
     go.Scattergeo(
@@ -352,7 +352,7 @@
 )
 
 figure.show("svg")
-
../_images/e9fa94379369910e6951b960eb663b9c39043a2399cc7d16ae7cfd15a226ea65.svg

Satellite body frame orientation plot:

def earth_data(earth):
+
../_images/06c29e4ad2630ddc63a367944d0633cd30498361a708ac7068040706074d8202.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 a08815c96..45bc93871 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()
-
[2024-12-06 19:06:27.354272] [0x00007f66fb597740] [debug]   Solving Segment:
+
[2024-12-20 07:07:48.032807] [0x00007f8ad6823740] [debug]   Solving Segment:
 -- Segment -----------------------------------------------------------------------------------------
     Name:                                    Coast                                    
     Type:                                    Coast                                    
@@ -148,7 +148,7 @@
     Integration relative tolerance:          9.9999999999999998e-13                   
     Integration absolute tolerance:          9.9999999999999998e-13                   
 ----------------------------------------------------------------------------------------------------
-
[2024-12-06 19:06:28.038592] [0x00007f66fb597740] [debug]   
+
[2024-12-20 07:07:48.715020] [0x00007f8ad6823740] [debug]   
 -- Segment Solution --------------------------------------------------------------------------------
     Name:                                    Coast - Mean SMA crossing - coast - 0    
     Condition satisfied:                     True                                     
@@ -159,7 +159,7 @@
 ----------------------------------------------------------------------------------------------------
 
 
-[2024-12-06 19:06:28.038827] [0x00007f66fb597740] [debug]   Solving Segment:
+[2024-12-20 07:07:48.715214] [0x00007f8ad6823740] [debug]   Solving Segment:
 -- Segment -----------------------------------------------------------------------------------------
     Name:                                    Maneuver                                 
     Type:                                    Maneuver                                 
@@ -204,7 +204,7 @@
     Integration relative tolerance:          9.9999999999999998e-13                   
     Integration absolute tolerance:          9.9999999999999998e-13                   
 ----------------------------------------------------------------------------------------------------
-
[2024-12-06 19:06:29.018699] [0x00007f66fb597740] [debug]   
+
[2024-12-20 07:07:49.687865] [0x00007f8ad6823740] [debug]   
 -- Segment Solution --------------------------------------------------------------------------------
     Name:                                    Maneuver - Mean SMA crossing - thrust - 0 
     Condition satisfied:                     True                                     
@@ -218,7 +218,7 @@
 ----------------------------------------------------------------------------------------------------
 
 
-[2024-12-06 19:06:29.018943] [0x00007f66fb597740] [debug]   Solving Segment:
+[2024-12-20 07:07:49.688048] [0x00007f8ad6823740] [debug]   Solving Segment:
 -- Segment -----------------------------------------------------------------------------------------
     Name:                                    Coast                                    
     Type:                                    Coast                                    
@@ -239,7 +239,7 @@
     Integration relative tolerance:          9.9999999999999998e-13                   
     Integration absolute tolerance:          9.9999999999999998e-13                   
 ----------------------------------------------------------------------------------------------------
-
[2024-12-06 19:06:32.295582] [0x00007f66fb597740] [debug]   
+
[2024-12-20 07:07:52.964026] [0x00007f8ad6823740] [debug]   
 -- Segment Solution --------------------------------------------------------------------------------
     Name:                                    Coast - Mean SMA crossing - coast - 1    
     Condition satisfied:                     True                                     
@@ -250,7 +250,7 @@
 ----------------------------------------------------------------------------------------------------
 
 
-[2024-12-06 19:06:32.296178] [0x00007f66fb597740] [debug]   Solving Segment:
+[2024-12-20 07:07:52.964586] [0x00007f8ad6823740] [debug]   Solving Segment:
 -- Segment -----------------------------------------------------------------------------------------
     Name:                                    Maneuver                                 
     Type:                                    Maneuver                                 
@@ -295,7 +295,7 @@
     Integration relative tolerance:          9.9999999999999998e-13                   
     Integration absolute tolerance:          9.9999999999999998e-13                   
 ----------------------------------------------------------------------------------------------------
-
[2024-12-06 19:06:33.297169] [0x00007f66fb597740] [debug]   
+
[2024-12-20 07:07:53.941699] [0x00007f8ad6823740] [debug]   
 -- Segment Solution --------------------------------------------------------------------------------
     Name:                                    Maneuver - Mean SMA crossing - thrust - 1 
     Condition satisfied:                     True                                     
diff --git a/_build/html/_notebooks/Target Tracking.html b/_build/html/_notebooks/Target Tracking.html
index 9542662a0..98ccfa63b 100644
--- a/_build/html/_notebooks/Target Tracking.html	
+++ b/_build/html/_notebooks/Target Tracking.html	
@@ -213,7 +213,7 @@
     yprs[["Yaw [deg]", "Pitch [deg]", "Roll [deg]"]],
     title="Yaw-Pitch-Roll Evolution",
 )
-

Visualize the scene in 3D:

# Get a token from https://cesium.com/learn/ion/cesium-ion-access-tokens/
+

Visualize the scene in 3D:

# Get a token from https://cesium.com/learn/ion/cesium-ion-access-tokens/
 viewer = Viewer(
     interval=access.get_interval(),
     cesium_token=os.environ.get("CESIUM_TOKEN"),
diff --git a/_build/html/_notebooks/Visualize Satellite Trajectory (Cesium).html b/_build/html/_notebooks/Visualize Satellite Trajectory (Cesium).html
index 84d5a9cb2..8e5f3d9f4 100644
--- a/_build/html/_notebooks/Visualize Satellite Trajectory (Cesium).html	
+++ b/_build/html/_notebooks/Visualize Satellite Trajectory (Cesium).html	
@@ -2,19 +2,17 @@
 
 !{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-fd73_012/cesiumpy_24f1f5e0101e4ee28a313b5abf1c81cc
-  Running command git clone --filter=blob:none --quiet https://github.com/open-space-collective/cesiumpy.git /tmp/pip-install-fd73_012/cesiumpy_24f1f5e0101e4ee28a313b5abf1c81cc
+  Cloning https://github.com/open-space-collective/cesiumpy.git to /tmp/pip-install-p38i49ej/cesiumpy_a37d0dd3848a4478a655e4c1d89a5a40
+  Running command git clone --filter=blob:none --quiet https://github.com/open-space-collective/cesiumpy.git /tmp/pip-install-p38i49ej/cesiumpy_a37d0dd3848a4478a655e4c1d89a5a40
 
  Resolved https://github.com/open-space-collective/cesiumpy.git to commit 70f6d212da41e7ef536f313ba533bc8026f6882b
   Running command git submodule update --init --recursive -q
 
  Preparing metadata (setup.py) ... ?25l-
 
 done
-?25hRequirement already satisfied: traitlets in /usr/local/lib/python3.11/dist-packages (from cesiumpy) (5.14.3)
+
?25hRequirement already satisfied: traitlets in /usr/local/lib/python3.11/dist-packages (from cesiumpy) (5.14.3)
 Requirement already satisfied: geopy>=1.11.0 in /usr/local/lib/python3.11/dist-packages (from cesiumpy) (2.4.1)
 Requirement already satisfied: geographiclib<3,>=1.52 in /usr/local/lib/python3.11/dist-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, possibly rendering your system unusable.It is recommended to use a virtual environment instead: https://pip.pypa.io/warnings/venv. Use the --root-user-action option if you know what you are doing and want to suppress this warning.
 
-
[notice] A new release of pip is available: 24.1.2 -> 24.3.1
-[notice] To update, run: python3.11 -m pip install --upgrade pip
 
import os
 
 from ostk.physics import Environment
@@ -67,4 +65,4 @@
     ],
 )
 
viewer
-
\ No newline at end of file +
\ No newline at end of file diff --git a/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.Orbit.rst.txt b/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.Orbit.rst.txt index e45abc46d..8201c91e4 100644 --- a/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.Orbit.rst.txt +++ b/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.Orbit.rst.txt @@ -26,6 +26,7 @@ ostk.astrodynamics.trajectory.Orbit ~Orbit.compute_passes ~Orbit.compute_passes_with_model ~Orbit.equatorial + ~Orbit.frozen ~Orbit.geo_synchronous ~Orbit.get_orbital_frame ~Orbit.get_pass_at diff --git a/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.rst.txt b/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.rst.txt index 66ffaa6e5..1cd69ca46 100644 --- a/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.rst.txt +++ b/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.rst.txt @@ -25,6 +25,7 @@ ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean ~BrouwerLyddaneMean.eccentric_anomaly_from_mean_anomaly ~BrouwerLyddaneMean.eccentric_anomaly_from_true_anomaly ~BrouwerLyddaneMean.from_SI_vector + ~BrouwerLyddaneMean.frozen_orbit ~BrouwerLyddaneMean.get_SI_vector ~BrouwerLyddaneMean.get_angular_momentum ~BrouwerLyddaneMean.get_aop diff --git a/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.rst.txt b/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.rst.txt index 352d093cc..bd55e0f8b 100644 --- a/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.rst.txt +++ b/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.rst.txt @@ -26,6 +26,7 @@ ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanL ~BrouwerLyddaneMeanLong.eccentric_anomaly_from_mean_anomaly ~BrouwerLyddaneMeanLong.eccentric_anomaly_from_true_anomaly ~BrouwerLyddaneMeanLong.from_SI_vector + ~BrouwerLyddaneMeanLong.frozen_orbit ~BrouwerLyddaneMeanLong.get_SI_vector ~BrouwerLyddaneMeanLong.get_angular_momentum ~BrouwerLyddaneMeanLong.get_aop diff --git a/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.rst.txt b/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.rst.txt index 9acdb86d8..6c3b42753 100644 --- a/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.rst.txt +++ b/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.rst.txt @@ -26,6 +26,7 @@ ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanS ~BrouwerLyddaneMeanShort.eccentric_anomaly_from_mean_anomaly ~BrouwerLyddaneMeanShort.eccentric_anomaly_from_true_anomaly ~BrouwerLyddaneMeanShort.from_SI_vector + ~BrouwerLyddaneMeanShort.frozen_orbit ~BrouwerLyddaneMeanShort.get_SI_vector ~BrouwerLyddaneMeanShort.get_angular_momentum ~BrouwerLyddaneMeanShort.get_aop diff --git a/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.kepler.COE.rst.txt b/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.kepler.COE.rst.txt index 825288cbf..f55268fc6 100644 --- a/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.kepler.COE.rst.txt +++ b/_build/html/_sources/_autosummary/ostk.astrodynamics.trajectory.orbit.model.kepler.COE.rst.txt @@ -25,6 +25,7 @@ ostk.astrodynamics.trajectory.orbit.model.kepler.COE ~COE.eccentric_anomaly_from_mean_anomaly ~COE.eccentric_anomaly_from_true_anomaly ~COE.from_SI_vector + ~COE.frozen_orbit ~COE.get_SI_vector ~COE.get_angular_momentum ~COE.get_aop diff --git a/_build/html/cpp_rst/class/classostk_1_1astrodynamics_1_1trajectory_1_1_orbit.html b/_build/html/cpp_rst/class/classostk_1_1astrodynamics_1_1trajectory_1_1_orbit.html index 7c2dc7174..4c4192806 100644 --- a/_build/html/cpp_rst/class/classostk_1_1astrodynamics_1_1trajectory_1_1_orbit.html +++ b/_build/html/cpp_rst/class/classostk_1_1astrodynamics_1_1trajectory_1_1_orbit.html @@ -1 +1 @@ - Class ostk::astrodynamics::trajectory::Orbit — Open Space Toolkit Astrodynamics Skip to content

Class ostk::astrodynamics::trajectory::Orbit

class Orbit : public ostk::astrodynamics::Trajectory

Gravitationally curved trajectory of an object.

https://en.wikipedia.org/wiki/Orbit

Public Types

enum class FrameType

Values:

enumerator Undefined
enumerator NED
enumerator LVLH
enumerator VVLH
enumerator LVLHGD
enumerator LVLHGDGT
enumerator QSW
enumerator TNW
enumerator VNC
typedef Array<Pass>::ConstIterator ConstPassIterator

Public Functions

Orbit(const orbit::Model &aModel, const Shared<const Celestial> &aCelestialObjectSPtr)

Constructor.

Parameters:

  • aModel -- An orbit model.

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body.

Orbit(const Array<State> &aStateArray, const Integer &anInitialRevolutionNumber, const Shared<const Celestial> &aCelestialObjectSPtr)

Constructor.

Parameters:

  • aStateArray -- An array of states.

  • anInitialRevolutionNumber -- An initial revolution number.

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body.

Orbit(const Orbit &anOrbit)

Copy constructor.

Parameters:

anOrbit -- Orbit to copy from.

~Orbit()

Destructor.

Orbit &operator=(const Orbit &anOrbit)

Copy assignment operator.

Parameters:

anOrbit -- Orbit to copy from.

Returns:

Reference to the updated Orbit.

bool operator==(const Orbit &anOrbit) const

Equality operator.

Parameters:

anOrbit -- Orbit to compare to.

Returns:

True if Orbits are equal, false otherwise.

bool operator!=(const Orbit &anOrbit) const

Inequality operator.

Parameters:

anOrbit -- Orbit to compare to.

Returns:

True if Orbits are not equal, false otherwise.

bool isDefined() const

Check if the Orbit is defined.

Returns:

True if the Orbit is defined, false otherwise.

Integer getRevolutionNumberAt(const Instant &anInstant) const

Get the revolution number at a given instant.

Parameters:

anInstant -- Instant to get the revolution number at.

Returns:

Revolution number at the given instant.

Pass getPassAt(const Instant &anInstant) const

Get the pass at a given instant.

Parameters:

anInstant -- Instant to get the pass at.

Returns:

Pass at the given instant.

Pass getPassWithRevolutionNumber(const Integer &aRevolutionNumber, const Duration &aStepDuration = Duration::Minutes(10.0)) const

Get the pass with a given revolution number.

Parameters:

  • aRevolutionNumber -- Revolution number to get the pass for.

  • aStepDuration -- Step duration to use. Defaults to Duration::Minutes(10.0).

Returns:

Pass with the given revolution number.

Array<Pass> getPassesWithinInterval(const Interval &anInterval) const

Get all passes within a given interval.

Parameters:

anInterval -- Interval to get the passes within.

Returns:

Array of passes within the given interval.

Shared<const Frame> getOrbitalFrame(const Orbit::FrameType &aFrameType) const

Get the orbital frame of a given type.

Parameters:

aFrameType -- Type of the frame to get.

Returns:

Shared pointer to the orbital frame of the given type.

virtual void print(std::ostream &anOutputStream, bool displayDecorator = true) const override

Print the Orbit to an output stream.

Parameters:

  • anOutputStream -- Output stream to print to.

  • displayDecorator -- Whether to display the decorator.

Public Static Functions

static Orbit Undefined()

Constructs an undefined orbit.

Returns:

Undefined orbit

static Orbit Circular(const Instant &anEpoch, const Length &anAltitude, const Angle &anInclination, const Shared<const Celestial> &aCelestialObjectSPtr)

Constructs a circular orbit.

Model: Kepler (No Perturbation).

Parameters:

  • anEpoch -- An orbit epoch

  • anAltitude -- An orbit altitude (wrt. equatorial radius)

  • anInclination -- An orbit inclination

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body

Returns:

Circular orbit

static Orbit Equatorial(const Instant &anEpoch, const Length &anApoapsisAltitude, const Length &aPeriapsisAltitude, const Shared<const Celestial> &aCelestialObjectSPtr)

Constructs an equatorial orbit.

Model: Kepler (No Perturbation).

Parameters:

  • anEpoch -- An orbit epoch

  • anApoapsisAltitude -- An orbit apoapsis altitude (wrt. equatorial radius)

  • aPeriapsisAltitude -- An orbit periapsis altitude (wrt. equatorial radius)

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body

Returns:

Equatorial orbit

static Orbit CircularEquatorial(const Instant &anEpoch, const Length &anAltitude, const Shared<const Celestial> &aCelestialObjectSPtr)

Constructs a circular-equatorial orbit.

Model: Kepler (No Perturbation).

Parameters:

  • anEpoch -- An orbit epoch

  • anAltitude -- An orbit altitude (wrt. equatorial radius)

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body

Returns:

Circular-equatorial orbit

static Orbit GeoSynchronous(const Instant &anEpoch, const Angle &anInclination, const Angle &aLongitude, const Shared<const Celestial> &aCelestialObjectSPtr)

Constructs a geosynchronous orbit.

Model: Kepler (J2 Perturbation).

Parameters:

  • anEpoch -- An orbit epoch

  • anInclination -- An orbit inclination

  • aLongitude -- A longitude above the surface

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body

Returns:

Circular orbit

static Orbit SunSynchronous(const Instant &anEpoch, const Length &anAltitude, const Time &aLocalTimeAtDescendingNode, const Shared<const Celestial> &aCelestialObjectSPtr, const Angle &anArgumentOfLatitude = Angle::Zero())

Constructs a Sun-synchronous orbit.

Model: Kepler (J2 Perturbation).

Parameters:

  • anEpoch -- An orbit epoch

  • anAltitude -- An orbit altitude (wrt. equatorial radius)

  • aLocalTimeAtDescendingNode -- A local time at descending node

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body

  • anArgumentOfLatitude -- An argument of latitude

Returns:

Sun-synchronous orbit

static String StringFromFrameType(const Orbit::FrameType &aFrameType)

Get the string representation of a frame type.

Parameters:

aFrameType -- Type of the frame to get the string representation of

Returns:

String representation of the frame type

static Array<Pair<Index, Pass>> ComputePasses(const Array<State> &aStateArray, const Integer &anInitialRevolutionNumber)

Compute passes for a given state array and initial revolution number.

Parameters:

  • aStateArray -- Array of states

  • anInitialRevolutionNumber -- Initial revolution number

Returns:

Array of Pair of Index + Passes

static Array<Pass> ComputePassesWithModel(const orbit::Model &aModel, const Instant &aStartInstant, const Instant &anEndInstant, const Integer &anInitialRevolutionNumber)

Compute passes for a given model and interval. Note: An Interval object is not used, as the start and end Instant can be forward or backward intervals.

Parameters:

  • aModel -- An Orbit model.

  • aStartInstant -- Start instant of the interval.

  • anEndInstant -- End instant of the interval.

  • anInitialRevolutionNumber -- Initial revolution number at the start of the interval.

Returns:

Array of passes

\ No newline at end of file + Class ostk::astrodynamics::trajectory::Orbit — Open Space Toolkit Astrodynamics Skip to content

Class ostk::astrodynamics::trajectory::Orbit

class Orbit : public ostk::astrodynamics::Trajectory

Gravitationally curved trajectory of an object.

https://en.wikipedia.org/wiki/Orbit

Public Types

enum class FrameType

Values:

enumerator Undefined
enumerator NED
enumerator LVLH
enumerator VVLH
enumerator LVLHGD
enumerator LVLHGDGT
enumerator QSW
enumerator TNW
enumerator VNC
typedef Array<Pass>::ConstIterator ConstPassIterator

Public Functions

Orbit(const orbit::Model &aModel, const Shared<const Celestial> &aCelestialObjectSPtr)

Constructor.

Parameters:

  • aModel -- An orbit model.

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body.

Orbit(const Array<State> &aStateArray, const Integer &anInitialRevolutionNumber, const Shared<const Celestial> &aCelestialObjectSPtr)

Constructor.

Parameters:

  • aStateArray -- An array of states.

  • anInitialRevolutionNumber -- An initial revolution number.

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body.

Orbit(const Orbit &anOrbit)

Copy constructor.

Parameters:

anOrbit -- Orbit to copy from.

~Orbit()

Destructor.

Orbit &operator=(const Orbit &anOrbit)

Copy assignment operator.

Parameters:

anOrbit -- Orbit to copy from.

Returns:

Reference to the updated Orbit.

bool operator==(const Orbit &anOrbit) const

Equality operator.

Parameters:

anOrbit -- Orbit to compare to.

Returns:

True if Orbits are equal, false otherwise.

bool operator!=(const Orbit &anOrbit) const

Inequality operator.

Parameters:

anOrbit -- Orbit to compare to.

Returns:

True if Orbits are not equal, false otherwise.

bool isDefined() const

Check if the Orbit is defined.

Returns:

True if the Orbit is defined, false otherwise.

Integer getRevolutionNumberAt(const Instant &anInstant) const

Get the revolution number at a given instant.

Parameters:

anInstant -- Instant to get the revolution number at.

Returns:

Revolution number at the given instant.

Pass getPassAt(const Instant &anInstant) const

Get the pass at a given instant.

Parameters:

anInstant -- Instant to get the pass at.

Returns:

Pass at the given instant.

Pass getPassWithRevolutionNumber(const Integer &aRevolutionNumber, const Duration &aStepDuration = Duration::Minutes(10.0)) const

Get the pass with a given revolution number.

Parameters:

  • aRevolutionNumber -- Revolution number to get the pass for.

  • aStepDuration -- Step duration to use. Defaults to Duration::Minutes(10.0).

Returns:

Pass with the given revolution number.

Array<Pass> getPassesWithinInterval(const Interval &anInterval) const

Get all passes within a given interval.

Parameters:

anInterval -- Interval to get the passes within.

Returns:

Array of passes within the given interval.

Shared<const Frame> getOrbitalFrame(const Orbit::FrameType &aFrameType) const

Get the orbital frame of a given type.

Parameters:

aFrameType -- Type of the frame to get.

Returns:

Shared pointer to the orbital frame of the given type.

virtual void print(std::ostream &anOutputStream, bool displayDecorator = true) const override

Print the Orbit to an output stream.

Parameters:

  • anOutputStream -- Output stream to print to.

  • displayDecorator -- Whether to display the decorator.

Public Static Functions

static Orbit Undefined()

Constructs an undefined orbit.

Returns:

Undefined orbit

static Orbit Circular(const Instant &anEpoch, const Length &anAltitude, const Angle &anInclination, const Shared<const Celestial> &aCelestialObjectSPtr)

Constructs a circular orbit.

Model: Kepler (No Perturbation).

Parameters:

  • anEpoch -- An orbit epoch

  • anAltitude -- An orbit altitude (wrt. equatorial radius)

  • anInclination -- An orbit inclination

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body

Returns:

Circular orbit

static Orbit Equatorial(const Instant &anEpoch, const Length &anApoapsisAltitude, const Length &aPeriapsisAltitude, const Shared<const Celestial> &aCelestialObjectSPtr)

Constructs an equatorial orbit.

Model: Kepler (No Perturbation).

Parameters:

  • anEpoch -- An orbit epoch

  • anApoapsisAltitude -- An orbit apoapsis altitude (wrt. equatorial radius)

  • aPeriapsisAltitude -- An orbit periapsis altitude (wrt. equatorial radius)

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body

Returns:

Equatorial orbit

static Orbit CircularEquatorial(const Instant &anEpoch, const Length &anAltitude, const Shared<const Celestial> &aCelestialObjectSPtr)

Constructs a circular-equatorial orbit.

Model: Kepler (No Perturbation).

Parameters:

  • anEpoch -- An orbit epoch

  • anAltitude -- An orbit altitude (wrt. equatorial radius)

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body

Returns:

Circular-equatorial orbit

static Orbit GeoSynchronous(const Instant &anEpoch, const Angle &anInclination, const Angle &aLongitude, const Shared<const Celestial> &aCelestialObjectSPtr)

Constructs a geosynchronous orbit.

Model: Kepler (J2 Perturbation).

Parameters:

  • anEpoch -- An orbit epoch

  • anInclination -- An orbit inclination

  • aLongitude -- A longitude above the surface

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body

Returns:

Circular orbit

static Orbit SunSynchronous(const Instant &anEpoch, const Length &anAltitude, const Time &aLocalTimeAtDescendingNode, const Shared<const Celestial> &aCelestialObjectSPtr, const Angle &anArgumentOfLatitude = Angle::Zero())

Constructs a Sun-synchronous orbit.

Model: Kepler (J2 Perturbation).

Parameters:

  • anEpoch -- An orbit epoch

  • anAltitude -- An orbit altitude (wrt. equatorial radius)

  • aLocalTimeAtDescendingNode -- A local time at descending node

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body

  • anArgumentOfLatitude -- An argument of latitude

Returns:

Sun-synchronous orbit

static Orbit Frozen(const Instant &anEpoch, const Length &anAltitude, const Shared<const Celestial> &aCelestialObjectSPtr, const Real &anEccentricity = Real::Undefined(), const Angle &anInclination = Angle::Undefined(), const Angle &aRaan = Angle::Degrees(0.0), const Angle &anAop = Angle::Undefined(), const Angle &aTrueAnomaly = Angle::Degrees(0.0))

Constructs a Frozen orbit.

Model: Kepler (J2 Perturbation)

The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.

At a minimum, an epoch, altitude, and celestial body with a defined J2 and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.

Additionally, the following combinations of inputs are supported:

  • AoP (inclination set to critical value, eccentricity derived)

  • AoP and eccentricity (inclination derived)

  • AoP and inclination, but at least one of them must be a critical value (eccentricity derived)

  • Inclination (AoP set to critical value, eccentricity derived)

  • Eccentricity (AoP set to critical value, inclination derived)

Note that inclination and eccentricity cannot both be provided.

RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting Orbit as they do not impact the frozen orbit condition.

Parameters:

  • anEpoch -- An orbit epoch

  • anAltitude -- An orbit altitude (wrt. equatorial radius)

  • aCelestialObjectSPtr -- A shared pointer to a central celestial body

  • anEccentricity -- An eccentricity

  • anInclination -- An inclination

  • aRaan -- A raan

  • anAop -- An aop

  • aTrueAnomaly -- A true anomaly

Returns:

Frozen orbit

static String StringFromFrameType(const Orbit::FrameType &aFrameType)

Get the string representation of a frame type.

Parameters:

aFrameType -- Type of the frame to get the string representation of

Returns:

String representation of the frame type

static Array<Pair<Index, Pass>> ComputePasses(const Array<State> &aStateArray, const Integer &anInitialRevolutionNumber)

Compute passes for a given state array and initial revolution number.

Parameters:

  • aStateArray -- Array of states

  • anInitialRevolutionNumber -- Initial revolution number

Returns:

Array of Pair of Index + Passes

static Array<Pass> ComputePassesWithModel(const orbit::Model &aModel, const Instant &aStartInstant, const Instant &anEndInstant, const Integer &anInitialRevolutionNumber)

Compute passes for a given model and interval. Note: An Interval object is not used, as the start and end Instant can be forward or backward intervals.

Parameters:

  • aModel -- An Orbit model.

  • aStartInstant -- Start instant of the interval.

  • anEndInstant -- End instant of the interval.

  • anInitialRevolutionNumber -- Initial revolution number at the start of the interval.

Returns:

Array of passes

\ No newline at end of file diff --git a/_build/html/cpp_rst/class/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1kepler_1_1_c_o_e.html b/_build/html/cpp_rst/class/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1kepler_1_1_c_o_e.html index 241f0a660..11f0102ab 100644 --- a/_build/html/cpp_rst/class/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1kepler_1_1_c_o_e.html +++ b/_build/html/cpp_rst/class/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1kepler_1_1_c_o_e.html @@ -1,3 +1,3 @@ - Class ostk::astrodynamics::trajectory::orbit::model::kepler::COE — Open Space Toolkit Astrodynamics Skip to content

Class ostk::astrodynamics::trajectory::orbit::model::kepler::COE

class COE

Classical Orbital Elements (COE)

https://en.wikipedia.org/wiki/Orbital_elements http://help.agi.com/stk/index.htm#stk/vehSat_coordType_classical.htm

Subclassed by ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMean

Public Types

enum class Element

Values:

enumerator SemiMajorAxis
enumerator Eccentricity
enumerator Inclination
enumerator Raan
enumerator Aop
enumerator TrueAnomaly
enumerator MeanAnomaly
enumerator EccentricAnomaly
enum class AnomalyType

Values:

enumerator True
enumerator Mean
enumerator Eccentric
typedef Pair<Position, Velocity> CartesianState

Public Functions

COE(const Length &aSemiMajorAxis, const Real &anEccentricity, const Angle &anInclination, const Angle &aRaan, const Angle &anAop, const Angle &aTrueAnomaly)

Constructor.

Parameters:

  • aSemiMajorAxis -- A semi-major axis

  • anEccentricity -- An eccentricity

  • anInclination -- An inclination

  • aRaan -- A raan

  • anAop -- An aop

  • aTrueAnomaly -- A true anomaly

bool operator==(const COE &aCOE) const

Equal to operator.

Parameters:

aCOE -- A set of COE

Returns:

True if COEs are equal

bool operator!=(const COE &aCOE) const

Not Equal to operator.

Parameters:

aCOE -- A set of COE

Returns:

True if COEs are not equal

bool isDefined() const

Check if COE is defined.

Returns:

True if COE is defined

Length getSemiMajorAxis() const

Get Semi Major Axis.

Returns:

Semi Major Axis

Real getEccentricity() const

Get Eccentricity.

Returns:

Eccentricity

Angle getInclination() const

Get Inclination.

Returns:

Inclination

Angle getRaan() const

Get Right ascenscion of the ascending node.

Returns:

Right ascenscion of the ascending node

Angle getAop() const

Get Argument of periapsis.

Returns:

Argument of periapsis

virtual Angle getTrueAnomaly() const

Get True anomaly.

Returns:

True anomaly

virtual Angle getMeanAnomaly() const

Get Mean anomaly.

Returns:

Mean anomaly

virtual Angle getEccentricAnomaly() const

Get Eccentric anomaly.

Returns:

Eccentric anomaly

Length getPeriapsisRadius() const

Get Periapsis radius.

Returns:

Periapsis radius

Length getApoapsisRadius() const

Get Apoapsis radius.

Returns:

Apoapsis radius

Length getSemiLatusRectum() const

Get Semi-Latus Rectum.

Returns:

Semi-Latus Rectum

Length getRadialDistance() const

Get Radial Distance.

Returns:

Radiaul Distance

Derived getAngularMomentum(const Derived &aGravitationalParameter) const

Get Angular Momentum.

Parameters:

aGravitationalParameter -- A gravitational parameter

Returns:

Angular Momentum

Derived getMeanMotion(const Derived &aGravitationalParameter) const

Get Mean motion.

Parameters:

aGravitationalParameter -- A gravitational parameter

Returns:

Mean motion

Derived getNodalPrecessionRate(const Derived &aGravitationalParameter, const Length &anEquatorialRadius, const Real &aJ2Parameter) const

Get Nodal precession rate.

Parameters:

  • aGravitationalParameter -- A gravitational parameter

  • anEquatorialRadius -- An equatorial radius

  • aJ2Parameter --

Returns:

Nodal precession rate

Duration getOrbitalPeriod(const Derived &aGravitationalParameter) const

Get Orbital period.

Parameters:

aGravitationalParameter -- A gravitational parameter

Returns:

Orbital period

COE::CartesianState getCartesianState(const Derived &aGravitationalParameter, const Shared<const Frame> &aFrameSPtr) const

Get Cartesian state.

Parameters:

  • aGravitationalParameter -- A gravitational parameter

  • aFrameSPtr -- A frame

Returns:

Cartesian state

Vector6d getSIVector(const AnomalyType &anAnomalyType) const

Get vector of elements in SI units.

Parameters:

anAnomalyType -- An anomaly type

Returns:

Vector

void print(std::ostream &anOutputStream, bool displayDecorator = true) const

Print COE.

Parameters:

  • anOutputStream -- An output stream

  • (optional) -- displayDecorators If true, display decorators

Public Static Functions

static COE Undefined()

Construct an undefined COE. 

COE coe = COE::Undefined();
-
Returns:

Undefined coe

static COE Cartesian(const COE::CartesianState &aCartesianState, const Derived &aGravitationalParameter)

Construct a COE from a cartesian state.

Parameters:

  • aCartesianState -- A cartesian state

  • aGravitationalParameter -- A gravitational parameter

Returns:

COE

static COE FromSIVector(const Vector6d &aCOEVector, const AnomalyType &anAnomalyType)

Construct a COE from a vector.

Parameters:

  • aCOEVector -- A vector

  • anAnomalyType -- An anomaly type

Returns:

COE

static Angle EccentricAnomalyFromTrueAnomaly(const Angle &aTrueAnomaly, const Real &anEccentricity)

Convert True anomaly to Eccentric anomaly.

Parameters:

  • aTrueAnomaly -- A true anomaly

  • anEccentricity -- An eccentricity

Returns:

Eccentric anomaly

static Angle TrueAnomalyFromEccentricAnomaly(const Angle &anEccentricAnomaly, const Real &anEccentricity)

Convert Eccentric anomaly to True anomaly.

Parameters:

  • anEccentricAnomaly -- An eccentric anomaly

  • anEccentricity -- An eccentricity

Returns:

True anomaly

static Angle MeanAnomalyFromEccentricAnomaly(const Angle &anEccentricAnomaly, const Real &anEccentricity)

Convert Mean anomaly to Eccentric anomaly.

Parameters:

  • aMeanAnomaly -- A mean anomaly

  • anEccentricity -- An eccentricity

Returns:

Eccentric anomaly

static Angle EccentricAnomalyFromMeanAnomaly(const Angle &aMeanAnomaly, const Real &anEccentricity, const Real &aTolerance)

Convert Eccentric anomaly to Mean anomaly.

Parameters:

  • anEccentricAnomaly -- An eccentric anomaly

  • anEccentricity -- An eccentricity

  • aTolerance -- a tolerance

Returns:

Mean anomaly

static Angle TrueAnomalyFromMeanAnomaly(const Angle &aMeanAnomly, const Real &anEccentricity, const Real &aTolerance)

Convert Mean anomaly to True anomaly.

Parameters:

  • aMeanAnomaly -- A mean anomaly

  • anEccentricity -- An eccentricity

  • aTolerance -- a tolerance

Returns:

True anomaly

static Real ComputeSemiLatusRectum(const Real &aSemiMajorAxis, const Real &anEccentricity)

Compute the semi-latus rectum of the orbit.

Parameters:

  • aSemiMajorAxis -- Semi-major axis of the orbit in meters.

  • anEccentricity -- Eccentricity of the orbit.

Returns:

Semi-latus rectum in meters.

static Real ComputeAngularMomentum(const Real &aSemiMajorAxis, const Real &anEccentricity, const Derived &aGravitationalParameter)

Compute the angular momentum of the orbit.

Parameters:

  • aSemiMajorAxis -- Semi-major axis of the orbit in meters.

  • anEccentricity -- Eccentricity of the orbit.

  • aGravitationalParameter -- Gravitational parameter.

Returns:

Angular momentum.

static Real ComputeAngularMomentum(const Real &aSemiLatusRectum, const Derived &aGravitationalParameter)

Compute the angular momentum of the orbit.

Parameters:

  • aSemiLatusRectum -- Semi-latus rectum of the orbit in meters.

  • aGravitationalParameter -- Gravitational parameter.

Returns:

Angular momentum.

static Real ComputeRadialDistance(const Real &aSemiMajorAxis, const Real &anEccentricity, const Real &trueAnomaly)

Compute the radial distance at a given true anomaly.

Parameters:

  • aSemiMajorAxis -- Semi-major axis of the orbit in meters.

  • anEccentricity -- Eccentricity of the orbit.

  • trueAnomaly -- True anomaly in radians.

Returns:

Radial distance in meters.

static Time ComputeMeanLTAN(const Angle &raan, const Instant &anInstant, const Sun &sun = Sun::Default())

Compute Mean Local Time of the Ascending Node (MLTAN) from RAAN and instant.

Parameters:

  • raan -- Right Ascension of the Ascending Node

  • anInstant -- The instant at which to compute LTAN

Returns:

Mean Local Time of the Ascending Node (MLTAN) in hours

static Time ComputeLTAN(const Angle &raan, const Instant &anInstant, const Sun &sun = Sun::Default())

Compute Local Time of the Ascending Node (LTAN) from RAAN and instant.

Parameters:

  • raan -- Right Ascension of the Ascending Node

  • anInstant -- The instant at which to compute LTAN

Returns:

Local Time of the Ascending Node (LTAN) in hours

static String StringFromElement(const COE::Element &anElement)

Convert element to string.

Parameters:

anElement -- An element

Returns:

String representing the element

Friends

friend std::ostream &operator<<(std::ostream &anOutputStream, const COE &aCOE)

Output stream operator. 

std::cout << COE(...);
+                        Class ostk::astrodynamics::trajectory::orbit::model::kepler::COE — Open Space Toolkit Astrodynamics                       Skip to content  
  
 
  
 
 
 
 
  
 
 
 
 
 
  
 
 
 
 
 
 
Class ostk::astrodynamics::trajectory::orbit::model::kepler::COE
 
 
 class COE
 
Classical Orbital Elements (COE) 
 
https://en.wikipedia.org/wiki/Orbital_elements http://help.agi.com/stk/index.htm#stk/vehSat_coordType_classical.htm
 
Subclassed by ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMean
 
 
Public Types
 
 
 enum class Element
 
Values:
 
 
 enumerator SemiMajorAxis
 
 
 
 enumerator Eccentricity
 
 
 
 enumerator Inclination
 
 
 
 enumerator Raan
 
 
 
 enumerator Aop
 
 
 
 enumerator TrueAnomaly
 
 
 
 enumerator MeanAnomaly
 
 
 
 enumerator EccentricAnomaly
 
 
 
 
 enum class AnomalyType
 
Values:
 
 
 enumerator True
 
 
 
 enumerator Mean
 
 
 
 enumerator Eccentric
 
 
 
 
 typedef Pair<Position, Velocity> CartesianState
 
 
 
 
Public Functions
 
 
 COE(const Length &aSemiMajorAxis, const Real &anEccentricity, const Angle &anInclination, const Angle &aRaan, const Angle &anAop, const Angle &aTrueAnomaly)
 
Constructor. 
 
 
Parameters: 
     
  • aSemiMajorAxis -- A semi-major axis 
     
  • anEccentricity -- An eccentricity 
     
  • anInclination -- An inclination 
     
  • aRaan -- A raan 
     
  • anAop -- An aop 
     
  • aTrueAnomaly -- A true anomaly 
     
 
 
 
 
 bool operator==(const COE &aCOE) const
 
Equal to operator. 
 
 
Parameters: 
aCOE -- A set of COE
 
Returns: 
True if COEs are equal 
 
 
 
 
 bool operator!=(const COE &aCOE) const
 
Not Equal to operator. 
 
 
Parameters: 
aCOE -- A set of COE
 
Returns: 
True if COEs are not equal 
 
 
 
 
 bool isDefined() const
 
Check if COE is defined. 
 
 
Returns: 
True if COE is defined 
 
 
 
 
 Length getSemiMajorAxis() const
 
Get Semi Major Axis. 
 
 
Returns: 
Semi Major Axis 
 
 
 
 
 Real getEccentricity() const
 
Get Eccentricity. 
 
 
Returns: 
Eccentricity 
 
 
 
 
 Angle getInclination() const
 
Get Inclination. 
 
 
Returns: 
Inclination 
 
 
 
 
 Angle getRaan() const
 
Get Right ascenscion of the ascending node. 
 
 
Returns: 
Right ascenscion of the ascending node 
 
 
 
 
 Angle getAop() const
 
Get Argument of periapsis. 
 
 
Returns: 
Argument of periapsis 
 
 
 
 
 virtual Angle getTrueAnomaly() const
 
Get True anomaly. 
 
 
Returns: 
True anomaly 
 
 
 
 
 virtual Angle getMeanAnomaly() const
 
Get Mean anomaly. 
 
 
Returns: 
Mean anomaly 
 
 
 
 
 virtual Angle getEccentricAnomaly() const
 
Get Eccentric anomaly. 
 
 
Returns: 
Eccentric anomaly 
 
 
 
 
 Length getPeriapsisRadius() const
 
Get Periapsis radius. 
 
 
Returns: 
Periapsis radius 
 
 
 
 
 Length getApoapsisRadius() const
 
Get Apoapsis radius. 
 
 
Returns: 
Apoapsis radius 
 
 
 
 
 Length getSemiLatusRectum() const
 
Get Semi-Latus Rectum. 
 
 
Returns: 
Semi-Latus Rectum 
 
 
 
 
 Length getRadialDistance() const
 
Get Radial Distance. 
 
 
Returns: 
Radiaul Distance 
 
 
 
 
 Derived getAngularMomentum(const Derived &aGravitationalParameter) const
 
Get Angular Momentum. 
 
 
Parameters: 
aGravitationalParameter -- A gravitational parameter 
 
Returns: 
Angular Momentum 
 
 
 
 
 Derived getMeanMotion(const Derived &aGravitationalParameter) const
 
Get Mean motion. 
 
 
Parameters: 
aGravitationalParameter -- A gravitational parameter 
 
Returns: 
Mean motion 
 
 
 
 
 Derived getNodalPrecessionRate(const Derived &aGravitationalParameter, const Length &anEquatorialRadius, const Real &aJ2Parameter) const
 
Get Nodal precession rate. 
 
 
Parameters: 
     
  • aGravitationalParameter -- A gravitational parameter 
     
  • anEquatorialRadius -- An equatorial radius 
     
  • aJ2Parameter -- 
     
 
Returns: 
Nodal precession rate 
 
 
 
 
 Duration getOrbitalPeriod(const Derived &aGravitationalParameter) const
 
Get Orbital period. 
 
 
Parameters: 
aGravitationalParameter -- A gravitational parameter 
 
Returns: 
Orbital period 
 
 
 
 
 COE::CartesianState getCartesianState(const Derived &aGravitationalParameter, const Shared<const Frame> &aFrameSPtr) const
 
Get Cartesian state. 
 
 
Parameters: 
     
  • aGravitationalParameter -- A gravitational parameter 
     
  • aFrameSPtr -- A frame 
     
 
Returns: 
Cartesian state 
 
 
 
 
 Vector6d getSIVector(const AnomalyType &anAnomalyType) const
 
Get vector of elements in SI units. 
 
 
Parameters: 
anAnomalyType -- An anomaly type 
 
Returns: 
Vector 
 
 
 
 
 void print(std::ostream &anOutputStream, bool displayDecorator = true) const
 
Print COE. 
 
 
Parameters: 
     
  • anOutputStream -- An output stream 
     
  • (optional) -- displayDecorators If true, display decorators 
     
 
 
 
 
 
Public Static Functions
 
 
 static COE Undefined()
 
Construct an undefined COE. 
 
COE coe = COE::Undefined();
+
 
 
 
Returns: 
Undefined coe 
 
 
 
 
 static COE Cartesian(const COE::CartesianState &aCartesianState, const Derived &aGravitationalParameter)
 
Construct a COE from a cartesian state. 
 
 
Parameters: 
     
  • aCartesianState -- A cartesian state 
     
  • aGravitationalParameter -- A gravitational parameter 
     
 
Returns: 
COE
 
 
 
 
 static COE FromSIVector(const Vector6d &aCOEVector, const AnomalyType &anAnomalyType)
 
Construct a COE from a vector. 
 
 
Parameters: 
     
  • aCOEVector -- A vector 
     
  • anAnomalyType -- An anomaly type 
     
 
Returns: 
COE
 
 
 
 
 static COE FrozenOrbit(const Length &aSemiMajorAxis, const Shared<const Celestial> &aCelestialObjectSPtr, const Real &anEccentricity = Real::Undefined(), const Angle &anInclination = Angle::Undefined(), const Angle &aRaan = Angle::Degrees(0.0), const Angle &anAop = Angle::Undefined(), const Angle &aTrueAnomaly = Angle::Degrees(0.0))
 
Construct a frozen orbit from an incomplete set of COEs. 
 
The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.
 
At a minimum, a semi-major axis and shared pointer to a central celestial body with a defined J2 and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.
 
Additionally, the following combinations of inputs are supported:
     
  • AoP (inclination set to critical value, eccentricity derived)
     
  • AoP and eccentricity (inclination derived)
     
  • AoP and inclination, but at least one of them must be a critical value (eccentricity derived)
     
  • Inclination (AoP set to critical value, eccentricity derived)
     
  • Eccentricity (AoP set to critical value, inclination derived)
     
 
 
Note that inclination and eccentricity cannot both be provided.
 
RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting COE as they do not impact the frozen orbit condition.
 
 
Parameters: 
     
  • aSemiMajorAxis -- A semi-major axis 
     
  • aCelestialObjectSPtr -- A shared pointer to a central celestial body 
     
  • anEccentricity -- An eccentricity 
     
  • anInclination -- An inclination 
     
  • aRaan -- A raan 
     
  • anAop -- An aop 
     
  • aTrueAnomaly -- A true anomaly 
     
 
Returns: 
COE
 
 
 
 
 static COE FrozenOrbit(const Length &aSemiMajorAxis, const Length &anEquatorialRadius, const Real &aJ2, const Real &aJ3, const Real &anEccentricity = Real::Undefined(), const Angle &anInclination = Angle::Undefined(), const Angle &aRaan = Angle::Degrees(0.0), const Angle &anAop = Angle::Undefined(), const Angle &aTrueAnomaly = Angle::Degrees(0.0))
 
Construct a frozen orbit from an incomplete set of COEs. 
 
The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.
 
At a minimum, a semi-major axis, equatorial radius, J2, and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.
 
Additionally, the following combinations of inputs are supported:
     
  • AoP (inclination set to critical value, eccentricity derived)
     
  • AoP and eccentricity (inclination derived)
     
  • AoP and inclination, but at least one of them must be a critical value (eccentricity derived)
     
  • Inclination (AoP set to critical value, eccentricity derived)
     
  • Eccentricity (AoP set to critical value, inclination derived)
     
 
 
Note that inclination and eccentricity cannot both be provided.
 
RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting COE as they do not impact the frozen orbit condition.
 
 
Parameters: 
     
  • aSemiMajorAxis -- A semi-major axis 
     
  • anEquatorialRadius -- An equatorial radius 
     
  • aJ2 -- A J2 
     
  • aJ3 -- A J3 
     
  • anEccentricity -- An eccentricity 
     
  • anInclination -- An inclination 
     
  • aRaan -- A raan 
     
  • anAop -- An aop 
     
  • aTrueAnomaly -- A true anomaly 
     
 
Returns: 
COE
 
 
 
 
 static Angle EccentricAnomalyFromTrueAnomaly(const Angle &aTrueAnomaly, const Real &anEccentricity)
 
Convert True anomaly to Eccentric anomaly. 
 
 
Parameters: 
     
  • aTrueAnomaly -- A true anomaly 
     
  • anEccentricity -- An eccentricity 
     
 
Returns: 
Eccentric anomaly 
 
 
 
 
 static Angle TrueAnomalyFromEccentricAnomaly(const Angle &anEccentricAnomaly, const Real &anEccentricity)
 
Convert Eccentric anomaly to True anomaly. 
 
 
Parameters: 
     
  • anEccentricAnomaly -- An eccentric anomaly 
     
  • anEccentricity -- An eccentricity 
     
 
Returns: 
True anomaly 
 
 
 
 
 static Angle MeanAnomalyFromEccentricAnomaly(const Angle &anEccentricAnomaly, const Real &anEccentricity)
 
Convert Mean anomaly to Eccentric anomaly. 
 
 
Parameters: 
     
  • aMeanAnomaly -- A mean anomaly 
     
  • anEccentricity -- An eccentricity 
     
 
Returns: 
Eccentric anomaly 
 
 
 
 
 static Angle EccentricAnomalyFromMeanAnomaly(const Angle &aMeanAnomaly, const Real &anEccentricity, const Real &aTolerance)
 
Convert Eccentric anomaly to Mean anomaly. 
 
 
Parameters: 
     
  • anEccentricAnomaly -- An eccentric anomaly 
     
  • anEccentricity -- An eccentricity 
     
  • aTolerance -- a tolerance 
     
 
Returns: 
Mean anomaly 
 
 
 
 
 static Angle TrueAnomalyFromMeanAnomaly(const Angle &aMeanAnomly, const Real &anEccentricity, const Real &aTolerance)
 
Convert Mean anomaly to True anomaly. 
 
 
Parameters: 
     
  • aMeanAnomaly -- A mean anomaly 
     
  • anEccentricity -- An eccentricity 
     
  • aTolerance -- a tolerance 
     
 
Returns: 
True anomaly 
 
 
 
 
 static Real ComputeSemiLatusRectum(const Real &aSemiMajorAxis, const Real &anEccentricity)
 
Compute the semi-latus rectum of the orbit. 
 
 
Parameters: 
     
  • aSemiMajorAxis -- Semi-major axis of the orbit in meters. 
     
  • anEccentricity -- Eccentricity of the orbit. 
     
 
Returns: 
Semi-latus rectum in meters. 
 
 
 
 
 static Real ComputeAngularMomentum(const Real &aSemiMajorAxis, const Real &anEccentricity, const Derived &aGravitationalParameter)
 
Compute the angular momentum of the orbit. 
 
 
Parameters: 
     
  • aSemiMajorAxis -- Semi-major axis of the orbit in meters. 
     
  • anEccentricity -- Eccentricity of the orbit. 
     
  • aGravitationalParameter -- Gravitational parameter. 
     
 
Returns: 
Angular momentum. 
 
 
 
 
 static Real ComputeAngularMomentum(const Real &aSemiLatusRectum, const Derived &aGravitationalParameter)
 
Compute the angular momentum of the orbit. 
 
 
Parameters: 
     
  • aSemiLatusRectum -- Semi-latus rectum of the orbit in meters. 
     
  • aGravitationalParameter -- Gravitational parameter. 
     
 
Returns: 
Angular momentum. 
 
 
 
 
 static Real ComputeRadialDistance(const Real &aSemiMajorAxis, const Real &anEccentricity, const Real &trueAnomaly)
 
Compute the radial distance at a given true anomaly. 
 
 
Parameters: 
     
  • aSemiMajorAxis -- Semi-major axis of the orbit in meters. 
     
  • anEccentricity -- Eccentricity of the orbit. 
     
  • trueAnomaly -- True anomaly in radians. 
     
 
Returns: 
Radial distance in meters. 
 
 
 
 
 static Time ComputeMeanLTAN(const Angle &raan, const Instant &anInstant, const Sun &sun = Sun::Default())
 
Compute Mean Local Time of the Ascending Node (MLTAN) from RAAN and instant. 
 
 
Parameters: 
     
  • raan -- Right Ascension of the Ascending Node 
     
  • anInstant -- The instant at which to compute LTAN 
     
 
Returns: 
Mean Local Time of the Ascending Node (MLTAN) in hours 
 
 
 
 
 static Time ComputeLTAN(const Angle &raan, const Instant &anInstant, const Sun &sun = Sun::Default())
 
Compute Local Time of the Ascending Node (LTAN) from RAAN and instant. 
 
 
Parameters: 
     
  • raan -- Right Ascension of the Ascending Node 
     
  • anInstant -- The instant at which to compute LTAN 
     
 
Returns: 
Local Time of the Ascending Node (LTAN) in hours 
 
 
 
 
 static String StringFromElement(const COE::Element &anElement)
 
Convert element to string. 
 
 
Parameters: 
anElement -- An element 
 
Returns: 
String representing the element 
 
 
 
 
 
Friends
 
 
 friend std::ostream &operator<<(std::ostream &anOutputStream, const COE &aCOE)
 
Output stream operator. 
 
std::cout << COE(...);
 
 
 
 
Parameters: 
     
  • anOutputStream -- An output stream 
     
  • aCOE -- A set of COE
     
 
Returns: 
A reference to output stream 
 
 
 
 
 
 
 
 
 
 
   
\ No newline at end of file
diff --git a/_build/html/cpp_rst/classlist.html b/_build/html/cpp_rst/classlist.html
index 2cc3df5de..f9f5a24ff 100644
--- a/_build/html/cpp_rst/classlist.html
+++ b/_build/html/cpp_rst/classlist.html
@@ -1 +1 @@
-                        Class list — Open Space Toolkit Astrodynamics                     Skip to content  
  
 
  
 
 
 
 
  
 
 
 
 
 
  
 
 
 
 
 
 
Class list
 
  
 
 
 
 
 
 
   
\ No newline at end of file
+                        Class list — Open Space Toolkit Astrodynamics                     Skip to content  
  
 
  
 
 
 
 
  
 
 
 
 
 
  
 
 
 
 
 
 
Class list
 
  
 
 
 
 
 
 
   
\ No newline at end of file
diff --git a/_build/html/genindex.html b/_build/html/genindex.html
index 2364d38a3..825513533 100644
--- a/_build/html/genindex.html
+++ b/_build/html/genindex.html
@@ -1 +1 @@
-                        Index — Open Space Toolkit Astrodynamics                     Skip to content  
  
 
  
 
 
 
 
  
 
 
 
 
 
  
 
 
 
 
 
Index
 
 _ | A | B | C | D | E | F | G | H | I | K | L | M | N | O | P | Q | R | S | T | U | V | W 
 
_
 
  
 
A
 
   
 
B
 
   
 
C
 
   
 
D
 
   
 
E
 
   
 
F
 
   
 
G
 
   
 
H
 
   
 
I
 
   
 
K
 
   
 
L
 
   
 
M
 
   
 
N
 
   
 
O
 
   
 
P
 
   
 
Q
 
   
 
R
 
   
 
S
 
   
 
T
 
   
 
U
 
   
 
V
 
   
 
W
 
   
 
 
 
 
 
   
\ No newline at end of file
+                        Index — Open Space Toolkit Astrodynamics                     Skip to content  
  
 
  
 
 
 
 
  
 
 
 
 
 
  
 
 
 
 
 
Index
 
 _ | A | B | C | D | E | F | G | H | I | K | L | M | N | O | P | Q | R | S | T | U | V | W 
 
_
 
  
 
A
 
   
 
B
 
   
 
C
 
   
 
D
 
   
 
E
 
   
 
F
 
   
 
G
 
   
 
H
 
   
 
I
 
   
 
K
 
   
 
L
 
   
 
M
 
   
 
N
 
   
 
O
 
   
 
P
 
   
 
Q
 
   
 
R
 
   
 
S
 
   
 
T
 
   
 
U
 
   
 
V
 
   
 
W
 
   
 
 
 
 
 
   
\ No newline at end of file
diff --git a/_build/html/objects.inv b/_build/html/objects.inv
index 2ac9c9f21..2ad0f52a5 100644
Binary files a/_build/html/objects.inv and b/_build/html/objects.inv differ
diff --git a/_build/html/reports/_notebooks/Access Computation.err.log b/_build/html/reports/_notebooks/Access Computation.err.log
index 0beb72f83..cfbd3e2e3 100644
--- a/_build/html/reports/_notebooks/Access Computation.err.log	
+++ b/_build/html/reports/_notebooks/Access Computation.err.log	
@@ -1,7 +1,7 @@
 Traceback (most recent call last):
   File "/usr/local/lib/python3.11/dist-packages/jupyter_cache/executors/utils.py", line 58, in single_nb_execution
     executenb(
-  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1314, in execute
+  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1319, in execute
     return NotebookClient(nb=nb, resources=resources, km=km, **kwargs).execute()
            ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
   File "/usr/local/lib/python3.11/dist-packages/jupyter_core/utils/__init__.py", line 165, in wrapped
diff --git a/_build/html/reports/_notebooks/Area Coverage.err.log b/_build/html/reports/_notebooks/Area Coverage.err.log
index 98b954fd5..b75a04164 100644
--- a/_build/html/reports/_notebooks/Area Coverage.err.log	
+++ b/_build/html/reports/_notebooks/Area Coverage.err.log	
@@ -1,7 +1,7 @@
 Traceback (most recent call last):
   File "/usr/local/lib/python3.11/dist-packages/jupyter_cache/executors/utils.py", line 58, in single_nb_execution
     executenb(
-  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1314, in execute
+  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1319, in execute
     return NotebookClient(nb=nb, resources=resources, km=km, **kwargs).execute()
            ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
   File "/usr/local/lib/python3.11/dist-packages/jupyter_core/utils/__init__.py", line 165, in wrapped
@@ -44,7 +44,7 @@ Invoked with: -- Orbit ---------------------------------------------------------
     Two-Line Elements - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 
 ----------------------------------------------------------------------------------------------------
 , -- Frame -------------------------------------------------------------------------------------------
-    Name:                                    VVLH @ Orbit [0x29976f0]                 
+    Name:                                    VVLH @ Orbit [0x2806340]                 
     Quasi-inertial:                          false                                    
     Parent frame:                            GCRF                                     
 ----------------------------------------------------------------------------------------------------
diff --git a/_build/html/reports/_notebooks/Constant Thrust Dynamics.err.log b/_build/html/reports/_notebooks/Constant Thrust Dynamics.err.log
index 97c6aa9ab..12142f07a 100644
--- a/_build/html/reports/_notebooks/Constant Thrust Dynamics.err.log	
+++ b/_build/html/reports/_notebooks/Constant Thrust Dynamics.err.log	
@@ -1,7 +1,7 @@
 Traceback (most recent call last):
   File "/usr/local/lib/python3.11/dist-packages/jupyter_cache/executors/utils.py", line 58, in single_nb_execution
     executenb(
-  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1314, in execute
+  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1319, in execute
     return NotebookClient(nb=nb, resources=resources, km=km, **kwargs).execute()
            ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
   File "/usr/local/lib/python3.11/dist-packages/jupyter_core/utils/__init__.py", line 165, in wrapped
diff --git a/_build/html/reports/_notebooks/Find RF Interference Accesses.err.log b/_build/html/reports/_notebooks/Find RF Interference Accesses.err.log
index 701e7bf94..82da3f716 100644
--- a/_build/html/reports/_notebooks/Find RF Interference Accesses.err.log	
+++ b/_build/html/reports/_notebooks/Find RF Interference Accesses.err.log	
@@ -1,7 +1,7 @@
 Traceback (most recent call last):
   File "/usr/local/lib/python3.11/dist-packages/jupyter_cache/executors/utils.py", line 58, in single_nb_execution
     executenb(
-  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1314, in execute
+  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1319, in execute
     return NotebookClient(nb=nb, resources=resources, km=km, **kwargs).execute()
            ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
   File "/usr/local/lib/python3.11/dist-packages/jupyter_core/utils/__init__.py", line 165, in wrapped
diff --git a/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 1).err.log b/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 1).err.log
index 5d0d5abc9..0aafe9425 100644
--- a/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 1).err.log	
+++ b/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 1).err.log	
@@ -1,7 +1,7 @@
 Traceback (most recent call last):
   File "/usr/local/lib/python3.11/dist-packages/jupyter_cache/executors/utils.py", line 58, in single_nb_execution
     executenb(
-  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1314, in execute
+  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1319, in execute
     return NotebookClient(nb=nb, resources=resources, km=km, **kwargs).execute()
            ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
   File "/usr/local/lib/python3.11/dist-packages/jupyter_core/utils/__init__.py", line 165, in wrapped
diff --git a/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 2).err.log b/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 2).err.log
index 96e85398e..4a1d752b6 100644
--- a/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 2).err.log	
+++ b/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 2).err.log	
@@ -1,7 +1,7 @@
 Traceback (most recent call last):
   File "/usr/local/lib/python3.11/dist-packages/jupyter_cache/executors/utils.py", line 58, in single_nb_execution
     executenb(
-  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1314, in execute
+  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1319, in execute
     return NotebookClient(nb=nb, resources=resources, km=km, **kwargs).execute()
            ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
   File "/usr/local/lib/python3.11/dist-packages/jupyter_core/utils/__init__.py", line 165, in wrapped
diff --git a/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 3).err.log b/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 3).err.log
index d9368c3f8..508c7e42b 100644
--- a/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 3).err.log	
+++ b/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 3).err.log	
@@ -1,7 +1,7 @@
 Traceback (most recent call last):
   File "/usr/local/lib/python3.11/dist-packages/jupyter_cache/executors/utils.py", line 58, in single_nb_execution
     executenb(
-  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1314, in execute
+  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1319, in execute
     return NotebookClient(nb=nb, resources=resources, km=km, **kwargs).execute()
            ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
   File "/usr/local/lib/python3.11/dist-packages/jupyter_core/utils/__init__.py", line 165, in wrapped
diff --git a/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 4).err.log b/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 4).err.log
index 0ce1db780..282570fa5 100644
--- a/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 4).err.log	
+++ b/_build/html/reports/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 4).err.log	
@@ -1,7 +1,7 @@
 Traceback (most recent call last):
   File "/usr/local/lib/python3.11/dist-packages/jupyter_cache/executors/utils.py", line 58, in single_nb_execution
     executenb(
-  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1314, in execute
+  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1319, in execute
     return NotebookClient(nb=nb, resources=resources, km=km, **kwargs).execute()
            ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
   File "/usr/local/lib/python3.11/dist-packages/jupyter_core/utils/__init__.py", line 165, in wrapped
diff --git a/_build/html/reports/_notebooks/Orbit Computation.err.log b/_build/html/reports/_notebooks/Orbit Computation.err.log
index f1fab1651..55d2e24fc 100644
--- a/_build/html/reports/_notebooks/Orbit Computation.err.log	
+++ b/_build/html/reports/_notebooks/Orbit Computation.err.log	
@@ -1,7 +1,7 @@
 Traceback (most recent call last):
   File "/usr/local/lib/python3.11/dist-packages/jupyter_cache/executors/utils.py", line 58, in single_nb_execution
     executenb(
-  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1314, in execute
+  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1319, in execute
     return NotebookClient(nb=nb, resources=resources, km=km, **kwargs).execute()
            ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
   File "/usr/local/lib/python3.11/dist-packages/jupyter_core/utils/__init__.py", line 165, in wrapped
diff --git a/_build/html/reports/_notebooks/Station-Keeping Sequence.err.log b/_build/html/reports/_notebooks/Station-Keeping Sequence.err.log
index 3a1b299ab..5fb3a760f 100644
--- a/_build/html/reports/_notebooks/Station-Keeping Sequence.err.log	
+++ b/_build/html/reports/_notebooks/Station-Keeping Sequence.err.log	
@@ -1,7 +1,7 @@
 Traceback (most recent call last):
   File "/usr/local/lib/python3.11/dist-packages/jupyter_cache/executors/utils.py", line 58, in single_nb_execution
     executenb(
-  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1314, in execute
+  File "/usr/local/lib/python3.11/dist-packages/nbclient/client.py", line 1319, in execute
     return NotebookClient(nb=nb, resources=resources, km=km, **kwargs).execute()
            ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
   File "/usr/local/lib/python3.11/dist-packages/jupyter_core/utils/__init__.py", line 165, in wrapped
diff --git a/_build/html/searchindex.js b/_build/html/searchindex.js
index 54ada4b63..1a102e501 100644
--- a/_build/html/searchindex.js
+++ b/_build/html/searchindex.js
@@ -1 +1 @@
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ostk::astrodynamics::conjunction::message::ccsds::CDM": [[143, null]], "Class ostk::astrodynamics::dynamics::AtmosphericDrag": [[144, null]], "Class ostk::astrodynamics::dynamics::CentralBodyGravity": [[145, null]], "Class ostk::astrodynamics::dynamics::PositionDerivative": [[146, null]], "Class ostk::astrodynamics::dynamics::Tabulated": [[147, null]], "Class ostk::astrodynamics::dynamics::ThirdBodyGravity": [[148, null]], "Class ostk::astrodynamics::dynamics::Thruster": [[149, null]], "Class ostk::astrodynamics::eventcondition::AngularCondition": [[150, null]], "Class ostk::astrodynamics::eventcondition::BooleanCondition": [[151, null]], "Class ostk::astrodynamics::eventcondition::COECondition": [[152, null]], "Class ostk::astrodynamics::eventcondition::InstantCondition": [[153, null]], "Class ostk::astrodynamics::eventcondition::LogicalCondition": [[154, null]], "Class ostk::astrodynamics::eventcondition::RealCondition": [[155, null]], "Class ostk::astrodynamics::flight::Maneuver": [[156, null]], "Class ostk::astrodynamics::flight::Profile": [[157, null]], "Class ostk::astrodynamics::flight::Profile::CustomTarget": [[158, null]], "Class ostk::astrodynamics::flight::Profile::OrientationProfileTarget": [[159, null]], "Class ostk::astrodynamics::flight::Profile::Target": [[160, null]], "Class ostk::astrodynamics::flight::Profile::TrajectoryTarget": [[161, null]], "Class ostk::astrodynamics::flight::System": [[162, null]], "Class ostk::astrodynamics::flight::profile::Model": [[163, null]], "Class ostk::astrodynamics::flight::profile::model::Tabulated": [[164, null]], "Class ostk::astrodynamics::flight::profile::model::Transform": [[165, null]], "Class ostk::astrodynamics::flight::system::PropulsionSystem": [[166, null]], "Class ostk::astrodynamics::flight::system::SatelliteSystem": [[167, null]], "Class ostk::astrodynamics::flight::system::SatelliteSystemBuilder": [[168, null]], "Class ostk::astrodynamics::guidancelaw::ConstantThrust": [[169, null]], "Class ostk::astrodynamics::guidancelaw::QLaw": [[170, null]], "Class ostk::astrodynamics::solver::FiniteDifferenceSolver": [[171, null]], "Class ostk::astrodynamics::solver::TemporalConditionSolver": [[172, null]], "Class ostk::astrodynamics::trajectory::LocalOrbitalFrameDirection": [[173, null]], "Class ostk::astrodynamics::trajectory::LocalOrbitalFrameFactory": [[174, null]], "Class ostk::astrodynamics::trajectory::LocalOrbitalFrameTransformProvider": [[175, null]], "Class ostk::astrodynamics::trajectory::Model": [[176, null]], "Class ostk::astrodynamics::trajectory::Orbit": [[177, null]], "Class ostk::astrodynamics::trajectory::Propagator": [[178, null]], "Class ostk::astrodynamics::trajectory::Segment": [[179, null]], "Class ostk::astrodynamics::trajectory::Sequence": [[180, null]], "Class ostk::astrodynamics::trajectory::State": [[181, null]], "Class ostk::astrodynamics::trajectory::StateBuilder": [[182, null]], "Class ostk::astrodynamics::trajectory::model::Static": [[183, null]], "Class ostk::astrodynamics::trajectory::model::Tabulated": [[184, null]], "Class ostk::astrodynamics::trajectory::orbit::Model": [[185, null]], "Class ostk::astrodynamics::trajectory::orbit::Pass": [[186, null]], "Class ostk::astrodynamics::trajectory::orbit::message::spacex::OPM": [[187, null]], "Class ostk::astrodynamics::trajectory::orbit::model::Kepler": [[188, null]], "Class ostk::astrodynamics::trajectory::orbit::model::Propagated": [[189, null]], "Class ostk::astrodynamics::trajectory::orbit::model::SGP4": [[190, null]], "Class ostk::astrodynamics::trajectory::orbit::model::SGP4::Impl": [[191, null]], "Class ostk::astrodynamics::trajectory::orbit::model::Tabulated": [[192, null]], "Class ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMean": [[193, null]], "Class ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanLong": [[194, null]], "Class ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanShort": [[195, null]], "Class ostk::astrodynamics::trajectory::orbit::model::kepler::COE": [[196, null]], "Class ostk::astrodynamics::trajectory::orbit::model::sgp4::TLE": [[197, null]], "Class ostk::astrodynamics::trajectory::state::CoordinateBroker": [[198, null]], "Class ostk::astrodynamics::trajectory::state::CoordinateSubset": [[199, null]], "Class ostk::astrodynamics::trajectory::state::NumericalSolver": [[200, null]], "Class ostk::astrodynamics::trajectory::state::coordinatesubset::AngularVelocity": [[201, null]], "Class ostk::astrodynamics::trajectory::state::coordinatesubset::AttitudeQuaternion": [[202, null]], "Class ostk::astrodynamics::trajectory::state::coordinatesubset::CartesianPosition": [[203, null]], "Class ostk::astrodynamics::trajectory::state::coordinatesubset::CartesianVelocity": [[204, null]], "Coast segment": [[131, "coast-segment"]], "Computation": [[117, "computation"], [127, "computation"], [129, "computation"], [132, "computation"]], "Constant Solar Flux and Geomagnetic Index Atmospheric Density Model": [[118, null]], "Constant Thrust Dynamics": [[119, null]], "Contribution": [[206, "contribution"]], "Create a model": [[121, "create-a-model"]], "Cross Validation and Accuracy Tolerances": [[206, "cross-validation-and-accuracy-tolerances"]], "Custom Event Condition": [[120, null]], "Custom Window Generation": [[121, null]], "Debian / Ubuntu": [[206, "debian-ubuntu"]], "Define Satellites": [[122, "define-satellites"]], "Define Scenario": [[122, "define-scenario"]], "Define our condition": [[121, "define-our-condition"]], "Define our solver": [[121, "define-our-solver"]], "Dependencies": [[206, "dependencies"]], "Development Environment": [[206, "development-environment"]], "Docker Images": [[206, "docker-images"]], "Documentation": [[206, "documentation"]], "Eccentricity targeting": [[128, "eccentricity-targeting"]], "Eclipse condition": [[120, "eclipse-condition"]], "Environment": [[116, "environment"], [117, "environment"], [129, "environment"]], "Examples {#Examples}": 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"ostk.astrodynamics.trajectory.orbit.model.kepler.COE.Element", false]], "coecondition (class in ostk.astrodynamics.event_condition)": [[41, "ostk.astrodynamics.event_condition.COECondition", false]], "coerce_to_datetime() (in module ostk.astrodynamics.converters)": [[13, "ostk.astrodynamics.converters.coerce_to_datetime", false]], "coerce_to_instant() (in module ostk.astrodynamics.converters)": [[14, "ostk.astrodynamics.converters.coerce_to_instant", false]], "coerce_to_interval() (in module ostk.astrodynamics.converters)": [[15, "ostk.astrodynamics.converters.coerce_to_interval", false]], "coerce_to_iso() (in module ostk.astrodynamics.converters)": [[16, "ostk.astrodynamics.converters.coerce_to_iso", 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)": [[103, "ostk.astrodynamics.utilities.compute_aer", false]], "compute_angular_momentum() (brouwerlyddanemean static method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.compute_angular_momentum", false]], "compute_angular_momentum() (brouwerlyddanemeanlong static method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.compute_angular_momentum", false]], "compute_angular_momentum() (brouwerlyddanemeanshort static method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.compute_angular_momentum", false]], "compute_angular_momentum() (coe static method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.compute_angular_momentum", false]], "compute_contribution() (atmosphericdrag method)": [[32, "ostk.astrodynamics.dynamics.AtmosphericDrag.compute_contribution", false]], "compute_contribution() (centralbodygravity method)": [[33, "ostk.astrodynamics.dynamics.CentralBodyGravity.compute_contribution", false]], "compute_contribution() (dynamics method)": [[3, "ostk.astrodynamics.Dynamics.compute_contribution", false]], "compute_contribution() (positionderivative method)": [[34, "ostk.astrodynamics.dynamics.PositionDerivative.compute_contribution", false]], "compute_contribution() (tabulated method)": [[35, "ostk.astrodynamics.dynamics.Tabulated.compute_contribution", false]], "compute_contribution() (thirdbodygravity method)": [[36, "ostk.astrodynamics.dynamics.ThirdBodyGravity.compute_contribution", false]], "compute_contribution() (thruster method)": [[37, "ostk.astrodynamics.dynamics.Thruster.compute_contribution", false]], "compute_delta_mass() (segment.solution method)": [[71, "ostk.astrodynamics.trajectory.Segment.Solution.compute_delta_mass", false]], "compute_delta_mass() (sequence.solution method)": [[72, "ostk.astrodynamics.trajectory.Sequence.Solution.compute_delta_mass", false]], "compute_delta_v() (segment.solution method)": [[71, "ostk.astrodynamics.trajectory.Segment.Solution.compute_delta_v", false]], "compute_delta_v() (sequence.solution method)": [[72, "ostk.astrodynamics.trajectory.Sequence.Solution.compute_delta_v", false]], "compute_gradient() (finitedifferencesolver method)": [[62, "ostk.astrodynamics.solver.FiniteDifferenceSolver.compute_gradient", false]], "compute_ground_track() (in module ostk.astrodynamics.utilities)": [[104, "ostk.astrodynamics.utilities.compute_ground_track", false]], "compute_jacobian() (finitedifferencesolver method)": [[62, "ostk.astrodynamics.solver.FiniteDifferenceSolver.compute_jacobian", false]], "compute_ltan() (brouwerlyddanemean static method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.compute_ltan", false]], "compute_ltan() (brouwerlyddanemeanlong static method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.compute_ltan", false]], "compute_ltan() (brouwerlyddanemeanshort static method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.compute_ltan", false]], "compute_ltan() (coe static method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.compute_ltan", false]], "compute_mean_ltan() (brouwerlyddanemean static method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.compute_mean_ltan", false]], "compute_mean_ltan() (brouwerlyddanemeanlong static method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.compute_mean_ltan", false]], "compute_mean_ltan() (brouwerlyddanemeanshort static method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.compute_mean_ltan", false]], "compute_mean_ltan() (coe static method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.compute_mean_ltan", false]], "compute_passes() (orbit static method)": [[69, "ostk.astrodynamics.trajectory.Orbit.compute_passes", false]], "compute_passes_with_model() (orbit static method)": [[69, "ostk.astrodynamics.trajectory.Orbit.compute_passes_with_model", false]], "compute_radial_distance() (brouwerlyddanemean static method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.compute_radial_distance", false]], "compute_radial_distance() (brouwerlyddanemeanlong static method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.compute_radial_distance", false]], "compute_radial_distance() (brouwerlyddanemeanshort static method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.compute_radial_distance", false]], "compute_radial_distance() (coe static method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.compute_radial_distance", false]], "compute_semi_latus_rectum() (brouwerlyddanemean static method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.compute_semi_latus_rectum", false]], "compute_semi_latus_rectum() (brouwerlyddanemeanlong static method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.compute_semi_latus_rectum", false]], "compute_semi_latus_rectum() (brouwerlyddanemeanshort static method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.compute_semi_latus_rectum", false]], "compute_semi_latus_rectum() (coe static method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.compute_semi_latus_rectum", false]], "compute_time_lla_aer_coordinates() (in module ostk.astrodynamics.utilities)": [[105, "ostk.astrodynamics.utilities.compute_time_lla_aer_coordinates", false]], "compute_trajectory_geometry() (in module ostk.astrodynamics.utilities)": [[106, "ostk.astrodynamics.utilities.compute_trajectory_geometry", false]], "condition_is_satisfied (numericalsolver.conditionsolution property)": [[96, "ostk.astrodynamics.trajectory.state.NumericalSolver.ConditionSolution.condition_is_satisfied", false]], "condition_is_satisfied (segment.solution property)": [[71, "ostk.astrodynamics.trajectory.Segment.Solution.condition_is_satisfied", false]], "conditional() (numericalsolver static method)": [[96, "ostk.astrodynamics.trajectory.state.NumericalSolver.conditional", false]], "conicsensor (class in ostk.astrodynamics.viewer)": [[112, "ostk.astrodynamics.viewer.ConicSensor", false]], "constant_mass_flow_rate_profile() (maneuver static method)": [[46, "ostk.astrodynamics.flight.Maneuver.constant_mass_flow_rate_profile", false]], "constantthrust (class in ostk.astrodynamics.guidance_law)": [[59, "ostk.astrodynamics.guidance_law.ConstantThrust", false]], "construct() (localorbitalframefactory static method)": [[66, "ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory.construct", false]], "construct() (localorbitalframetransformprovider static method)": [[67, "ostk.astrodynamics.trajectory.LocalOrbitalFrameTransformProvider.construct", false]], "construct() (tle static method)": [[92, "ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE.construct", false]], "convert_state() (in module ostk.astrodynamics.utilities)": [[107, "ostk.astrodynamics.utilities.convert_state", false]], "convert_to_ground_track_plotting_data() (in module ostk.astrodynamics.display)": [[27, "ostk.astrodynamics.display.convert_to_ground_track_plotting_data", false]], "coordinatebroker (class in ostk.astrodynamics.trajectory.state)": [[94, "ostk.astrodynamics.trajectory.state.CoordinateBroker", false]], "coordinatesubset (class in ostk.astrodynamics.trajectory.state)": [[95, "ostk.astrodynamics.trajectory.state.CoordinateSubset", false]], "covariance_matrix (cdm.data property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Data.covariance_matrix", false]], "covariance_method (cdm.metadata property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Metadata.covariance_method", false]], "cr_area_over_mass (cdm.data property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Data.cr_area_over_mass", false]], "create_2d_map() (in module ostk.astrodynamics.display)": [[28, "ostk.astrodynamics.display.create_2d_map", false]], "create_3d_globe() (in module ostk.astrodynamics.display)": [[29, "ostk.astrodynamics.display.create_3d_globe", false]], "create_plotly_figure() (in module ostk.astrodynamics.display)": [[30, "ostk.astrodynamics.display.create_plotly_figure", false]], "creation_date (cdm.header property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Header.creation_date", false]], "custom_pointing() (profile static method)": [[47, "ostk.astrodynamics.flight.Profile.custom_pointing", false]], "date (opm.deployment property)": [[79, "ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.Deployment.date", false]], "default() (angularvelocity static method)": [[98, "ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity.default", false]], "default() (attitudequaternion static method)": [[99, "ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion.default", false]], "default() (cartesianposition static method)": [[100, "ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition.default", false]], "default() (cartesianvelocity static method)": [[101, "ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity.default", false]], "default() (finitedifferencesolver static method)": [[62, "ostk.astrodynamics.solver.FiniteDifferenceSolver.default", false]], "default() (numericalsolver static method)": [[96, "ostk.astrodynamics.trajectory.state.NumericalSolver.default", false]], "default() (propagator static method)": [[70, "ostk.astrodynamics.trajectory.Propagator.default", false]], "default() (propulsionsystem static method)": [[55, "ostk.astrodynamics.flight.system.PropulsionSystem.default", false]], "default() (rootsolver static method)": [[6, "ostk.astrodynamics.RootSolver.default", false]], "default() (satellitesystem static method)": [[56, "ostk.astrodynamics.flight.system.SatelliteSystem.default", false]], "default() (satellitesystembuilder static method)": [[57, "ostk.astrodynamics.flight.system.SatelliteSystemBuilder.default", false]], "default_conditional() (numericalsolver static method)": [[96, "ostk.astrodynamics.trajectory.state.NumericalSolver.default_conditional", false]], "dictionary() (cdm static method)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.dictionary", false]], "dictionary() (opm static method)": [[79, "ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.dictionary", false]], "drag_coefficient() (angularvelocity static method)": [[98, "ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity.drag_coefficient", false]], "drag_coefficient() (attitudequaternion static method)": [[99, "ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion.drag_coefficient", false]], "drag_coefficient() (cartesianposition static method)": [[100, "ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition.drag_coefficient", false]], "drag_coefficient() (cartesianvelocity static method)": [[101, "ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity.drag_coefficient", false]], "drag_coefficient() (coordinatesubset static method)": [[95, "ostk.astrodynamics.trajectory.state.CoordinateSubset.drag_coefficient", false]], "duration_condition() (booleancondition static method)": [[40, "ostk.astrodynamics.event_condition.BooleanCondition.duration_condition", false]], "duration_condition() (instantcondition static method)": [[42, "ostk.astrodynamics.event_condition.InstantCondition.duration_condition", false]], "duration_condition() (realcondition static method)": [[44, "ostk.astrodynamics.event_condition.RealCondition.duration_condition", false]], "dynamics (class in ostk.astrodynamics)": [[3, "ostk.astrodynamics.Dynamics", false]], "dynamics (segment.solution property)": [[71, "ostk.astrodynamics.trajectory.Segment.Solution.dynamics", false]], "earth_tides (cdm.metadata property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Metadata.earth_tides", false]], "eccentric_anomaly() (coecondition static method)": [[41, "ostk.astrodynamics.event_condition.COECondition.eccentric_anomaly", false]], "eccentric_anomaly_from_mean_anomaly() (brouwerlyddanemean static method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.eccentric_anomaly_from_mean_anomaly", false]], "eccentric_anomaly_from_mean_anomaly() (brouwerlyddanemeanlong static method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.eccentric_anomaly_from_mean_anomaly", false]], "eccentric_anomaly_from_mean_anomaly() (brouwerlyddanemeanshort static method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.eccentric_anomaly_from_mean_anomaly", false]], "eccentric_anomaly_from_mean_anomaly() (coe static method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.eccentric_anomaly_from_mean_anomaly", false]], "eccentric_anomaly_from_true_anomaly() (brouwerlyddanemean static method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.eccentric_anomaly_from_true_anomaly", false]], "eccentric_anomaly_from_true_anomaly() (brouwerlyddanemeanlong static method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.eccentric_anomaly_from_true_anomaly", false]], "eccentric_anomaly_from_true_anomaly() (brouwerlyddanemeanshort static method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.eccentric_anomaly_from_true_anomaly", false]], "eccentric_anomaly_from_true_anomaly() (coe static method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.eccentric_anomaly_from_true_anomaly", false]], "eccentricity() (coecondition static method)": [[41, "ostk.astrodynamics.event_condition.COECondition.eccentricity", false]], "end_screen_period (cdm.relativemetadata property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.RelativeMetadata.end_screen_period", false]], "ephemeris_name (cdm.metadata property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Metadata.ephemeris_name", false]], "equatorial() (orbit static method)": [[69, "ostk.astrodynamics.trajectory.Orbit.equatorial", false]], "evaluate() (booleancondition method)": [[40, "ostk.astrodynamics.event_condition.BooleanCondition.evaluate", false]], "evaluate() (instantcondition method)": [[42, "ostk.astrodynamics.event_condition.InstantCondition.evaluate", false]], "evaluate() (realcondition method)": [[44, "ostk.astrodynamics.event_condition.RealCondition.evaluate", false]], "eventcondition (class in ostk.astrodynamics)": [[4, "ostk.astrodynamics.EventCondition", false]], "eventcondition.target (class in ostk.astrodynamics)": [[4, "ostk.astrodynamics.EventCondition.Target", false]], "eventcondition.target.type (class in ostk.astrodynamics)": [[4, "ostk.astrodynamics.EventCondition.Target.Type", false]], "execution_is_complete (sequence.solution property)": [[72, "ostk.astrodynamics.trajectory.Sequence.Solution.execution_is_complete", false]], "expand() (statebuilder method)": [[74, "ostk.astrodynamics.trajectory.StateBuilder.expand", false]], "extract_coordinate() (coordinatebroker method)": [[94, "ostk.astrodynamics.trajectory.state.CoordinateBroker.extract_coordinate", false]], "extract_coordinate() (state method)": [[73, "ostk.astrodynamics.trajectory.State.extract_coordinate", false]], "extract_coordinates() (coordinatebroker method)": [[94, "ostk.astrodynamics.trajectory.state.CoordinateBroker.extract_coordinates", false]], "extract_coordinates() (state method)": [[73, "ostk.astrodynamics.trajectory.State.extract_coordinates", false]], "extract_maneuvers() (segment.solution method)": [[71, "ostk.astrodynamics.trajectory.Segment.Solution.extract_maneuvers", false]], "finitedifferencesolver (class in ostk.astrodynamics.solver)": [[62, "ostk.astrodynamics.solver.FiniteDifferenceSolver", false]], "finitedifferencesolver.type (class in ostk.astrodynamics.solver)": [[62, "ostk.astrodynamics.solver.FiniteDifferenceSolver.Type", false]], "fixed_step_size() (numericalsolver static method)": [[96, "ostk.astrodynamics.trajectory.state.NumericalSolver.fixed_step_size", false]], "from_dict() (state static method)": [[73, "ostk.astrodynamics.trajectory.State.from_dict", false]], "from_environment() (atmosphericdrag static method)": [[32, "ostk.astrodynamics.dynamics.AtmosphericDrag.from_environment", false]], "from_environment() (centralbodygravity static method)": [[33, "ostk.astrodynamics.dynamics.CentralBodyGravity.from_environment", false]], "from_environment() (dynamics static method)": [[3, "ostk.astrodynamics.Dynamics.from_environment", false]], "from_environment() (positionderivative static method)": [[34, "ostk.astrodynamics.dynamics.PositionDerivative.from_environment", false]], "from_environment() (propagator static method)": [[70, "ostk.astrodynamics.trajectory.Propagator.from_environment", false]], "from_environment() (tabulated static method)": [[35, "ostk.astrodynamics.dynamics.Tabulated.from_environment", false]], "from_environment() (thirdbodygravity static method)": [[36, "ostk.astrodynamics.dynamics.ThirdBodyGravity.from_environment", false]], "from_environment() (thruster static method)": [[37, "ostk.astrodynamics.dynamics.Thruster.from_environment", false]], "from_si_vector() (brouwerlyddanemean static method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.from_SI_vector", false]], "from_si_vector() (brouwerlyddanemeanlong static method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.from_SI_vector", false]], "from_si_vector() (brouwerlyddanemeanshort static method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.from_SI_vector", false]], "from_si_vector() (coe static method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.from_SI_vector", false]], "generate_checksum() (tle static method)": [[92, "ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE.generate_checksum", false]], "generate_column_names() (in module ostk.astrodynamics.dataframe)": [[18, "ostk.astrodynamics.dataframe.generate_column_names", false]], "generate_dataframe_from_orbit() (in module ostk.astrodynamics.dataframe)": [[19, "ostk.astrodynamics.dataframe.generate_dataframe_from_orbit", false]], "generate_dataframe_from_profile() (in module ostk.astrodynamics.dataframe)": [[20, "ostk.astrodynamics.dataframe.generate_dataframe_from_profile", false]], "generate_dataframe_from_states() (in module ostk.astrodynamics.dataframe)": [[21, "ostk.astrodynamics.dataframe.generate_dataframe_from_states", false]], 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(numericalsolver method)": [[96, "ostk.astrodynamics.trajectory.state.NumericalSolver.get_absolute_tolerance", false]], "get_acceleration() (propulsionsystem method)": [[55, "ostk.astrodynamics.flight.system.PropulsionSystem.get_acceleration", false]], "get_acceleration_profile() (maneuver method)": [[46, "ostk.astrodynamics.flight.Maneuver.get_acceleration_profile", false]], "get_access_filter() (generator method)": [[9, "ostk.astrodynamics.access.Generator.get_access_filter", false]], "get_acquisition_of_signal() (access method)": [[2, "ostk.astrodynamics.Access.get_acquisition_of_signal", false]], "get_aer_filter() (generator method)": [[9, "ostk.astrodynamics.access.Generator.get_aer_filter", false]], "get_all_dynamics_contributions() (segment.solution method)": [[71, "ostk.astrodynamics.trajectory.Segment.Solution.get_all_dynamics_contributions", false]], "get_angular_momentum() (brouwerlyddanemean method)": [[81, 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\ No newline at end of file
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ostk.astrodynamics.trajectory.orbit.model)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean", false]], "brouwerlyddanemean.anomalytype (class in ostk.astrodynamics.trajectory.orbit.model)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.AnomalyType", false]], "brouwerlyddanemean.element (class in ostk.astrodynamics.trajectory.orbit.model)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.Element", false]], "brouwerlyddanemeanlong (class in ostk.astrodynamics.trajectory.orbit.model.brouwerlyddanemean)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong", false]], "brouwerlyddanemeanlong.anomalytype (class in ostk.astrodynamics.trajectory.orbit.model.brouwerlyddanemean)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.AnomalyType", false]], "brouwerlyddanemeanlong.element (class in 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"ostk.astrodynamics.utilities.convert_state", false]], "convert_to_ground_track_plotting_data() (in module ostk.astrodynamics.display)": [[27, "ostk.astrodynamics.display.convert_to_ground_track_plotting_data", false]], "coordinatebroker (class in ostk.astrodynamics.trajectory.state)": [[94, "ostk.astrodynamics.trajectory.state.CoordinateBroker", false]], "coordinatesubset (class in ostk.astrodynamics.trajectory.state)": [[95, "ostk.astrodynamics.trajectory.state.CoordinateSubset", false]], "covariance_matrix (cdm.data property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Data.covariance_matrix", false]], "covariance_method (cdm.metadata property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Metadata.covariance_method", false]], "cr_area_over_mass (cdm.data property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Data.cr_area_over_mass", false]], "create_2d_map() (in module ostk.astrodynamics.display)": [[28, "ostk.astrodynamics.display.create_2d_map", false]], "create_3d_globe() (in module ostk.astrodynamics.display)": [[29, "ostk.astrodynamics.display.create_3d_globe", false]], "create_plotly_figure() (in module ostk.astrodynamics.display)": [[30, "ostk.astrodynamics.display.create_plotly_figure", false]], "creation_date (cdm.header property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Header.creation_date", false]], "custom_pointing() (profile static method)": [[47, "ostk.astrodynamics.flight.Profile.custom_pointing", false]], "date (opm.deployment property)": [[79, "ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.Deployment.date", false]], "default() (angularvelocity static method)": [[98, "ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity.default", false]], "default() (attitudequaternion static method)": [[99, "ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion.default", false]], "default() (cartesianposition static method)": [[100, "ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition.default", false]], "default() (cartesianvelocity static method)": [[101, "ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity.default", false]], "default() (finitedifferencesolver static method)": [[62, "ostk.astrodynamics.solver.FiniteDifferenceSolver.default", false]], "default() (numericalsolver static method)": [[96, "ostk.astrodynamics.trajectory.state.NumericalSolver.default", false]], "default() (propagator static method)": [[70, "ostk.astrodynamics.trajectory.Propagator.default", false]], "default() (propulsionsystem static method)": [[55, "ostk.astrodynamics.flight.system.PropulsionSystem.default", false]], "default() (rootsolver static method)": [[6, "ostk.astrodynamics.RootSolver.default", false]], "default() (satellitesystem static method)": [[56, "ostk.astrodynamics.flight.system.SatelliteSystem.default", false]], "default() (satellitesystembuilder static method)": [[57, "ostk.astrodynamics.flight.system.SatelliteSystemBuilder.default", false]], "default_conditional() (numericalsolver static method)": [[96, "ostk.astrodynamics.trajectory.state.NumericalSolver.default_conditional", false]], "dictionary() (cdm static method)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.dictionary", false]], "dictionary() (opm static method)": [[79, "ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.dictionary", false]], "drag_coefficient() (angularvelocity static method)": [[98, "ostk.astrodynamics.trajectory.state.coordinate_subset.AngularVelocity.drag_coefficient", false]], "drag_coefficient() (attitudequaternion static method)": [[99, "ostk.astrodynamics.trajectory.state.coordinate_subset.AttitudeQuaternion.drag_coefficient", false]], "drag_coefficient() (cartesianposition static method)": [[100, "ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianPosition.drag_coefficient", false]], "drag_coefficient() (cartesianvelocity static method)": [[101, "ostk.astrodynamics.trajectory.state.coordinate_subset.CartesianVelocity.drag_coefficient", false]], "drag_coefficient() (coordinatesubset static method)": [[95, "ostk.astrodynamics.trajectory.state.CoordinateSubset.drag_coefficient", false]], "duration_condition() (booleancondition static method)": [[40, "ostk.astrodynamics.event_condition.BooleanCondition.duration_condition", false]], "duration_condition() (instantcondition static method)": [[42, "ostk.astrodynamics.event_condition.InstantCondition.duration_condition", false]], "duration_condition() (realcondition static method)": [[44, "ostk.astrodynamics.event_condition.RealCondition.duration_condition", false]], "dynamics (class in ostk.astrodynamics)": [[3, "ostk.astrodynamics.Dynamics", false]], "dynamics (segment.solution property)": [[71, "ostk.astrodynamics.trajectory.Segment.Solution.dynamics", false]], "earth_tides (cdm.metadata property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Metadata.earth_tides", false]], "eccentric_anomaly() (coecondition static method)": [[41, "ostk.astrodynamics.event_condition.COECondition.eccentric_anomaly", false]], "eccentric_anomaly_from_mean_anomaly() (brouwerlyddanemean static method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.eccentric_anomaly_from_mean_anomaly", false]], "eccentric_anomaly_from_mean_anomaly() (brouwerlyddanemeanlong static method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.eccentric_anomaly_from_mean_anomaly", false]], "eccentric_anomaly_from_mean_anomaly() (brouwerlyddanemeanshort static method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.eccentric_anomaly_from_mean_anomaly", false]], "eccentric_anomaly_from_mean_anomaly() (coe static method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.eccentric_anomaly_from_mean_anomaly", false]], "eccentric_anomaly_from_true_anomaly() (brouwerlyddanemean static method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.eccentric_anomaly_from_true_anomaly", false]], "eccentric_anomaly_from_true_anomaly() (brouwerlyddanemeanlong static method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.eccentric_anomaly_from_true_anomaly", false]], "eccentric_anomaly_from_true_anomaly() (brouwerlyddanemeanshort static method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.eccentric_anomaly_from_true_anomaly", false]], "eccentric_anomaly_from_true_anomaly() (coe static method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.eccentric_anomaly_from_true_anomaly", false]], "eccentricity() (coecondition static method)": [[41, "ostk.astrodynamics.event_condition.COECondition.eccentricity", false]], "end_screen_period (cdm.relativemetadata property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.RelativeMetadata.end_screen_period", false]], "ephemeris_name (cdm.metadata property)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.Metadata.ephemeris_name", false]], "equatorial() (orbit static method)": [[69, "ostk.astrodynamics.trajectory.Orbit.equatorial", false]], "evaluate() (booleancondition method)": [[40, "ostk.astrodynamics.event_condition.BooleanCondition.evaluate", false]], "evaluate() (instantcondition method)": [[42, "ostk.astrodynamics.event_condition.InstantCondition.evaluate", false]], "evaluate() (realcondition method)": [[44, "ostk.astrodynamics.event_condition.RealCondition.evaluate", false]], "eventcondition (class in ostk.astrodynamics)": [[4, "ostk.astrodynamics.EventCondition", false]], "eventcondition.target (class in ostk.astrodynamics)": [[4, "ostk.astrodynamics.EventCondition.Target", false]], "eventcondition.target.type (class in ostk.astrodynamics)": [[4, "ostk.astrodynamics.EventCondition.Target.Type", false]], "execution_is_complete (sequence.solution property)": [[72, "ostk.astrodynamics.trajectory.Sequence.Solution.execution_is_complete", false]], "expand() (statebuilder method)": [[74, "ostk.astrodynamics.trajectory.StateBuilder.expand", false]], "extract_coordinate() (coordinatebroker method)": [[94, "ostk.astrodynamics.trajectory.state.CoordinateBroker.extract_coordinate", false]], "extract_coordinate() (state method)": [[73, "ostk.astrodynamics.trajectory.State.extract_coordinate", false]], "extract_coordinates() (coordinatebroker method)": [[94, "ostk.astrodynamics.trajectory.state.CoordinateBroker.extract_coordinates", false]], "extract_coordinates() (state method)": [[73, "ostk.astrodynamics.trajectory.State.extract_coordinates", false]], "extract_maneuvers() (segment.solution method)": [[71, "ostk.astrodynamics.trajectory.Segment.Solution.extract_maneuvers", false]], "finitedifferencesolver (class in ostk.astrodynamics.solver)": [[62, "ostk.astrodynamics.solver.FiniteDifferenceSolver", false]], "finitedifferencesolver.type (class in ostk.astrodynamics.solver)": [[62, "ostk.astrodynamics.solver.FiniteDifferenceSolver.Type", false]], "fixed_step_size() (numericalsolver static method)": [[96, "ostk.astrodynamics.trajectory.state.NumericalSolver.fixed_step_size", false]], "from_dict() (state static method)": [[73, "ostk.astrodynamics.trajectory.State.from_dict", false]], "from_environment() (atmosphericdrag static method)": [[32, "ostk.astrodynamics.dynamics.AtmosphericDrag.from_environment", false]], "from_environment() (centralbodygravity static method)": [[33, "ostk.astrodynamics.dynamics.CentralBodyGravity.from_environment", false]], "from_environment() (dynamics static method)": [[3, "ostk.astrodynamics.Dynamics.from_environment", false]], "from_environment() (positionderivative static method)": [[34, "ostk.astrodynamics.dynamics.PositionDerivative.from_environment", false]], "from_environment() (propagator static method)": [[70, "ostk.astrodynamics.trajectory.Propagator.from_environment", false]], "from_environment() (tabulated static method)": [[35, "ostk.astrodynamics.dynamics.Tabulated.from_environment", false]], "from_environment() (thirdbodygravity static method)": [[36, "ostk.astrodynamics.dynamics.ThirdBodyGravity.from_environment", false]], "from_environment() (thruster static method)": [[37, "ostk.astrodynamics.dynamics.Thruster.from_environment", false]], "from_si_vector() (brouwerlyddanemean static method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.from_SI_vector", false]], "from_si_vector() (brouwerlyddanemeanlong static method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.from_SI_vector", false]], "from_si_vector() (brouwerlyddanemeanshort static method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.from_SI_vector", false]], "from_si_vector() (coe static method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.from_SI_vector", false]], "frozen() (orbit static method)": [[69, "ostk.astrodynamics.trajectory.Orbit.frozen", false]], "frozen_orbit() (brouwerlyddanemean static method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.frozen_orbit", false]], "frozen_orbit() (brouwerlyddanemeanlong static method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.frozen_orbit", false]], "frozen_orbit() (brouwerlyddanemeanshort static method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.frozen_orbit", false]], "frozen_orbit() (coe static method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.frozen_orbit", false]], "generate_checksum() (tle static method)": [[92, "ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE.generate_checksum", false]], "generate_column_names() (in module ostk.astrodynamics.dataframe)": [[18, "ostk.astrodynamics.dataframe.generate_column_names", false]], "generate_dataframe_from_orbit() (in module ostk.astrodynamics.dataframe)": [[19, "ostk.astrodynamics.dataframe.generate_dataframe_from_orbit", false]], "generate_dataframe_from_profile() (in module ostk.astrodynamics.dataframe)": [[20, "ostk.astrodynamics.dataframe.generate_dataframe_from_profile", false]], "generate_dataframe_from_states() (in module ostk.astrodynamics.dataframe)": [[21, "ostk.astrodynamics.dataframe.generate_dataframe_from_states", false]], "generate_frame() (localorbitalframefactory method)": [[66, "ostk.astrodynamics.trajectory.LocalOrbitalFrameFactory.generate_frame", false]], "generate_orbit_from_dataframe() (in module ostk.astrodynamics.dataframe)": [[22, "ostk.astrodynamics.dataframe.generate_orbit_from_dataframe", false]], "generate_profile_from_dataframe() (in module ostk.astrodynamics.dataframe)": [[23, "ostk.astrodynamics.dataframe.generate_profile_from_dataframe", false]], "generate_states_from_dataframe() (in module ostk.astrodynamics.dataframe)": [[24, "ostk.astrodynamics.dataframe.generate_states_from_dataframe", false]], "generation_date (opm.header property)": [[79, "ostk.astrodynamics.trajectory.orbit.message.spacex.OPM.Header.generation_date", false]], "generator (class in ostk.astrodynamics.access)": [[9, "ostk.astrodynamics.access.Generator", false]], "geo_synchronous() (orbit static method)": [[69, "ostk.astrodynamics.trajectory.Orbit.geo_synchronous", false]], "get_absolute_tolerance() (numericalsolver method)": [[96, "ostk.astrodynamics.trajectory.state.NumericalSolver.get_absolute_tolerance", false]], "get_acceleration() (propulsionsystem method)": [[55, "ostk.astrodynamics.flight.system.PropulsionSystem.get_acceleration", false]], "get_acceleration_profile() (maneuver method)": [[46, "ostk.astrodynamics.flight.Maneuver.get_acceleration_profile", false]], "get_access_filter() (generator method)": [[9, "ostk.astrodynamics.access.Generator.get_access_filter", false]], "get_acquisition_of_signal() (access method)": [[2, "ostk.astrodynamics.Access.get_acquisition_of_signal", false]], "get_aer_filter() (generator method)": [[9, "ostk.astrodynamics.access.Generator.get_aer_filter", false]], "get_all_dynamics_contributions() (segment.solution method)": [[71, "ostk.astrodynamics.trajectory.Segment.Solution.get_all_dynamics_contributions", false]], "get_angular_momentum() (brouwerlyddanemean method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.get_angular_momentum", false]], "get_angular_momentum() (brouwerlyddanemeanlong method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.get_angular_momentum", false]], "get_angular_momentum() (brouwerlyddanemeanshort method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.get_angular_momentum", false]], "get_angular_momentum() (coe method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.get_angular_momentum", false]], "get_angular_velocity() (state method)": [[73, "ostk.astrodynamics.trajectory.State.get_angular_velocity", false]], "get_aop() (brouwerlyddanemean method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.get_aop", false]], "get_aop() (brouwerlyddanemeanlong method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.get_aop", false]], "get_aop() (brouwerlyddanemeanshort method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.get_aop", false]], "get_aop() (coe method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.get_aop", false]], "get_aop() (tle method)": [[92, "ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE.get_aop", false]], "get_apoapsis_radius() (brouwerlyddanemean method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.get_apoapsis_radius", false]], "get_apoapsis_radius() (brouwerlyddanemeanlong method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.get_apoapsis_radius", false]], "get_apoapsis_radius() (brouwerlyddanemeanshort method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.get_apoapsis_radius", false]], "get_apoapsis_radius() (coe method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.get_apoapsis_radius", false]], "get_attitude() (state method)": [[73, "ostk.astrodynamics.trajectory.State.get_attitude", false]], "get_axes_at() (model method)": [[50, "ostk.astrodynamics.flight.profile.Model.get_axes_at", false]], "get_axes_at() (profile method)": [[47, "ostk.astrodynamics.flight.Profile.get_axes_at", false]], "get_axes_at() (tabulated method)": [[52, "ostk.astrodynamics.flight.profile.model.Tabulated.get_axes_at", false]], "get_axes_at() (transform method)": [[53, "ostk.astrodynamics.flight.profile.model.Transform.get_axes_at", false]], "get_b_star_drag_term() (tle method)": [[92, "ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE.get_b_star_drag_term", false]], "get_body_frame() (model method)": [[50, "ostk.astrodynamics.flight.profile.Model.get_body_frame", false]], "get_body_frame() (profile method)": [[47, "ostk.astrodynamics.flight.Profile.get_body_frame", false]], "get_body_frame() (tabulated method)": [[52, "ostk.astrodynamics.flight.profile.model.Tabulated.get_body_frame", false]], "get_body_frame() (transform method)": [[53, "ostk.astrodynamics.flight.profile.model.Transform.get_body_frame", false]], "get_cartesian_state() (brouwerlyddanemean method)": [[81, "ostk.astrodynamics.trajectory.orbit.model.BrouwerLyddaneMean.get_cartesian_state", false]], "get_cartesian_state() (brouwerlyddanemeanlong method)": [[87, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanLong.get_cartesian_state", false]], "get_cartesian_state() (brouwerlyddanemeanshort method)": [[88, "ostk.astrodynamics.trajectory.orbit.model.brouwerLyddaneMean.BrouwerLyddaneMeanShort.get_cartesian_state", false]], "get_cartesian_state() (coe method)": [[90, "ostk.astrodynamics.trajectory.orbit.model.kepler.COE.get_cartesian_state", false]], "get_ccsds_cdm_version() (cdm method)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.get_ccsds_cdm_version", false]], "get_celestial() (atmosphericdrag method)": [[32, "ostk.astrodynamics.dynamics.AtmosphericDrag.get_celestial", false]], "get_celestial() (centralbodygravity method)": [[33, "ostk.astrodynamics.dynamics.CentralBodyGravity.get_celestial", false]], "get_celestial() (thirdbodygravity method)": [[36, "ostk.astrodynamics.dynamics.ThirdBodyGravity.get_celestial", false]], "get_classical_orbital_elements() (kepler method)": [[82, "ostk.astrodynamics.trajectory.orbit.model.Kepler.get_classical_orbital_elements", false]], "get_classification() (tle method)": [[92, "ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE.get_classification", false]], "get_collision_probability() (cdm method)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.get_collision_probability", false]], "get_collision_probability_method() (cdm method)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.get_collision_probability_method", false]], "get_condition_function() (generator method)": [[9, "ostk.astrodynamics.access.Generator.get_condition_function", false]], "get_contribution_profile_from_coordinate_subsets() (tabulated method)": [[35, "ostk.astrodynamics.dynamics.Tabulated.get_contribution_profile_from_coordinate_subsets", false]], "get_control_weights() (qlaw.parameters method)": [[60, "ostk.astrodynamics.guidance_law.QLaw.Parameters.get_control_weights", false]], "get_coordinate_subsets() (state method)": [[73, "ostk.astrodynamics.trajectory.State.get_coordinate_subsets", false]], "get_coordinate_subsets() (statebuilder method)": [[74, "ostk.astrodynamics.trajectory.StateBuilder.get_coordinate_subsets", false]], "get_coordinates() (state method)": [[73, "ostk.astrodynamics.trajectory.State.get_coordinates", false]], "get_creation_instant() (cdm method)": [[11, "ostk.astrodynamics.conjunction.message.ccsds.CDM.get_creation_instant", false]], "get_criterion() (angularcondition method)": [[39, "ostk.astrodynamics.event_condition.AngularCondition.get_criterion", false]], "get_criterion() (booleancondition method)": [[40, "ostk.astrodynamics.event_condition.BooleanCondition.get_criterion", false]], "get_criterion() (instantcondition method)": [[42, "ostk.astrodynamics.event_condition.InstantCondition.get_criterion", false]], "get_criterion() (realcondition 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diff --git a/_build/html/_images/e9fa94379369910e6951b960eb663b9c39043a2399cc7d16ae7cfd15a226ea65.svg b/_build/jupyter_execute/06c29e4ad2630ddc63a367944d0633cd30498361a708ac7068040706074d8202.svg
similarity index 99%
rename from _build/html/_images/e9fa94379369910e6951b960eb663b9c39043a2399cc7d16ae7cfd15a226ea65.svg
rename to _build/jupyter_execute/06c29e4ad2630ddc63a367944d0633cd30498361a708ac7068040706074d8202.svg
index 7ccedf658..47143e156 100644
--- a/_build/html/_images/e9fa94379369910e6951b960eb663b9c39043a2399cc7d16ae7cfd15a226ea65.svg
+++ b/_build/jupyter_execute/06c29e4ad2630ddc63a367944d0633cd30498361a708ac7068040706074d8202.svg
@@ -1 +1 @@
-
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+
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diff --git a/_build/html/_images/6156a06b98da8747f1993132ee86b2969db2579a8dfabd644f38210523787c98.svg b/_build/jupyter_execute/69a1697a287fb6cf4c98702ee6a4057b6efe55ebc985bea282aa9caf9158b957.svg
similarity index 99%
rename from _build/html/_images/6156a06b98da8747f1993132ee86b2969db2579a8dfabd644f38210523787c98.svg
rename to _build/jupyter_execute/69a1697a287fb6cf4c98702ee6a4057b6efe55ebc985bea282aa9caf9158b957.svg
index f8259a886..50bb56021 100644
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+++ b/_build/jupyter_execute/69a1697a287fb6cf4c98702ee6a4057b6efe55ebc985bea282aa9caf9158b957.svg
@@ -1 +1 @@
-trace 1
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+trace 1
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similarity index 99%
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@@ -1 +1 @@
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+
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diff --git a/_build/jupyter_execute/_notebooks/Access Computation.ipynb b/_build/jupyter_execute/_notebooks/Access Computation.ipynb
index 634fed21e..192634491 100644
--- a/_build/jupyter_execute/_notebooks/Access Computation.ipynb	
+++ b/_build/jupyter_execute/_notebooks/Access Computation.ipynb	
@@ -274,13 +274,7 @@
       "Locking local repository [/var/cache/open-space-toolkit-data/data/manifest]...\n",
       "Fetching Data Manifest from [https://github.com/open-space-collective/open-space-toolkit-data/raw/v1/data/manifest.json]...\n",
       "Unlocking local repository [/var/cache/open-space-toolkit-data/data/manifest]...\n",
-      "Data Manifest [/var/cache/open-space-toolkit-data/data/manifest/manifest.json] has been successfully fetched from [https://github.com/open-space-collective/open-space-toolkit-data/raw/v1/data/manifest.json].\n",
-      "Fetching latest Bulletin A...\n",
-      "Locking local repository [/var/cache/open-space-toolkit-data/data/coordinate/frame/provider/iers]...\n",
-      "Creating temporary directory [/var/cache/open-space-toolkit-data/data/coordinate/frame/provider/iers/bulletin-A/tmp]...\n",
-      "Fetching Bulletin A from [https://github.com/open-space-collective/open-space-toolkit-data/raw/v1/data//coordinate/frame/provider/iers/bulletin-A/ser7.dat]...\n",
-      "Unlocking local repository [/var/cache/open-space-toolkit-data/data/coordinate/frame/provider/iers]...\n",
-      "Bulletin A [/var/cache/open-space-toolkit-data/data/coordinate/frame/provider/iers/bulletin-A/ser7.dat] has been successfully fetched from [https://github.com/open-space-collective/open-space-toolkit-data/raw/v1/data//coordinate/frame/provider/iers/bulletin-A/ser7.dat].\n"
+      "Data Manifest [/var/cache/open-space-toolkit-data/data/manifest/manifest.json] has been successfully fetched from [https://github.com/open-space-collective/open-space-toolkit-data/raw/v1/data/manifest.json].\n"
      ]
     }
    ],
@@ -39362,7 +39356,7 @@
    "name": "python",
    "nbconvert_exporter": "python",
    "pygments_lexer": "ipython3",
-   "version": "3.11.9"
+   "version": "3.11.11"
   }
  },
  "nbformat": 4,
diff --git a/_build/jupyter_execute/_notebooks/Area Coverage.ipynb b/_build/jupyter_execute/_notebooks/Area Coverage.ipynb
index 00ace0615..7376f66cc 100644
--- a/_build/jupyter_execute/_notebooks/Area Coverage.ipynb	
+++ b/_build/jupyter_execute/_notebooks/Area Coverage.ipynb	
@@ -536,13 +536,13 @@
    "outputs": [
     {
      "ename": "TypeError",
-     "evalue": "nadir_pointing(): incompatible function arguments. The following argument types are supported:\n    1. (orbit: ostk.astrodynamics.trajectory.Orbit, orbital_frame_type: ostk.astrodynamics.trajectory.Orbit.FrameType) -> ostk.astrodynamics.flight.Profile\n\nInvoked with: -- Orbit -------------------------------------------------------------------------------------------\n    Model - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - \n    Epoch:                                   2018-09-17 18:34:54.432.768 [UTC]        \n    Two-Line Elements - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - \n----------------------------------------------------------------------------------------------------\n, -- Frame -------------------------------------------------------------------------------------------\n    Name:                                    VVLH @ Orbit [0x29976f0]                 \n    Quasi-inertial:                          false                                    \n    Parent frame:                            GCRF                                     \n----------------------------------------------------------------------------------------------------\n",
+     "evalue": "nadir_pointing(): incompatible function arguments. The following argument types are supported:\n    1. (orbit: ostk.astrodynamics.trajectory.Orbit, orbital_frame_type: ostk.astrodynamics.trajectory.Orbit.FrameType) -> ostk.astrodynamics.flight.Profile\n\nInvoked with: -- Orbit -------------------------------------------------------------------------------------------\n    Model - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - \n    Epoch:                                   2018-09-17 18:34:54.432.768 [UTC]        \n    Two-Line Elements - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - \n----------------------------------------------------------------------------------------------------\n, -- Frame -------------------------------------------------------------------------------------------\n    Name:                                    VVLH @ Orbit [0x2806340]                 \n    Quasi-inertial:                          false                                    \n    Parent frame:                            GCRF                                     \n----------------------------------------------------------------------------------------------------\n",
      "output_type": "error",
      "traceback": [
       "\u001b[0;31m---------------------------------------------------------------------------\u001b[0m",
       "\u001b[0;31mTypeError\u001b[0m                                 Traceback (most recent call last)",
       "Cell \u001b[0;32mIn[19], line 2\u001b[0m\n\u001b[1;32m      1\u001b[0m orbital_frame \u001b[38;5;241m=\u001b[39m satellite_orbit\u001b[38;5;241m.\u001b[39mget_orbital_frame(Orbit\u001b[38;5;241m.\u001b[39mFrameType\u001b[38;5;241m.\u001b[39mVVLH)\n\u001b[0;32m----> 2\u001b[0m orbital_profile \u001b[38;5;241m=\u001b[39m \u001b[43mProfile\u001b[49m\u001b[38;5;241;43m.\u001b[39;49m\u001b[43mnadir_pointing\u001b[49m\u001b[43m(\u001b[49m\u001b[43msatellite_orbit\u001b[49m\u001b[43m,\u001b[49m\u001b[43m \u001b[49m\u001b[43morbital_frame\u001b[49m\u001b[43m)\u001b[49m\n\u001b[1;32m      3\u001b[0m \u001b[38;5;28;01mif\u001b[39;00m Frame\u001b[38;5;241m.\u001b[39mexists(\u001b[38;5;124m\"\u001b[39m\u001b[38;5;124mBody\u001b[39m\u001b[38;5;124m\"\u001b[39m):\n\u001b[1;32m      4\u001b[0m     Frame\u001b[38;5;241m.\u001b[39mdestruct(\u001b[38;5;124m\"\u001b[39m\u001b[38;5;124mBody\u001b[39m\u001b[38;5;124m\"\u001b[39m)\n",
-      "\u001b[0;31mTypeError\u001b[0m: nadir_pointing(): incompatible function arguments. The following argument types are supported:\n    1. (orbit: ostk.astrodynamics.trajectory.Orbit, orbital_frame_type: ostk.astrodynamics.trajectory.Orbit.FrameType) -> ostk.astrodynamics.flight.Profile\n\nInvoked with: -- Orbit -------------------------------------------------------------------------------------------\n    Model - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - \n    Epoch:                                   2018-09-17 18:34:54.432.768 [UTC]        \n    Two-Line Elements - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - \n----------------------------------------------------------------------------------------------------\n, -- Frame -------------------------------------------------------------------------------------------\n    Name:                                    VVLH @ Orbit [0x29976f0]                 \n    Quasi-inertial:                          false                                    \n    Parent frame:                            GCRF                                     \n----------------------------------------------------------------------------------------------------\n"
+      "\u001b[0;31mTypeError\u001b[0m: nadir_pointing(): incompatible function arguments. The following argument types are supported:\n    1. (orbit: ostk.astrodynamics.trajectory.Orbit, orbital_frame_type: ostk.astrodynamics.trajectory.Orbit.FrameType) -> ostk.astrodynamics.flight.Profile\n\nInvoked with: -- Orbit -------------------------------------------------------------------------------------------\n    Model - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - \n    Epoch:                                   2018-09-17 18:34:54.432.768 [UTC]        \n    Two-Line Elements - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - \n----------------------------------------------------------------------------------------------------\n, -- Frame -------------------------------------------------------------------------------------------\n    Name:                                    VVLH @ Orbit [0x2806340]                 \n    Quasi-inertial:                          false                                    \n    Parent frame:                            GCRF                                     \n----------------------------------------------------------------------------------------------------\n"
      ]
     }
    ],
@@ -1159,7 +1159,7 @@
    "name": "python",
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index d7e2cc1af..009fb60ee 100644
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index 5b5daed2d..b99304af5 100644
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index dd3167a5c..7efcd771f 100644
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index 3063b7722..5f52aa28b 100644
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index f423db200..b376a8301 100644
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index de9fcfea8..3992fa4be 100644
--- a/_build/jupyter_execute/_notebooks/OSTk Cross Platform Validation (Mission Sequence Scenario 1).ipynb	
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index b96934eba..c9937df42 100644
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index 27fb04685..24eac4e45 100644
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index d03ce5691..6afae906d 100644
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index e4533fbc5..071d11a42 100644
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       "-- Segment -----------------------------------------------------------------------------------------\n",
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diff --git a/_notebooks/render.html b/_notebooks/render.html
index f9e1c04ec..bd4339d9a 100644
--- a/_notebooks/render.html
+++ b/_notebooks/render.html
@@ -7,28 +7,28 @@
   async function init() {
     Cesium.Ion.defaultAccessToken = "eyJhbGciOiJIUzI1NiIsInR5cCI6IkpXVCJ9.eyJqdGkiOiJlYmYyODhkOS1jNDY5LTQ0NTUtOWNlZi0zMDhjNjE1NDY2OTUiLCJpZCI6NzE4ODUsImlhdCI6MTYzNTUzNzc1Mn0.YQiV6xUFOiEhdQ-w3Dmgy1XYZogK5dclhn7X0U6i7Oo";
     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("2024-01-01T15:08:42.062272+00:00"), stopTime: Cesium.JulianDate.fromIso8601("2024-01-01T15:09:59.522054+00:00"), clockRange: Cesium.ClockRange.CLAMPED, canAnimate: true, shouldAnimate: false}))});
-    widget.property_3fae4706 = new Cesium.SampledProperty(Cesium.Cartesian3);
-    widget.property_3fae4706.addSample("2024-01-01T15:08:42.062272+00:00", Cesium.Cartesian3.fromDegrees(-9.137930271362766, 4.362430553709083, 550122.7669634694));
-    widget.property_3fae4706.addSample("2024-01-01T15:08:52.062272+00:00", Cesium.Cartesian3.fromDegrees(-9.261797647382496, 3.737522066100169, 550090.1591987774));
-    widget.property_3fae4706.addSample("2024-01-01T15:09:02.062272+00:00", Cesium.Cartesian3.fromDegrees(-9.38554923641237, 3.112594977378538, 550062.5564545575));
-    widget.property_3fae4706.addSample("2024-01-01T15:09:12.062272+00:00", Cesium.Cartesian3.fromDegrees(-9.509204704154577, 2.4876524003059486, 550039.9721058706));
-    widget.property_3fae4706.addSample("2024-01-01T15:09:22.062272+00:00", Cesium.Cartesian3.fromDegrees(-9.63278362632062, 1.8626974463482582, 550022.4170964456));
-    widget.property_3fae4706.addSample("2024-01-01T15:09:32.062272+00:00", Cesium.Cartesian3.fromDegrees(-9.756305002611578, 1.237733225954018, 550009.8999331509));
-    widget.property_3fae4706.addSample("2024-01-01T15:09:42.062272+00:00", Cesium.Cartesian3.fromDegrees(-9.879788283453337, 0.6127628488178318, 550002.426681713));
-    widget.property_3fae4706.addSample("2024-01-01T15:09:52.062272+00:00", Cesium.Cartesian3.fromDegrees(-10.003252883728202, -0.01221057585955051, 550000.0009636492));
-    widget.property_3fae4706.addSample("2024-01-01T15:09:59.522054+00:00", Cesium.Cartesian3.fromDegrees(-10.095353742010236, -0.47842726730938373, 550001.47933361));
-    widget.property_95af224b = new Cesium.SampledProperty(Cesium.Quaternion);
-    widget.property_95af224b.addSample("2024-01-01T15:08:42.062272+00:00", new Cesium.Quaternion(-0.7745270532877749, 0.3201986758532946, 0.3818494147296324, 0.3895788446229985));
-    widget.property_95af224b.addSample("2024-01-01T15:08:52.062272+00:00", new Cesium.Quaternion(-0.7458551025950836, 0.345047316946292, 0.41423862756603663, 0.39121461428894616));
-    widget.property_95af224b.addSample("2024-01-01T15:09:02.062272+00:00", new Cesium.Quaternion(-0.7140832164841817, 0.370529995190869, 0.44861698019482715, 0.389275593481449));
-    widget.property_95af224b.addSample("2024-01-01T15:09:12.062272+00:00", new Cesium.Quaternion(-0.6793714639520361, 0.3958062568935332, 0.48449460978147424, 0.38347984831578186));
-    widget.property_95af224b.addSample("2024-01-01T15:09:22.062272+00:00", new Cesium.Quaternion(-0.6421430497278803, 0.41986389309274663, 0.5211727859974736, 0.37382555035579307));
-    widget.property_95af224b.addSample("2024-01-01T15:09:32.062272+00:00", new Cesium.Quaternion(-0.6030953858636139, 0.44164915680270034, 0.5578119184712468, 0.3606491944492734));
-    widget.property_95af224b.addSample("2024-01-01T15:09:42.062272+00:00", new Cesium.Quaternion(-0.5631387153775337, 0.4602383932243905, 0.5935492691157129, 0.34460800016449944));
-    widget.property_95af224b.addSample("2024-01-01T15:09:52.062272+00:00", new Cesium.Quaternion(-0.5232686870952316, 0.47499264150157017, 0.6276290281636949, 0.32657874185453295));
-    widget.property_95af224b.addSample("2024-01-01T15:09:59.522054+00:00", new Cesium.Quaternion(-0.49414348424426224, 0.48332441215715466, 0.6516334860509023, 0.3123996310001508));
-    widget.entities.add({position: widget.property_3fae4706, orientation: widget.property_95af224b, model: {uri: await Cesium.IonResource.fromAssetId(1359555), availability: new Cesium.TimeIntervalCollection({intervals: [new Cesium.TimeInterval({start: Cesium.JulianDate.fromIso8601("2024-01-01T15:08:42.062272+00:00"), stop: Cesium.JulianDate.fromIso8601("2024-01-01T15:09:59.522054+00:00")})]})}});
-    widget.entities.add({polyline: {positions: Cesium.Cartesian3.fromDegreesArrayHeights([-9.137930271362766, 4.362430553709083, 550122.7669634694, -9.261797647382496, 3.737522066100169, 550090.1591987774, -9.38554923641237, 3.112594977378538, 550062.5564545575, -9.509204704154577, 2.4876524003059486, 550039.9721058706, -9.63278362632062, 1.8626974463482582, 550022.4170964456, -9.756305002611578, 1.237733225954018, 550009.8999331509, -9.879788283453337, 0.6127628488178318, 550002.426681713, -10.003252883728202, -0.01221057585955051, 550000.0009636492, -10.095353742010236, -0.47842726730938373, 550001.47933361]), width: 1.0}});
+    widget.property_3f09a5ab = new Cesium.SampledProperty(Cesium.Cartesian3);
+    widget.property_3f09a5ab.addSample("2024-01-01T15:08:42.062272+00:00", Cesium.Cartesian3.fromDegrees(-9.137930272185047, 4.362430553737098, 550122.7669634755));
+    widget.property_3f09a5ab.addSample("2024-01-01T15:08:52.062272+00:00", Cesium.Cartesian3.fromDegrees(-9.261797648205023, 3.7375220661285726, 550090.1591987855));
+    widget.property_3f09a5ab.addSample("2024-01-01T15:09:02.062272+00:00", Cesium.Cartesian3.fromDegrees(-9.385549237240038, 3.1125949774073116, 550062.5564545591));
+    widget.property_3f09a5ab.addSample("2024-01-01T15:09:12.062272+00:00", Cesium.Cartesian3.fromDegrees(-9.509204704984114, 2.4876524003351057, 550039.972105868));
+    widget.property_3f09a5ab.addSample("2024-01-01T15:09:22.062272+00:00", Cesium.Cartesian3.fromDegrees(-9.632783627150436, 1.8626974463777943, 550022.4170964444));
+    widget.property_3f09a5ab.addSample("2024-01-01T15:09:32.062272+00:00", Cesium.Cartesian3.fromDegrees(-9.756305003443265, 1.2377332259839398, 550009.8999331556));
+    widget.property_3f09a5ab.addSample("2024-01-01T15:09:42.062272+00:00", Cesium.Cartesian3.fromDegrees(-9.87978828428689, 0.6127628488481233, 550002.4266817163));
+    widget.property_3f09a5ab.addSample("2024-01-01T15:09:52.062272+00:00", Cesium.Cartesian3.fromDegrees(-10.003252884566892, -0.012210575828876516, 550000.0009636488));
+    widget.property_3f09a5ab.addSample("2024-01-01T15:09:59.522054+00:00", Cesium.Cartesian3.fromDegrees(-10.095353742848685, -0.4784272672784221, 550001.4793336083));
+    widget.property_ccf162ea = new Cesium.SampledProperty(Cesium.Quaternion);
+    widget.property_ccf162ea.addSample("2024-01-01T15:08:42.062272+00:00", new Cesium.Quaternion(-0.7745270532731057, 0.32019867587153694, 0.3818494147302193, 0.38957884463659437));
+    widget.property_ccf162ea.addSample("2024-01-01T15:08:52.062272+00:00", new Cesium.Quaternion(-0.7458551025801965, 0.34504731696437685, 0.41423862756624874, 0.3912146143011534));
+    widget.property_ccf162ea.addSample("2024-01-01T15:09:02.062272+00:00", new Cesium.Quaternion(-0.7140832164691815, 0.3705299952086629, 0.44861698019448293, 0.3892755934924248));
+    widget.property_ccf162ea.addSample("2024-01-01T15:09:12.062272+00:00", new Cesium.Quaternion(-0.6793714639372284, 0.395806256910742, 0.4844946097803658, 0.38347984832565335));
+    widget.property_ccf162ea.addSample("2024-01-01T15:09:22.062272+00:00", new Cesium.Quaternion(-0.6421430497135727, 0.4198638931091663, 0.52117278599541, 0.37382555036480486));
+    widget.property_ccf162ea.addSample("2024-01-01T15:09:32.062272+00:00", new Cesium.Quaternion(-0.6030953858500578, 0.4416491568182824, 0.5578119184680776, 0.36064919445776256));
+    widget.property_ccf162ea.addSample("2024-01-01T15:09:42.062272+00:00", new Cesium.Quaternion(-0.5631387153649707, 0.4602383932391689, 0.5935492691113625, 0.3446080001727855));
+    widget.property_ccf162ea.addSample("2024-01-01T15:09:52.062272+00:00", new Cesium.Quaternion(-0.5232686870837849, 0.4749926415157336, 0.6276290281581541, 0.32657874186292196));
+    widget.property_ccf162ea.addSample("2024-01-01T15:09:59.522054+00:00", new Cesium.Quaternion(-0.49414348423376403, 0.48332441217092914, 0.6516334860445472, 0.3123996310087014));
+    widget.entities.add({position: widget.property_3f09a5ab, orientation: widget.property_ccf162ea, model: {uri: await Cesium.IonResource.fromAssetId(1359555), availability: new Cesium.TimeIntervalCollection({intervals: [new Cesium.TimeInterval({start: Cesium.JulianDate.fromIso8601("2024-01-01T15:08:42.062272+00:00"), stop: Cesium.JulianDate.fromIso8601("2024-01-01T15:09:59.522054+00:00")})]})}});
+    widget.entities.add({polyline: {positions: Cesium.Cartesian3.fromDegreesArrayHeights([-9.137930272185047, 4.362430553737098, 550122.7669634755, -9.261797648205023, 3.7375220661285726, 550090.1591987855, -9.385549237240038, 3.1125949774073116, 550062.5564545591, -9.509204704984114, 2.4876524003351057, 550039.972105868, -9.632783627150436, 1.8626974463777943, 550022.4170964444, -9.756305003443265, 1.2377332259839398, 550009.8999331556, -9.87978828428689, 0.6127628488481233, 550002.4266817163, -10.003252884566892, -0.012210575828876516, 550000.0009636488, -10.095353742848685, -0.4784272672784221, 550001.4793336083]), width: 1.0}});
     widget.entities.add({position: Cesium.Cartesian3.fromDegrees(0.0, 0.0, 9.999999999622059), point: {pixelSize: 10.0, color: Cesium.Color.RED}});
     widget.zoomTo(widget.entities);
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diff --git a/dev/bench/data.js b/dev/bench/data.js
deleted file mode 100644
index 6c463be6c..000000000
--- a/dev/bench/data.js
+++ /dev/null
@@ -1,170 +0,0 @@
-window.BENCHMARK_DATA = {
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-  "repoUrl": "https://github.com/open-space-collective/open-space-toolkit-astrodynamics",
-  "entries": {
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-            "name": "Vishwa Shah",
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-          "message": "fix: startup script for jupyter (#471)",
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-          "tree_id": "0eedb04296dcfccf31bfc6f28cffa4034c5f4421",
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-            "name": "Propagation | Numerical | EGM2008 {100, 100}/iterations:10",
-            "value": 3196785188.400008,
-            "unit": "ns/iter",
-            "extra": "iterations: 10\ncpu: 3196688772.7999988 ns\nthreads: 1"
-          }
-        ]
-      },
-      {
-        "commit": {
-          "author": {
-            "email": "35860220+alex-liang3@users.noreply.github.com",
-            "name": "Alex Liang",
-            "username": "alex-liang3"
-          },
-          "committer": {
-            "email": "noreply@github.com",
-            "name": "GitHub",
-            "username": "web-flow"
-          },
-          "distinct": true,
-          "id": "6956a4e18fabf2a52c0b3aafc7efc7dbc5ef3eb2",
-          "message": "feat: frozen orbit conditions (#473)\n\n* feat: add method to get coe for frozen orbit\r\n\r\n* feat: add frozen Orbit constructor\r\n\r\n* test: add coe gtest\r\n\r\n* chore: improve error handling\r\n\r\n* refactor: make re, j2, and j3 args\r\n\r\n* test: add tests for orbit\r\n\r\n* chore: bump ostk-physics dependency version\r\n\r\n* test: add python tests\r\n\r\n* perf: loosen criticality requirement\r\n\r\n* style: use camelCase\r\n\r\n* style: add units and long for to var names\r\n\r\n* style: make lambda captures explicit\r\n\r\n* perf: use ostk Arrays\r\n\r\n* test: add more tests\r\n\r\n* doc: add more documentation\r\n\r\n* test: improve tests\r\n\r\n* doc: add docs for Orbit constructor\r\n\r\n* feat: add overloaded ctor for COE\r\n\r\n* test: add test for ctor with Celestial\r\n\r\n* test: add python test\r\n\r\n* perf: use reference\r\n\r\n* chore: fix typos\r\n\r\n* doc: add doc to orbit.hpp\r\n\r\n* test: add negative tests for celestial ctor",
-          "timestamp": "2024-12-17T13:50:49-03:00",
-          "tree_id": "b9713c32b18cb97e6bdc8dc001a4df72f7762185",
-          "url": "https://github.com/open-space-collective/open-space-toolkit-astrodynamics/commit/6956a4e18fabf2a52c0b3aafc7efc7dbc5ef3eb2"
-        },
-        "date": 1734455480354,
-        "tool": "googlecpp",
-        "benches": [
-          {
-            "name": "Access | Ground Station <> TLE/iterations:10",
-            "value": 584720371.7999946,
-            "unit": "ns/iter",
-            "extra": "iterations: 10\ncpu: 584694399.8999999 ns\nthreads: 1"
-          },
-          {
-            "name": "Propagation | Numerical | Spherical/iterations:10",
-            "value": 881762585.0999889,
-            "unit": "ns/iter",
-            "extra": "iterations: 10\ncpu: 881722342.2000002 ns\nthreads: 1"
-          },
-          {
-            "name": "Propagation | Numerical | EGM1984 {100, 100}/iterations:10",
-            "value": 3175390347.0000067,
-            "unit": "ns/iter",
-            "extra": "iterations: 10\ncpu: 3175295313.600001 ns\nthreads: 1"
-          },
-          {
-            "name": "Propagation | Numerical | EGM1996 {100, 100}/iterations:10",
-            "value": 3174495148.300002,
-            "unit": "ns/iter",
-            "extra": "iterations: 10\ncpu: 3174368380.999999 ns\nthreads: 1"
-          },
-          {
-            "name": "Propagation | Numerical | EGM2008 {100, 100}/iterations:10",
-            "value": 3175764644.300011,
-            "unit": "ns/iter",
-            "extra": "iterations: 10\ncpu: 3175667149.8999968 ns\nthreads: 1"
-          }
-        ]
-      },
-      {
-        "commit": {
-          "author": {
-            "email": "35860220+alex-liang3@users.noreply.github.com",
-            "name": "Alex Liang",
-            "username": "alex-liang3"
-          },
-          "committer": {
-            "email": "noreply@github.com",
-            "name": "GitHub",
-            "username": "web-flow"
-          },
-          "distinct": true,
-          "id": "84816150be89cca9f52929306466e147990db9b3",
-          "message": "docs: clarify altitude definition in Orbit constructors (#475)\n\ndoc: clarify altitude definition in Orbit ctors",
-          "timestamp": "2024-12-18T11:28:38+01:00",
-          "tree_id": "db8e00e55ad6fe506767b9457b42a5dd467304c2",
-          "url": "https://github.com/open-space-collective/open-space-toolkit-astrodynamics/commit/84816150be89cca9f52929306466e147990db9b3"
-        },
-        "date": 1734518764637,
-        "tool": "googlecpp",
-        "benches": [
-          {
-            "name": "Access | Ground Station <> TLE/iterations:10",
-            "value": 583768593.700006,
-            "unit": "ns/iter",
-            "extra": "iterations: 10\ncpu: 583730880.0000001 ns\nthreads: 1"
-          },
-          {
-            "name": "Propagation | Numerical | Spherical/iterations:10",
-            "value": 888723954.0999985,
-            "unit": "ns/iter",
-            "extra": "iterations: 10\ncpu: 888686518.8999999 ns\nthreads: 1"
-          },
-          {
-            "name": "Propagation | Numerical | EGM1984 {100, 100}/iterations:10",
-            "value": 3184520978.800026,
-            "unit": "ns/iter",
-            "extra": "iterations: 10\ncpu: 3184384983.400001 ns\nthreads: 1"
-          },
-          {
-            "name": "Propagation | Numerical | EGM1996 {100, 100}/iterations:10",
-            "value": 3181799061.9000173,
-            "unit": "ns/iter",
-            "extra": "iterations: 10\ncpu: 3181680421.199998 ns\nthreads: 1"
-          },
-          {
-            "name": "Propagation | Numerical | EGM2008 {100, 100}/iterations:10",
-            "value": 3186331568.2999883,
-            "unit": "ns/iter",
-            "extra": "iterations: 10\ncpu: 3186055682.699998 ns\nthreads: 1"
-          }
-        ]
-      }
-    ]
-  }
-}
\ No newline at end of file
diff --git a/dev/bench/index.html b/dev/bench/index.html
deleted file mode 100644
index 6c887805e..000000000
--- a/dev/bench/index.html
+++ /dev/null
@@ -1,281 +0,0 @@
-
-
-  
-    
-    
-    
-    Benchmarks
-  
-
-  
-    
-    

-    
-
-    
-    
-    
-  
-
diff --git a/xml/_c_o_e_8cpp.xml b/xml/_c_o_e_8cpp.xml
index 35c5064cb..d781f5c47 100644
--- a/xml/_c_o_e_8cpp.xml
+++ b/xml/_c_o_e_8cpp.xml
@@ -152,1045 +152,1199 @@
 namespacekepler
 {
 
-usingostk::core::type::Integer;
-usingostk::core::type::Real;
-usingostk::core::type::Shared;
-usingostk::core::type::Size;
-usingostk::core::type::String;
-
-usingostk::mathematics::geometry::d3::transformation::rotation::RotationMatrix;
-usingostk::mathematics::object::Vector3d;
-
-usingostk::physics::time::Scale;
-usingostk::physics::unit::Angle;
-usingostk::physics::unit::Derived;
-usingostk::physics::unit::ElectricCurrent;
-usingostk::physics::unit::Length;
-usingostk::physics::unit::Mass;
-usingTimeUnit=ostk::physics::unit::Time;
-usingEarthGravitationalModel=ostk::physics::environment::gravitational::Earth;
-
-staticconstRealTolerance=1e-30;
-staticconstDerived::UnitGravitationalParameterSIUnit=Derived::Unit::MeterCubedPerSecondSquared();
-staticconstDerived::UnitangularVelocitySIUnit=Derived::Unit::RadianPerSecond();
-staticconstDerived::UnitAngularMomentumSIUnit={
-Length::Unit::Meter,
-{2},
-Mass::Unit::Kilogram,
-{1},
-TimeUnit::Unit::Second,
-{-2},
-ElectricCurrent::Unit::Undefined,
-{0},
-Angle::Unit::Undefined,
-{0},
-};
-
-COE::COE(
-constLength&aSemiMajorAxis,
-constReal&anEccentricity,
-constAngle&anInclination,
-constAngle&aRaan,
-constAngle&anAop,
-constAngle&aTrueAnomaly
-)
-:semiMajorAxis_(aSemiMajorAxis),
-eccentricity_(anEccentricity),
-inclination_(anInclination),
-raan_(aRaan),
-aop_(anAop),
-anomaly_(aTrueAnomaly),
-anomalyType_(COE::AnomalyType::True)
-{
-}
-
-boolCOE::operator==(constCOE&aCOE)const
-{
-if((!this->isDefined())||(!aCOE.isDefined()))
-{
-returnfalse;
-}
-
-return(semiMajorAxis_==aCOE.semiMajorAxis_)&&(eccentricity_==aCOE.eccentricity_)&&
-(inclination_==aCOE.inclination_)&&(raan_==aCOE.raan_)&&(aop_==aCOE.aop_)&&
-(anomaly_==aCOE.anomaly_)&&(anomalyType_==aCOE.anomalyType_);
-}
-
-boolCOE::operator!=(constCOE&aCOE)const
-{
-return!((*this)==aCOE);
-}
-
-std::ostream&operator<<(std::ostream&anOutputStream,constCOE&aCOE)
-{
-aCOE.print(anOutputStream);
-
-returnanOutputStream;
-}
-
-boolCOE::isDefined()const
-{
-returnsemiMajorAxis_.isDefined()&&eccentricity_.isDefined()&&inclination_.isDefined()&&raan_.isDefined()&&
-aop_.isDefined()&&anomaly_.isDefined();
-}
-
-LengthCOE::getSemiMajorAxis()const
-{
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-returnsemiMajorAxis_;
-}
-
-RealCOE::getEccentricity()const
-{
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-returneccentricity_;
-}
-
-AngleCOE::getInclination()const
-{
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-returninclination_;
-}
-
-AngleCOE::getRaan()const
-{
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-returnraan_;
-}
-
-AngleCOE::getAop()const
-{
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-returnaop_;
-}
-
-AngleCOE::getTrueAnomaly()const
-{
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-returnanomaly_;
-}
-
-AngleCOE::getMeanAnomaly()const
-{
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-returnCOE::MeanAnomalyFromEccentricAnomaly(this->getEccentricAnomaly(),eccentricity_);
-}
-
-AngleCOE::getEccentricAnomaly()const
-{
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-returnCOE::EccentricAnomalyFromTrueAnomaly(anomaly_,eccentricity_);
-}
-
-LengthCOE::getPeriapsisRadius()const
-{
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-returnthis->semiMajorAxis_*(1.0-this->eccentricity_);
-}
-
-LengthCOE::getApoapsisRadius()const
-{
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-returnthis->semiMajorAxis_*(1.0+this->eccentricity_);
-}
-
-LengthCOE::getSemiLatusRectum()const
-{
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-returnLength::Meters(COE::ComputeSemiLatusRectum(semiMajorAxis_.inMeters(),eccentricity_));
-}
-
-LengthCOE::getRadialDistance()const
-{
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-returnLength::Meters(COE::ComputeRadialDistance(
-semiMajorAxis_.inMeters(),
-eccentricity_,
-COE::ConvertAnomaly(anomaly_,eccentricity_,anomalyType_,AnomalyType::True,1e-12).inRadians()
-));
-}
-
-DerivedCOE::getAngularMomentum(constDerived&aGravitationalParameter)const
-{
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-returnDerived(
-COE::ComputeAngularMomentum(
-COE::ComputeSemiLatusRectum(semiMajorAxis_.inMeters(),eccentricity_),aGravitationalParameter
-),
-AngularMomentumSIUnit
-);
-}
-
-DerivedCOE::getMeanMotion(constDerived&aGravitationalParameter)const
-{
-if(!aGravitationalParameter.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Gravitationalparameter");
-}
-
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-constRealsemiMajorAxis_m=semiMajorAxis_.inMeters();
-
-constRealgravitationalParameter_SI=aGravitationalParameter.in(GravitationalParameterSIUnit);
-
-returnDerived(
-std::sqrt(gravitationalParameter_SI/(semiMajorAxis_m*semiMajorAxis_m*semiMajorAxis_m)),
-angularVelocitySIUnit
-);
-}
-
-DerivedCOE::getNodalPrecessionRate(
-constDerived&aGravitationalParameter,constLength&anEquatorialRadius,constReal&aJ2Parameter
-)const
-{
-constRealomega=this->getMeanMotion(aGravitationalParameter).in(angularVelocitySIUnit);
-
-constRealomega_p=
--(3.0/2.0)*std::pow(anEquatorialRadius.inMeters(),2.0)*aJ2Parameter*omega*
-std::cos(this->inclination_.inRadians())/
-std::pow(this->semiMajorAxis_.inMeters()*(1.0-(this->eccentricity_*this->eccentricity_)),2.0);
-
-returnDerived(omega_p,angularVelocitySIUnit);
-}
-
-DurationCOE::getOrbitalPeriod(constDerived&aGravitationalParameter)const
-{
-if(!aGravitationalParameter.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Gravitationalparameter");
-}
-
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-returnDuration::Seconds(Real::TwoPi()/this->getMeanMotion(aGravitationalParameter).in(angularVelocitySIUnit));
-}
-
-COE::CartesianStateCOE::getCartesianState(
-constDerived&aGravitationalParameter,constShared<constFrame>&aFrameSPtr
-)const
-{
-if(!aGravitationalParameter.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Gravitationalparameter");
-}
-
-if((aFrameSPtr==nullptr)||(!aFrameSPtr->isDefined()))
-{
-throwostk::core::error::runtime::Undefined("Frame");
-}
-
-if(!this->isDefined())
-{
-throwostk::core::error::runtime::Undefined("COE");
-}
-
-constReala_m=semiMajorAxis_.inMeters();
-constRealinclination_rad=inclination_.inRadians();
-constRealraan_rad=raan_.inRadians();
-constRealaop_rad=aop_.inRadians();
-constRealnu_rad=anomaly_.inRadians();
-constRealmu_SI=aGravitationalParameter.in(GravitationalParameterSIUnit);
-
-constRealp_m=a_m*(1.0-eccentricity_*eccentricity_);
-
-constVector3dR_pqw={
-p_m*std::cos(nu_rad)/(1.0+eccentricity_*std::cos(nu_rad)),
-p_m*std::sin(nu_rad)/(1.0+eccentricity_*std::cos(nu_rad)),
-0.0,
-};
-
-constVector3dV_pqw={
--std::sqrt(mu_SI/p_m)*std::sin(nu_rad),
-+std::sqrt(mu_SI/p_m)*(eccentricity_+std::cos(nu_rad)),
-0.0,
-};
-
-try
-{
-constVector3dx_ECI=RotationMatrix::RZ(Angle::Radians(-raan_rad))*
-RotationMatrix::RX(Angle::Radians(-inclination_rad))*
-RotationMatrix::RZ(Angle::Radians(-aop_rad))*R_pqw;
-constVector3dv_ECI=RotationMatrix::RZ(Angle::Radians(-raan_rad))*
-RotationMatrix::RX(Angle::Radians(-inclination_rad))*
-RotationMatrix::RZ(Angle::Radians(-aop_rad))*V_pqw;
-
-constPositionposition=Position::Meters(x_ECI,aFrameSPtr);
-constVelocityvelocity=Velocity::MetersPerSecond(v_ECI,aFrameSPtr);
-
-return{
-position,
-velocity,
-};
-}
-catch(constostk::core::error::Exception&anException)
-{
-std::cout<<"raan_rad="<<raan_rad<<std::endl;
-std::cout<<"inclination_rad="<<inclination_rad<<std::endl;
-std::cout<<"aop_rad="<<aop_rad<<std::endl;
-std::cout<<"R_pqw="<<R_pqw<<std::endl;
-std::cout<<"V_pqw="<<V_pqw<<std::endl;
-
-throwanException;
-}
-}
-
-Vector6dCOE::getSIVector(constCOE::AnomalyType&anAnomalyType)const
-{
-return{
-semiMajorAxis_.inMeters(),
-eccentricity_,
-inclination_.inRadians(),
-raan_.inRadians(),
-aop_.inRadians(),
-COE::ConvertAnomaly(anomaly_,eccentricity_,AnomalyType::True,anAnomalyType,1e-12).inRadians(),
-};
-}
-
-voidCOE::print(std::ostream&anOutputStream,booldisplayDecorator)const
-{
-displayDecorator?ostk::core::utils::Print::Header(anOutputStream,"ClassicalOrbitalElements"):void();
-
-ostk::core::utils::Print::Line(anOutputStream)
-<<"Semi-majoraxis:"
-<<(semiMajorAxis_.isDefined()?String::Format("{}[m]",semiMajorAxis_.inMeters().toString()):"Undefined");
-ostk::core::utils::Print::Line(anOutputStream)
-<<"Eccentricity:"<<(eccentricity_.isDefined()?eccentricity_.toString():"Undefined");
-ostk::core::utils::Print::Line(anOutputStream)
-<<"Inclination:"
-<<(inclination_.isDefined()?String::Format("{}[deg]",inclination_.inDegrees(0.0,360.0).toString())
-:"Undefined");
-ostk::core::utils::Print::Line(anOutputStream)
-<<"Rightascensionoftheascendingnode:"
-<<(raan_.isDefined()?String::Format("{}[deg]",raan_.inDegrees(0.0,360.0).toString()):"Undefined");
-ostk::core::utils::Print::Line(anOutputStream)
-<<"Argumentofperiapsis:"
-<<(aop_.isDefined()?String::Format("{}[deg]",aop_.inDegrees(0.0,360.0).toString()):"Undefined");
-StringanomalyType=String::Empty();
-switch(anomalyType_)
-{
-caseCOE::AnomalyType::True:
-anomalyType="True";
-break;
-caseCOE::AnomalyType::Mean:
-anomalyType="Mean";
-break;
-caseCOE::AnomalyType::Eccentric:
-anomalyType="Eccentric";
-break;
-default:
-throwostk::core::error::runtime::Wrong("Anomalytype");
-}
-ostk::core::utils::Print::Line(anOutputStream)
-<<String::Format("{}anomaly:",anomalyType)
-<<(anomaly_.isDefined()?String::Format("{}[deg]",anomaly_.inDegrees(0.0,360.0).toString()):"Undefined");
-
-displayDecorator?ostk::core::utils::Print::Footer(anOutputStream):void();
-}
-
-COECOE::Undefined()
-{
-return{
-Length::Undefined(),
-Real::Undefined(),
-Angle::Undefined(),
+usingostk::core::type::Array;
+usingostk::core::type::Integer;
+usingostk::core::type::Real;
+usingostk::core::type::Shared;
+usingostk::core::type::Size;
+usingostk::core::type::String;
+
+usingostk::mathematics::geometry::d3::transformation::rotation::RotationMatrix;
+usingostk::mathematics::object::Vector3d;
+
+usingostk::physics::time::Scale;
+usingostk::physics::unit::Angle;
+usingostk::physics::unit::Derived;
+usingostk::physics::unit::ElectricCurrent;
+usingostk::physics::unit::Length;
+usingostk::physics::unit::Mass;
+usingTimeUnit=ostk::physics::unit::Time;
+usingEarthGravitationalModel=ostk::physics::environment::gravitational::Earth;
+
+staticconstRealTolerance=1e-30;
+staticconstDerived::UnitGravitationalParameterSIUnit=Derived::Unit::MeterCubedPerSecondSquared();
+staticconstDerived::UnitangularVelocitySIUnit=Derived::Unit::RadianPerSecond();
+staticconstDerived::UnitAngularMomentumSIUnit={
+Length::Unit::Meter,
+{2},
+Mass::Unit::Kilogram,
+{1},
+TimeUnit::Unit::Second,
+{-2},
+ElectricCurrent::Unit::Undefined,
+{0},
+Angle::Unit::Undefined,
+{0},
+};
+
+COE::COE(
+constLength&aSemiMajorAxis,
+constReal&anEccentricity,
+constAngle&anInclination,
+constAngle&aRaan,
+constAngle&anAop,
+constAngle&aTrueAnomaly
+)
+:semiMajorAxis_(aSemiMajorAxis),
+eccentricity_(anEccentricity),
+inclination_(anInclination),
+raan_(aRaan),
+aop_(anAop),
+anomaly_(aTrueAnomaly),
+anomalyType_(COE::AnomalyType::True)
+{
+}
+
+boolCOE::operator==(constCOE&aCOE)const
+{
+if((!this->isDefined())||(!aCOE.isDefined()))
+{
+returnfalse;
+}
+
+return(semiMajorAxis_==aCOE.semiMajorAxis_)&&(eccentricity_==aCOE.eccentricity_)&&
+(inclination_==aCOE.inclination_)&&(raan_==aCOE.raan_)&&(aop_==aCOE.aop_)&&
+(anomaly_==aCOE.anomaly_)&&(anomalyType_==aCOE.anomalyType_);
+}
+
+boolCOE::operator!=(constCOE&aCOE)const
+{
+return!((*this)==aCOE);
+}
+
+std::ostream&operator<<(std::ostream&anOutputStream,constCOE&aCOE)
+{
+aCOE.print(anOutputStream);
+
+returnanOutputStream;
+}
+
+boolCOE::isDefined()const
+{
+returnsemiMajorAxis_.isDefined()&&eccentricity_.isDefined()&&inclination_.isDefined()&&raan_.isDefined()&&
+aop_.isDefined()&&anomaly_.isDefined();
+}
+
+LengthCOE::getSemiMajorAxis()const
+{
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+returnsemiMajorAxis_;
+}
+
+RealCOE::getEccentricity()const
+{
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+returneccentricity_;
+}
+
+AngleCOE::getInclination()const
+{
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+returninclination_;
+}
+
+AngleCOE::getRaan()const
+{
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+returnraan_;
+}
+
+AngleCOE::getAop()const
+{
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+returnaop_;
+}
+
+AngleCOE::getTrueAnomaly()const
+{
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+returnanomaly_;
+}
+
+AngleCOE::getMeanAnomaly()const
+{
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+returnCOE::MeanAnomalyFromEccentricAnomaly(this->getEccentricAnomaly(),eccentricity_);
+}
+
+AngleCOE::getEccentricAnomaly()const
+{
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+returnCOE::EccentricAnomalyFromTrueAnomaly(anomaly_,eccentricity_);
+}
+
+LengthCOE::getPeriapsisRadius()const
+{
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+returnthis->semiMajorAxis_*(1.0-this->eccentricity_);
+}
+
+LengthCOE::getApoapsisRadius()const
+{
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+returnthis->semiMajorAxis_*(1.0+this->eccentricity_);
+}
+
+LengthCOE::getSemiLatusRectum()const
+{
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+returnLength::Meters(COE::ComputeSemiLatusRectum(semiMajorAxis_.inMeters(),eccentricity_));
+}
+
+LengthCOE::getRadialDistance()const
+{
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+returnLength::Meters(COE::ComputeRadialDistance(
+semiMajorAxis_.inMeters(),
+eccentricity_,
+COE::ConvertAnomaly(anomaly_,eccentricity_,anomalyType_,AnomalyType::True,1e-12).inRadians()
+));
+}
+
+DerivedCOE::getAngularMomentum(constDerived&aGravitationalParameter)const
+{
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+returnDerived(
+COE::ComputeAngularMomentum(
+COE::ComputeSemiLatusRectum(semiMajorAxis_.inMeters(),eccentricity_),aGravitationalParameter
+),
+AngularMomentumSIUnit
+);
+}
+
+DerivedCOE::getMeanMotion(constDerived&aGravitationalParameter)const
+{
+if(!aGravitationalParameter.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Gravitationalparameter");
+}
+
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+constRealsemiMajorAxis_m=semiMajorAxis_.inMeters();
+
+constRealgravitationalParameter_SI=aGravitationalParameter.in(GravitationalParameterSIUnit);
+
+returnDerived(
+std::sqrt(gravitationalParameter_SI/(semiMajorAxis_m*semiMajorAxis_m*semiMajorAxis_m)),
+angularVelocitySIUnit
+);
+}
+
+DerivedCOE::getNodalPrecessionRate(
+constDerived&aGravitationalParameter,constLength&anEquatorialRadius,constReal&aJ2Parameter
+)const
+{
+constRealomega=this->getMeanMotion(aGravitationalParameter).in(angularVelocitySIUnit);
+
+constRealomega_p=
+-(3.0/2.0)*std::pow(anEquatorialRadius.inMeters(),2.0)*aJ2Parameter*omega*
+std::cos(this->inclination_.inRadians())/
+std::pow(this->semiMajorAxis_.inMeters()*(1.0-(this->eccentricity_*this->eccentricity_)),2.0);
+
+returnDerived(omega_p,angularVelocitySIUnit);
+}
+
+DurationCOE::getOrbitalPeriod(constDerived&aGravitationalParameter)const
+{
+if(!aGravitationalParameter.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Gravitationalparameter");
+}
+
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+returnDuration::Seconds(Real::TwoPi()/this->getMeanMotion(aGravitationalParameter).in(angularVelocitySIUnit));
+}
+
+COE::CartesianStateCOE::getCartesianState(
+constDerived&aGravitationalParameter,constShared<constFrame>&aFrameSPtr
+)const
+{
+if(!aGravitationalParameter.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Gravitationalparameter");
+}
+
+if((aFrameSPtr==nullptr)||(!aFrameSPtr->isDefined()))
+{
+throwostk::core::error::runtime::Undefined("Frame");
+}
+
+if(!this->isDefined())
+{
+throwostk::core::error::runtime::Undefined("COE");
+}
+
+constReala_m=semiMajorAxis_.inMeters();
+constRealinclination_rad=inclination_.inRadians();
+constRealraan_rad=raan_.inRadians();
+constRealaop_rad=aop_.inRadians();
+constRealnu_rad=anomaly_.inRadians();
+constRealmu_SI=aGravitationalParameter.in(GravitationalParameterSIUnit);
+
+constRealp_m=a_m*(1.0-eccentricity_*eccentricity_);
+
+constVector3dR_pqw={
+p_m*std::cos(nu_rad)/(1.0+eccentricity_*std::cos(nu_rad)),
+p_m*std::sin(nu_rad)/(1.0+eccentricity_*std::cos(nu_rad)),
+0.0,
+};
+
+constVector3dV_pqw={
+-std::sqrt(mu_SI/p_m)*std::sin(nu_rad),
++std::sqrt(mu_SI/p_m)*(eccentricity_+std::cos(nu_rad)),
+0.0,
+};
+
+try
+{
+constVector3dx_ECI=RotationMatrix::RZ(Angle::Radians(-raan_rad))*
+RotationMatrix::RX(Angle::Radians(-inclination_rad))*
+RotationMatrix::RZ(Angle::Radians(-aop_rad))*R_pqw;
+constVector3dv_ECI=RotationMatrix::RZ(Angle::Radians(-raan_rad))*
+RotationMatrix::RX(Angle::Radians(-inclination_rad))*
+RotationMatrix::RZ(Angle::Radians(-aop_rad))*V_pqw;
+
+constPositionposition=Position::Meters(x_ECI,aFrameSPtr);
+constVelocityvelocity=Velocity::MetersPerSecond(v_ECI,aFrameSPtr);
+
+return{
+position,
+velocity,
+};
+}
+catch(constostk::core::error::Exception&anException)
+{
+std::cout<<"raan_rad="<<raan_rad<<std::endl;
+std::cout<<"inclination_rad="<<inclination_rad<<std::endl;
+std::cout<<"aop_rad="<<aop_rad<<std::endl;
+std::cout<<"R_pqw="<<R_pqw<<std::endl;
+std::cout<<"V_pqw="<<V_pqw<<std::endl;
+
+throwanException;
+}
+}
+
+Vector6dCOE::getSIVector(constCOE::AnomalyType&anAnomalyType)const
+{
+return{
+semiMajorAxis_.inMeters(),
+eccentricity_,
+inclination_.inRadians(),
+raan_.inRadians(),
+aop_.inRadians(),
+COE::ConvertAnomaly(anomaly_,eccentricity_,AnomalyType::True,anAnomalyType,1e-12).inRadians(),
+};
+}
+
+voidCOE::print(std::ostream&anOutputStream,booldisplayDecorator)const
+{
+displayDecorator?ostk::core::utils::Print::Header(anOutputStream,"ClassicalOrbitalElements"):void();
+
+ostk::core::utils::Print::Line(anOutputStream)
+<<"Semi-majoraxis:"
+<<(semiMajorAxis_.isDefined()?String::Format("{}[m]",semiMajorAxis_.inMeters().toString()):"Undefined");
+ostk::core::utils::Print::Line(anOutputStream)
+<<"Eccentricity:"<<(eccentricity_.isDefined()?eccentricity_.toString():"Undefined");
+ostk::core::utils::Print::Line(anOutputStream)
+<<"Inclination:"
+<<(inclination_.isDefined()?String::Format("{}[deg]",inclination_.inDegrees(0.0,360.0).toString())
+:"Undefined");
+ostk::core::utils::Print::Line(anOutputStream)
+<<"Rightascensionoftheascendingnode:"
+<<(raan_.isDefined()?String::Format("{}[deg]",raan_.inDegrees(0.0,360.0).toString()):"Undefined");
+ostk::core::utils::Print::Line(anOutputStream)
+<<"Argumentofperiapsis:"
+<<(aop_.isDefined()?String::Format("{}[deg]",aop_.inDegrees(0.0,360.0).toString()):"Undefined");
+StringanomalyType=String::Empty();
+switch(anomalyType_)
+{
+caseCOE::AnomalyType::True:
+anomalyType="True";
+break;
+caseCOE::AnomalyType::Mean:
+anomalyType="Mean";
+break;
+caseCOE::AnomalyType::Eccentric:
+anomalyType="Eccentric";
+break;
+default:
+throwostk::core::error::runtime::Wrong("Anomalytype");
+}
+ostk::core::utils::Print::Line(anOutputStream)
+<<String::Format("{}anomaly:",anomalyType)
+<<(anomaly_.isDefined()?String::Format("{}[deg]",anomaly_.inDegrees(0.0,360.0).toString()):"Undefined");
+
+displayDecorator?ostk::core::utils::Print::Footer(anOutputStream):void();
+}
+
+COECOE::Undefined()
+{
+return{
+Length::Undefined(),
+Real::Undefined(),
 Angle::Undefined(),
 Angle::Undefined(),
 Angle::Undefined(),
-};
-}
-
-COECOE::Cartesian(constCOE::CartesianState&aCartesianState,constDerived&aGravitationalParameter)
-{
-if((!aCartesianState.first.isDefined())||(!aCartesianState.second.isDefined()))
-{
-throwostk::core::error::runtime::Undefined("Cartesianstate");
-}
-
-if(!aGravitationalParameter.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Gravitationalparameter");
-}
-
-staticconstRealtolerance=1e-11;
-
-constRealmu=aGravitationalParameter.in(GravitationalParameterSIUnit);
-
-if(mu==0.0)
-{
-throwostk::core::error::runtime::Wrong("Gravitationalparameter");
-}
-
-constVector3d&positionVector=aCartesianState.first.accessCoordinates();
-constVector3d&velocityVector=aCartesianState.second.accessCoordinates();
-
-constRealposition=positionVector.norm();
-constRealvelocity=velocityVector.norm();
-
-if(position==0.0)
-{
-throwostk::core::error::runtime::Wrong("Positionvector");
-}
-
-//Angularmomentum
-
-constVector3dangularMomentumVector=positionVector.cross(velocityVector);
-
-constRealangularMomentum=angularMomentumVector.norm();
-
-if(angularMomentum==0.0)
-{
-throwostk::core::error::runtime::Wrong("Angularmomentum");
-}
-
-//Node
-
-constVector3dnodeVector=Vector3d::Z().cross(angularMomentumVector);
-
-constRealnode=nodeVector.norm();
-
-//Eccentricity
-
-constVector3deccentricityVector=(1.0/mu)*((((velocity*velocity)-(mu/position))*positionVector)-
-((positionVector.dot(velocityVector))*(velocityVector)));
-
-constReale=eccentricityVector.norm();
-
-if((std::abs(1.0-e))<=Real::Epsilon())
-{
-throwostk::core::error::runtime::ToBeImplemented("Supportforparabolicorbits.");
-}
-
-//Semi-majoraxis
-
-constRealE=(0.5*velocity*velocity)-(mu/position);
-
-if(E==0.0)
-{
-throwostk::core::error::runtime::Wrong("Specificorbitalenergy");
-}
-
-constReala_m=-mu/(2.0*E);
-
-if(std::abs(a_m*(1.0-e))<Real::Epsilon())
-{
-throwostk::core::error::RuntimeError("Conicsectionissingular.");
-}
-
-//Inclination
-
-constReali_rad=std::acos(angularMomentumVector(2)/angularMomentum);
-
-//Otherangles
-
-Realraan_rad=0.0;//[rad]RightAscensionoftheAscendingNode(RAAN)
-Realaop_rad=0.0;//[rad]ArgumentOfPeriapsis(AOP)
-Realnu_rad=0.0;//[rad]Trueanomaly(Nu)
-
-if((e>=tolerance)&&((i_rad>=tolerance)&&(i_rad<=(Real::Pi()-tolerance))))//Non-circular,inclined
-{
-if(node==0.0)
-{
-throwostk::core::error::runtime::Undefined("Node");
-}
-
-raan_rad=std::acos(nodeVector(0)/node);
-
-if(nodeVector(1)<0.0)
-{
-raan_rad=Real::TwoPi()-raan_rad;
-}
-
-aop_rad=std::acos(std::clamp((double)(nodeVector.dot(eccentricityVector)/(node*e)),-1.0,1.0));
-
-if(eccentricityVector(2)<0.0)
-{
-aop_rad=Real::TwoPi()-aop_rad;
-}
-
-nu_rad=std::acos(std::clamp((double)(eccentricityVector.dot(positionVector)/(e*position)),-1.0,1.0));
-
-if(positionVector.dot(velocityVector)<0.0)
-{
-nu_rad=Real::TwoPi()-nu_rad;
-}
-}
-elseif((e>=tolerance)&&((i_rad<tolerance)||(i_rad>(Real::Pi()-tolerance))))//Non-circular,
-//equatorial
-{
-raan_rad=0.0;
-aop_rad=std::acos(eccentricityVector(0)/e);
-
-if(eccentricityVector(1)<0.0)
-{
-aop_rad=Real::TwoPi()-aop_rad;
-}
-
-if(i_rad>(Real::Pi()-tolerance))
-{
-aop_rad=aop_rad*-1.0;
-}
-
-if(aop_rad<0.0)
-{
-aop_rad=aop_rad+Real::TwoPi();
-}
-
-nu_rad=std::acos(std::clamp((double)(eccentricityVector.dot(positionVector)/(e*position)),-1.0,1.0));
-
-if(positionVector.dot(velocityVector)<0.0)
-{
-nu_rad=Real::TwoPi()-nu_rad;
-}
-}
-elseif((e<tolerance)&&((i_rad>=tolerance)&&(i_rad<=(Real::Pi()-tolerance))))//Circular,inclined
-{
-if(node==0.0)
-{
-throwostk::core::error::runtime::Undefined("Node");
-}
-
-raan_rad=std::acos(nodeVector(0)/node);
-
-if(nodeVector(1)<0.0)
-{
-raan_rad=Real::TwoPi()-raan_rad;
-}
-
-aop_rad=0.0;
-
-nu_rad=std::acos(std::clamp((double)(nodeVector.dot(positionVector)/(node*position)),-1.0,1.0));
-
-if(positionVector(2)<0.0)
-{
-nu_rad=Real::TwoPi()-nu_rad;
-}
-}
-elseif((e<tolerance)&&((i_rad<tolerance)||(i_rad>(Real::Pi()-tolerance))))//Circular,equatorial
-{
-raan_rad=0.0;
-aop_rad=0.0;
-
-nu_rad=std::acos(positionVector(0)/position);
-
-if(positionVector(1)<0.0)
-{
-nu_rad=Real::TwoPi()-nu_rad;
-}
-
-if(i_rad>(Real::Pi()-tolerance))
-{
-nu_rad=nu_rad*-1.0;
-}
-
-if(nu_rad<0.0)
-{
-nu_rad=nu_rad+Real::TwoPi();
-}
-}
-
-return{
-Length::Meters(a_m),
-e,
-Angle::Radians(i_rad),
-Angle::Radians(raan_rad),
-Angle::Radians(aop_rad),
-Angle::Radians(nu_rad),
-};
-}
-
-COECOE::FromSIVector(constVector6d&aCOEVector,constAnomalyType&anAnomalyType)
-{
-return{
-Length::Meters(aCOEVector[0]),
-aCOEVector[1],
-Angle::Radians(aCOEVector[2]),
-Angle::Radians(aCOEVector[3]),
-Angle::Radians(aCOEVector[4]),
-COE::ConvertAnomaly(Angle::Radians(aCOEVector[5]),aCOEVector[1],anAnomalyType,AnomalyType::True,1e-15),
-};
-}
-
-AngleCOE::EccentricAnomalyFromTrueAnomaly(constAngle&aTrueAnomaly,constReal&anEccentricity)
-{
-if(!aTrueAnomaly.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Trueanomaly");
-}
-
-if(!anEccentricity.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Eccentricity");
-}
-
-constRealtrueAnomaly_rad=aTrueAnomaly.inRadians();
-
-RealeccentricAnomaly_rad=Real::Undefined();
-Realm=Real::Undefined();
-
-if(anEccentricity.abs()<Tolerance)//Circulartrajectory
-{
-m=trueAnomaly_rad;
-eccentricAnomaly_rad=trueAnomaly_rad;
-}
-else
-{
-if(anEccentricity<(1.0-Tolerance))//Ellipticaltrajectory
-{
-constRealsinE=(std::sqrt(1.0-anEccentricity*anEccentricity)*std::sin(trueAnomaly_rad))/
-(1.0+anEccentricity*std::cos(trueAnomaly_rad));
-constRealcosE=
-(anEccentricity+std::cos(trueAnomaly_rad))/(1.0+anEccentricity*std::cos(trueAnomaly_rad));
-
-eccentricAnomaly_rad=std::atan2(sinE,cosE);
-m=eccentricAnomaly_rad-anEccentricity*std::sin(eccentricAnomaly_rad);
-}
-else
-{
-if(anEccentricity>(1.0+Tolerance))//Hyperbolictrajectory
-{
-if((anEccentricity>1.0)&&
-(std::fabs(trueAnomaly_rad)+0.00001<(M_PI-std::acos(1.0/anEccentricity))))
-{
-constRealsinE=(std::sqrt(anEccentricity*anEccentricity-1.0)*std::sin(trueAnomaly_rad))/
-(1.0+anEccentricity*std::cos(trueAnomaly_rad));
-
-eccentricAnomaly_rad=std::asinh(sinE);
-m=anEccentricity*std::sinh(eccentricAnomaly_rad)-eccentricAnomaly_rad;
-}
-else
-{
-throwostk::core::error::RuntimeError("Algorithmerror.");
-}
-}
-else
-{
-if(std::fabs(trueAnomaly_rad)<168.0*M_PI/180.0)//Parabolictrajectory
-{
-eccentricAnomaly_rad=std::tan(trueAnomaly_rad*0.5);
-m=eccentricAnomaly_rad+
-(eccentricAnomaly_rad*eccentricAnomaly_rad*eccentricAnomaly_rad)/3.0;
-}
-else
-{
-throwostk::core::error::RuntimeError("Algorithmerror.");
-}
-}
-}
-}
-
-if(anEccentricity<1.0)
-{
-m=std::fmod(m,2.0*M_PI);
-
-if(m<0.0)
-{
-m+=2.0*M_PI;
-}
-
-eccentricAnomaly_rad=std::fmod(eccentricAnomaly_rad,2.0*M_PI);
-}
-
-returnAngle::Radians(Angle::Radians(eccentricAnomaly_rad).inRadians(0.0,Real::TwoPi()));
-}
-
-AngleCOE::TrueAnomalyFromEccentricAnomaly(constAngle&anEccentricAnomaly,constReal&anEccentricity)
-{
-if(!anEccentricAnomaly.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Eccentricanomaly");
-}
-
-if(!anEccentricity.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Eccentricity");
-}
+Angle::Undefined(),
+};
+}
+
+COECOE::Cartesian(constCOE::CartesianState&aCartesianState,constDerived&aGravitationalParameter)
+{
+if((!aCartesianState.first.isDefined())||(!aCartesianState.second.isDefined()))
+{
+throwostk::core::error::runtime::Undefined("Cartesianstate");
+}
+
+if(!aGravitationalParameter.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Gravitationalparameter");
+}
+
+staticconstRealtolerance=1e-11;
+
+constRealmu=aGravitationalParameter.in(GravitationalParameterSIUnit);
+
+if(mu==0.0)
+{
+throwostk::core::error::runtime::Wrong("Gravitationalparameter");
+}
+
+constVector3d&positionVector=aCartesianState.first.accessCoordinates();
+constVector3d&velocityVector=aCartesianState.second.accessCoordinates();
+
+constRealposition=positionVector.norm();
+constRealvelocity=velocityVector.norm();
+
+if(position==0.0)
+{
+throwostk::core::error::runtime::Wrong("Positionvector");
+}
+
+//Angularmomentum
+
+constVector3dangularMomentumVector=positionVector.cross(velocityVector);
+
+constRealangularMomentum=angularMomentumVector.norm();
+
+if(angularMomentum==0.0)
+{
+throwostk::core::error::runtime::Wrong("Angularmomentum");
+}
+
+//Node
+
+constVector3dnodeVector=Vector3d::Z().cross(angularMomentumVector);
+
+constRealnode=nodeVector.norm();
+
+//Eccentricity
+
+constVector3deccentricityVector=(1.0/mu)*((((velocity*velocity)-(mu/position))*positionVector)-
+((positionVector.dot(velocityVector))*(velocityVector)));
+
+constReale=eccentricityVector.norm();
+
+if((std::abs(1.0-e))<=Real::Epsilon())
+{
+throwostk::core::error::runtime::ToBeImplemented("Supportforparabolicorbits.");
+}
+
+//Semi-majoraxis
+
+constRealE=(0.5*velocity*velocity)-(mu/position);
+
+if(E==0.0)
+{
+throwostk::core::error::runtime::Wrong("Specificorbitalenergy");
+}
+
+constReala_m=-mu/(2.0*E);
+
+if(std::abs(a_m*(1.0-e))<Real::Epsilon())
+{
+throwostk::core::error::RuntimeError("Conicsectionissingular.");
+}
+
+//Inclination
+
+constReali_rad=std::acos(angularMomentumVector(2)/angularMomentum);
+
+//Otherangles
+
+Realraan_rad=0.0;//[rad]RightAscensionoftheAscendingNode(RAAN)
+Realaop_rad=0.0;//[rad]ArgumentOfPeriapsis(AOP)
+Realnu_rad=0.0;//[rad]Trueanomaly(Nu)
+
+if((e>=tolerance)&&((i_rad>=tolerance)&&(i_rad<=(Real::Pi()-tolerance))))//Non-circular,inclined
+{
+if(node==0.0)
+{
+throwostk::core::error::runtime::Undefined("Node");
+}
+
+raan_rad=std::acos(nodeVector(0)/node);
+
+if(nodeVector(1)<0.0)
+{
+raan_rad=Real::TwoPi()-raan_rad;
+}
+
+aop_rad=std::acos(std::clamp((double)(nodeVector.dot(eccentricityVector)/(node*e)),-1.0,1.0));
+
+if(eccentricityVector(2)<0.0)
+{
+aop_rad=Real::TwoPi()-aop_rad;
+}
+
+nu_rad=std::acos(std::clamp((double)(eccentricityVector.dot(positionVector)/(e*position)),-1.0,1.0));
+
+if(positionVector.dot(velocityVector)<0.0)
+{
+nu_rad=Real::TwoPi()-nu_rad;
+}
+}
+elseif((e>=tolerance)&&((i_rad<tolerance)||(i_rad>(Real::Pi()-tolerance))))//Non-circular,
+//equatorial
+{
+raan_rad=0.0;
+aop_rad=std::acos(eccentricityVector(0)/e);
+
+if(eccentricityVector(1)<0.0)
+{
+aop_rad=Real::TwoPi()-aop_rad;
+}
+
+if(i_rad>(Real::Pi()-tolerance))
+{
+aop_rad=aop_rad*-1.0;
+}
+
+if(aop_rad<0.0)
+{
+aop_rad=aop_rad+Real::TwoPi();
+}
+
+nu_rad=std::acos(std::clamp((double)(eccentricityVector.dot(positionVector)/(e*position)),-1.0,1.0));
+
+if(positionVector.dot(velocityVector)<0.0)
+{
+nu_rad=Real::TwoPi()-nu_rad;
+}
+}
+elseif((e<tolerance)&&((i_rad>=tolerance)&&(i_rad<=(Real::Pi()-tolerance))))//Circular,inclined
+{
+if(node==0.0)
+{
+throwostk::core::error::runtime::Undefined("Node");
+}
+
+raan_rad=std::acos(nodeVector(0)/node);
+
+if(nodeVector(1)<0.0)
+{
+raan_rad=Real::TwoPi()-raan_rad;
+}
+
+aop_rad=0.0;
+
+nu_rad=std::acos(std::clamp((double)(nodeVector.dot(positionVector)/(node*position)),-1.0,1.0));
+
+if(positionVector(2)<0.0)
+{
+nu_rad=Real::TwoPi()-nu_rad;
+}
+}
+elseif((e<tolerance)&&((i_rad<tolerance)||(i_rad>(Real::Pi()-tolerance))))//Circular,equatorial
+{
+raan_rad=0.0;
+aop_rad=0.0;
+
+nu_rad=std::acos(positionVector(0)/position);
+
+if(positionVector(1)<0.0)
+{
+nu_rad=Real::TwoPi()-nu_rad;
+}
+
+if(i_rad>(Real::Pi()-tolerance))
+{
+nu_rad=nu_rad*-1.0;
+}
+
+if(nu_rad<0.0)
+{
+nu_rad=nu_rad+Real::TwoPi();
+}
+}
+
+return{
+Length::Meters(a_m),
+e,
+Angle::Radians(i_rad),
+Angle::Radians(raan_rad),
+Angle::Radians(aop_rad),
+Angle::Radians(nu_rad),
+};
+}
+
+COECOE::FromSIVector(constVector6d&aCOEVector,constAnomalyType&anAnomalyType)
+{
+return{
+Length::Meters(aCOEVector[0]),
+aCOEVector[1],
+Angle::Radians(aCOEVector[2]),
+Angle::Radians(aCOEVector[3]),
+Angle::Radians(aCOEVector[4]),
+COE::ConvertAnomaly(Angle::Radians(aCOEVector[5]),aCOEVector[1],anAnomalyType,AnomalyType::True,1e-15),
+};
+}
+
+COECOE::FrozenOrbit(
+constLength&aSemiMajorAxis,
+constShared<constCelestial>&aCelestialObjectSPtr,
+constReal&anEccentricity,
+constAngle&anInclination,
+constAngle&aRaan,
+constAngle&anAop,
+constAngle&aTrueAnomaly
+)
+{
+if((aCelestialObjectSPtr==nullptr)||(!aCelestialObjectSPtr->isDefined()))
+{
+throwostk::core::error::runtime::Undefined("Celestialobject");
+}
+
+constLengthequatorialRadius=aCelestialObjectSPtr->getEquatorialRadius();
+constRealj2=aCelestialObjectSPtr->accessGravitationalModel()->getParameters().J2_;
+constRealj3=aCelestialObjectSPtr->accessGravitationalModel()->getParameters().J3_;
+
+returnCOE::FrozenOrbit(
+aSemiMajorAxis,equatorialRadius,j2,j3,anEccentricity,anInclination,aRaan,anAop,aTrueAnomaly
+);
+}
+
+COECOE::FrozenOrbit(
+constLength&aSemiMajorAxis,
+constLength&anEquatorialRadius,
+constReal&aJ2,
+constReal&aJ3,
+constReal&anEccentricity,
+constAngle&anInclination,
+constAngle&aRaan,
+constAngle&anAop,
+constAngle&aTrueAnomaly
+)
+{
+if(!aSemiMajorAxis.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Semi-majorAxis");
+}
+if(!anEquatorialRadius.isDefined())
+{
+throwostk::core::error::runtime::Undefined("EquatorialRadius");
+}
+if(!aJ2.isDefined()||aJ2==0.0)
+{
+throwostk::core::error::runtime::Undefined("J2");
+}
+if(!aJ3.isDefined()||aJ3==0.0)
+{
+throwostk::core::error::runtime::Undefined("J3");
+}
+if(!aRaan.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Raan");
+}
+if(!aTrueAnomaly.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Trueanomaly");
+}
+if(anEccentricity.isDefined()&&anInclination.isDefined())
+{
+throwostk::core::error::RuntimeError("Cannotdefinebotheccentricityandinclination");
+}
+
+constArray<Angle>criticalInclinations={Angle::Degrees(63.4349),Angle::Degrees(116.5651)};
+constArray<Angle>criticalAops={Angle::Degrees(90.0),Angle::Degrees(270.0)};
+
+constRealequatorialRadius_meters=anEquatorialRadius.inMeters();
+constRealj2=aJ2;
+constRealj3=aJ3;
+
+//ecc=~eccCoefficient*sin(incl)
+constRealeccCoefficient=-j3*equatorialRadius_meters/2.0/j2/aSemiMajorAxis.inMeters();
+
+constautoeccentricityFromInclination=[&eccCoefficient](constAngle&inclination)->Real
+{
+returneccCoefficient*std::sin(inclination.inRadians());
+};
+
+constautoinclinationFromEccentricity=[&eccCoefficient](constReal&eccentricity)->Angle
+{
+returnAngle::Radians(asin(eccentricity/eccCoefficient));
+};
+
+//TBI:thisonlyworksbecauseneithersetofcriticalanglesare0/360degrees
+constautoisCritical=[](constAngle&angle,constArray<Angle>&criticalAngles)->bool
+{
+constRealepsilon=Angle::Arcseconds(1.0).inRadians();//TBI:makeconfigurable?
+
+return(angle.inRadians().isNear(criticalAngles[0].inRadians(),epsilon))||
+(angle.inRadians().isNear(criticalAngles[1].inRadians(),epsilon));
+};
 
-constRealeccentricAnomaly_rad=anEccentricAnomaly.inRadians();
-constRealtrueAnomaly_rad=2.0*std::atan2(
-(std::sqrt(1.0+anEccentricity)*std::sin(eccentricAnomaly_rad/2.0)),
-(std::sqrt(1.0-anEccentricity)*std::cos(eccentricAnomaly_rad/2.0))
-);
-
-returnAngle::Radians(Angle::Radians(trueAnomaly_rad).inRadians(0.0,Real::TwoPi()));
-}
+//UsetheprovidedAoP,ordefaulttoacriticalvalue
+constAngleaop=anAop.isDefined()?anAop:criticalAops[0];
+
+//IfAoPmatchesacriticalvalue
+if(isCritical(aop,criticalAops))
+{
+Angleinclination=Angle::Undefined();
+Realeccentricity=Real::Undefined();
 
-AngleCOE::MeanAnomalyFromEccentricAnomaly(constAngle&anEccentricAnomaly,constReal&anEccentricity)
-{
-if(!anEccentricAnomaly.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Eccentricanomaly");
-}
-
-if(!anEccentricity.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Eccentricity");
-}
-
-constRealeccentricAnomaly_rad=anEccentricAnomaly.inRadians();
-constRealmeanAnomaly_rad=eccentricAnomaly_rad-anEccentricity*std::sin(eccentricAnomaly_rad);
-
-returnAngle::Radians(Angle::Radians(meanAnomaly_rad).inRadians(0.0,Real::TwoPi()));
-}
-
-AngleCOE::EccentricAnomalyFromMeanAnomaly(
-constAngle&aMeanAnomaly,constReal&anEccentricity,constReal&aTolerance
-)
-{
-if(!aMeanAnomaly.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Meananomaly");
-}
-
-if(!anEccentricity.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Eccentricity");
-}
-
-if(!aTolerance.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Tolerance");
-}
-
-//https://en.wikipedia.org/wiki/Kepler%27s_equation
-//http://alpheratz.net/dynamics/twobody/KeplerIterations_summary.pdf
-//https://gist.github.com/j-faria/1fd079e677325ce820971d9d5d286dad
-
-//ProvidesastartingvaluetosolveKepler'sequation
-
-autokeplerstart3=[](Reale,RealM)->Real
-{
-constRealt34=e*e;
-constRealt35=e*t34;
-constRealt33=std::cos(M);
-
-returnM+(-0.5*t35+e+(t34+1.5*t33*t35)*t33)*std::sin(M);
-};
-
-//Aniteration(correction)methodtosolveKepler'sequation
-
-autoeps3=[](Reale,RealM,Realx)->Real
-{
-constRealt1=std::cos(x);
-constRealt2=-1.0+e*t1;
-constRealt3=std::sin(x);
-constRealt4=e*t3;
-constRealt5=-x+t4+M;
-constRealt6=t5/(0.5*t5*t4/t2+t2);
-
-returnt5/(((0.5*t3)-((1.0/6.0)*t1*t6))*e*t6+t2);
-};
-
-constRealmeanAnomaly_rad=aMeanAnomaly.inRadians();
-
-constRealM=meanAnomaly_rad;
-constRealMnorm=std::fmod(M,2.0*M_PI);
-
-RealE=Real::Undefined();
-
-RealE0=keplerstart3(anEccentricity,Mnorm);
-RealdE=aTolerance+1.0;
-Sizecount=0;
-
-while(dE>aTolerance)
-{
-E=E0-eps3(anEccentricity,Mnorm,E0);
-dE=std::abs(E-E0);
-E0=E;
-
-count++;
-
-if(count>1000)//Failedtoconverge,thisonlyhappensfornearlyparabolicorbits
-{
-throwostk::core::error::RuntimeError(
-"Cannotconvergetosolution({},{},{}).",
-aMeanAnomaly.toString(32),
-anEccentricity.toString(32),
-aTolerance.toString(32)
-);
-}
-}
-
-returnAngle::Radians(E);
-}
-
-AngleCOE::TrueAnomalyFromMeanAnomaly(constAngle&aMeanAnomly,constReal&anEccentricity,constReal&aTolerance)
-{
-returnTrueAnomalyFromEccentricAnomaly(
-EccentricAnomalyFromMeanAnomaly(aMeanAnomly,anEccentricity,aTolerance),anEccentricity
-);
-}
-
-RealCOE::ComputeSemiLatusRectum(constReal&aSemiMajorAxis,constReal&anEccentricity)
-{
-returnaSemiMajorAxis*(1.0-(anEccentricity*anEccentricity));
-}
-
-RealCOE::ComputeRadialDistance(constReal&aSemiMajorAxis,constReal&anEccentricity,constReal&aTrueAnomaly)
-{
-returnComputeSemiLatusRectum(aSemiMajorAxis,anEccentricity)/(1.0+anEccentricity*std::cos(aTrueAnomaly));
-}
-
-RealCOE::ComputeAngularMomentum(
-constReal&aSemiMajorAxis,constReal&anEccentricity,constDerived&aGravitationalParameter
-)
-{
-constRealmu_SI=aGravitationalParameter.in(GravitationalParameterSIUnit);
+//Ifeccnotdefined,usethegiveninclinationordefaulttocriticalinclination,andcalculateecc
+if(!anEccentricity.isDefined())
+{
+inclination=anInclination.isDefined()?anInclination:criticalInclinations[0];
+eccentricity=eccentricityFromInclination(inclination);
+}
+//Ifeccdefined,useittocalculateinc
+else
+{
+//Iftheeccentricityislargerthanthisvalue,theapproximationisn'tvalid
+if(anEccentricity>eccCoefficient)
+{
+throwostk::core::error::RuntimeError(
+"Providedeccentricity["+anEccentricity.toString()+"]cannotbegreaterthan"+
+eccCoefficient.toString()
+);
+}
+inclination=inclinationFromEccentricity(anEccentricity);
+eccentricity=anEccentricity;
+}
+
+return{
+aSemiMajorAxis,
+eccentricity,
+inclination,
+aRaan,
+aop,
+aTrueAnomaly,
+};
+}
+
+//IfAoPis(given)andnotacriticalangle,thentheinclinationmustbecritical
+constAngleinclination=anInclination.isDefined()?anInclination:criticalInclinations[0];
+if(!isCritical(inclination,criticalInclinations))
+{
+throwostk::core::error::RuntimeError("Providedinclinationmustbeacriticalvalue");
+}
+
+constRealeccentricity=eccentricityFromInclination(inclination);
+
+return{
+aSemiMajorAxis,
+eccentricity,
+inclination,
+aRaan,
+aop,
+aTrueAnomaly,
+};
+}
+
+AngleCOE::EccentricAnomalyFromTrueAnomaly(constAngle&aTrueAnomaly,constReal&anEccentricity)
+{
+if(!aTrueAnomaly.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Trueanomaly");
+}
+
+if(!anEccentricity.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Eccentricity");
+}
+
+constRealtrueAnomaly_rad=aTrueAnomaly.inRadians();
+
+RealeccentricAnomaly_rad=Real::Undefined();
+Realm=Real::Undefined();
+
+if(anEccentricity.abs()<Tolerance)//Circulartrajectory
+{
+m=trueAnomaly_rad;
+eccentricAnomaly_rad=trueAnomaly_rad;
+}
+else
+{
+if(anEccentricity<(1.0-Tolerance))//Ellipticaltrajectory
+{
+constRealsinE=(std::sqrt(1.0-anEccentricity*anEccentricity)*std::sin(trueAnomaly_rad))/
+(1.0+anEccentricity*std::cos(trueAnomaly_rad));
+constRealcosE=
+(anEccentricity+std::cos(trueAnomaly_rad))/(1.0+anEccentricity*std::cos(trueAnomaly_rad));
+
+eccentricAnomaly_rad=std::atan2(sinE,cosE);
+m=eccentricAnomaly_rad-anEccentricity*std::sin(eccentricAnomaly_rad);
+}
+else
+{
+if(anEccentricity>(1.0+Tolerance))//Hyperbolictrajectory
+{
+if((anEccentricity>1.0)&&
+(std::fabs(trueAnomaly_rad)+0.00001<(M_PI-std::acos(1.0/anEccentricity))))
+{
+constRealsinE=(std::sqrt(anEccentricity*anEccentricity-1.0)*std::sin(trueAnomaly_rad))/
+(1.0+anEccentricity*std::cos(trueAnomaly_rad));
+
+eccentricAnomaly_rad=std::asinh(sinE);
+m=anEccentricity*std::sinh(eccentricAnomaly_rad)-eccentricAnomaly_rad;
+}
+else
+{
+throwostk::core::error::RuntimeError("Algorithmerror.");
+}
+}
+else
+{
+if(std::fabs(trueAnomaly_rad)<168.0*M_PI/180.0)//Parabolictrajectory
+{
+eccentricAnomaly_rad=std::tan(trueAnomaly_rad*0.5);
+m=eccentricAnomaly_rad+
+(eccentricAnomaly_rad*eccentricAnomaly_rad*eccentricAnomaly_rad)/3.0;
+}
+else
+{
+throwostk::core::error::RuntimeError("Algorithmerror.");
+}
+}
+}
+}
+
+if(anEccentricity<1.0)
+{
+m=std::fmod(m,2.0*M_PI);
 
-returnstd::sqrt(mu_SI*ComputeSemiLatusRectum(aSemiMajorAxis,anEccentricity));
-}
-
-RealCOE::ComputeAngularMomentum(constReal&aSemiLatusRectum,constDerived&aGravitationalParameter)
-{
-constRealmu_SI=aGravitationalParameter.in(GravitationalParameterSIUnit);
-
-returnstd::sqrt(mu_SI*aSemiLatusRectum);
-}
-
-TimeCOE::ComputeMeanLTAN(constAngle&raan,constInstant&anInstant,constSun&aSun)
-{
-//Calculatesunposition
-constVector3dsunDirectionGCRF=aSun.getPositionIn(Frame::GCRF(),anInstant).getCoordinates();
-
-//Calculatesunapparentlocaltime
-constAngleapparentSolarTime=Angle::Radians(std::atan2(sunDirectionGCRF.y(),sunDirectionGCRF.x()));
+if(m<0.0)
+{
+m+=2.0*M_PI;
+}
+
+eccentricAnomaly_rad=std::fmod(eccentricAnomaly_rad,2.0*M_PI);
+}
+
+returnAngle::Radians(Angle::Radians(eccentricAnomaly_rad).inRadians(0.0,Real::TwoPi()));
+}
+
+AngleCOE::TrueAnomalyFromEccentricAnomaly(constAngle&anEccentricAnomaly,constReal&anEccentricity)
+{
+if(!anEccentricAnomaly.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Eccentricanomaly");
+}
 
-//Getequationoftime
-constAngleequationOfTime=COE::ComputeEquationOfTime(anInstant);
-
-//Computesunmeanlocaltime
-constAnglesmlt=apparentSolarTime+equationOfTime;
-
-//Getanglebetweensunandascendingnode
-constRealalpha=std::fmod((raan-smlt).inRadians(),2.0*M_PI);
-
-//GetMeanLTAN
-constRealmeanLTAN=std::fmod((alpha*12.0/M_PI)+12.0,24.0);
-
-returnTime::Hours(meanLTAN);
-}
-
-TimeCOE::ComputeLTAN(constAngle&raan,constInstant&anInstant,constSun&aSun)
-{
-//Calculatesunposition
-constVector3dsunDirectionGCRF=aSun.getPositionIn(Frame::GCRF(),anInstant).getCoordinates();
-
-//Calculatesunapparentlocaltime
-constAngleapparentSolarTime=Angle::Radians(std::atan2(sunDirectionGCRF.y(),sunDirectionGCRF.x()));
-
-//Getanglebetweensunandascendingnode
-constRealalpha=std::fmod((raan-apparentSolarTime).inRadians(),2.0*M_PI);
+if(!anEccentricity.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Eccentricity");
+}
+
+constRealeccentricAnomaly_rad=anEccentricAnomaly.inRadians();
+constRealtrueAnomaly_rad=2.0*std::atan2(
+(std::sqrt(1.0+anEccentricity)*std::sin(eccentricAnomaly_rad/2.0)),
+(std::sqrt(1.0-anEccentricity)*std::cos(eccentricAnomaly_rad/2.0))
+);
+
+returnAngle::Radians(Angle::Radians(trueAnomaly_rad).inRadians(0.0,Real::TwoPi()));
+}
+
+AngleCOE::MeanAnomalyFromEccentricAnomaly(constAngle&anEccentricAnomaly,constReal&anEccentricity)
+{
+if(!anEccentricAnomaly.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Eccentricanomaly");
+}
+
+if(!anEccentricity.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Eccentricity");
+}
 
-//GetLTAN
-constRealLTAN=std::fmod((alpha*12.0/M_PI)+12.0,24.0);
+constRealeccentricAnomaly_rad=anEccentricAnomaly.inRadians();
+constRealmeanAnomaly_rad=eccentricAnomaly_rad-anEccentricity*std::sin(eccentricAnomaly_rad);
 
-returnTime::Hours(LTAN);
+returnAngle::Radians(Angle::Radians(meanAnomaly_rad).inRadians(0.0,Real::TwoPi()));
 }
 
-StringCOE::StringFromElement(constCOE::Element&anElement)
-{
-switch(anElement)
-{
-caseCOE::Element::SemiMajorAxis:
-return"SemiMajorAxis";
-caseCOE::Element::Eccentricity:
-return"Eccentricity";
-caseCOE::Element::Inclination:
-return"Inclination";
-caseCOE::Element::Aop:
-return"Aop";
-caseCOE::Element::Raan:
-return"Raan";
-caseCOE::Element::TrueAnomaly:
-return"TrueAnomaly";
-caseCOE::Element::MeanAnomaly:
-return"MeanAnomaly";
-caseCOE::Element::EccentricAnomaly:
-return"EccentricAnomaly";
-}
-
-throwostk::core::error::runtime::Wrong("Element");
-}
+AngleCOE::EccentricAnomalyFromMeanAnomaly(
+constAngle&aMeanAnomaly,constReal&anEccentricity,constReal&aTolerance
+)
+{
+if(!aMeanAnomaly.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Meananomaly");
+}
+
+if(!anEccentricity.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Eccentricity");
+}
+
+if(!aTolerance.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Tolerance");
+}
+
+//https://en.wikipedia.org/wiki/Kepler%27s_equation
+//http://alpheratz.net/dynamics/twobody/KeplerIterations_summary.pdf
+//https://gist.github.com/j-faria/1fd079e677325ce820971d9d5d286dad
+
+//ProvidesastartingvaluetosolveKepler'sequation
 
-COE::COE(
-constLength&aSemiMajorAxis,
-constReal&anEccentricity,
-constAngle&anInclination,
-constAngle&aRaan,
-constAngle&anAop,
-constAngle&anAnomaly,
-constAnomalyType&anAnomalyType
-)
-:semiMajorAxis_(aSemiMajorAxis),
-eccentricity_(anEccentricity),
-inclination_(anInclination),
-raan_(aRaan),
-aop_(anAop),
-anomaly_(anAnomaly),
-anomalyType_(anAnomalyType)
-{
-}
-
-AngleCOE::ConvertAnomaly(
-constAngle&anAnomaly,
-constReal&anEccentricity,
-constAnomalyType&fromAnomalyType,
-constAnomalyType&toAnomalyType,
-constReal&aTolerance
-)
-{
-switch(fromAnomalyType)
-{
-case(AnomalyType::True):
-{
-switch(toAnomalyType)
-{
-case(AnomalyType::True):
-returnanAnomaly;
-case(AnomalyType::Eccentric):
-returnEccentricAnomalyFromTrueAnomaly(anAnomaly,anEccentricity);
-case(AnomalyType::Mean):
-returnMeanAnomalyFromEccentricAnomaly(
-EccentricAnomalyFromTrueAnomaly(anAnomaly,anEccentricity),anEccentricity
-);
-default:
-throwostk::core::error::runtime::Wrong("ToAnomalytype");
-}
-}
-
-case(AnomalyType::Eccentric):
-{
-switch(toAnomalyType)
-{
-case(AnomalyType::True):
-returnTrueAnomalyFromEccentricAnomaly(anAnomaly,anEccentricity);
-case(AnomalyType::Eccentric):
-returnanAnomaly;
-case(AnomalyType::Mean):
-returnMeanAnomalyFromEccentricAnomaly(anAnomaly,anEccentricity);
-default:
-throwostk::core::error::runtime::Wrong("ToAnomalytype");
-}
-}
-
-case(AnomalyType::Mean):
-{
-switch(toAnomalyType)
-{
-case(AnomalyType::True):
-returnTrueAnomalyFromMeanAnomaly(anAnomaly,anEccentricity,aTolerance);
-case(AnomalyType::Eccentric):
-returnEccentricAnomalyFromMeanAnomaly(anAnomaly,anEccentricity,aTolerance);
-case(AnomalyType::Mean):
-returnanAnomaly;
-default:
-throwostk::core::error::runtime::Wrong("ToAnomalytype");
-}
-}
-
-default:
-throwostk::core::error::runtime::Wrong("FromAnomalytype");
-}
-}
-
-AngleCOE::ComputeEquationOfTime(constInstant&anInstant)
-{
-//Assumeinstantisadatetimeobject
-constRealjulianDate=anInstant.getJulianDate(Scale::UTC);
+autokeplerstart3=[](Reale,RealM)->Real
+{
+constRealt34=e*e;
+constRealt35=e*t34;
+constRealt33=std::cos(M);
+
+returnM+(-0.5*t35+e+(t34+1.5*t33*t35)*t33)*std::sin(M);
+};
+
+//Aniteration(correction)methodtosolveKepler'sequation
+
+autoeps3=[](Reale,RealM,Realx)->Real
+{
+constRealt1=std::cos(x);
+constRealt2=-1.0+e*t1;
+constRealt3=std::sin(x);
+constRealt4=e*t3;
+constRealt5=-x+t4+M;
+constRealt6=t5/(0.5*t5*t4/t2+t2);
+
+returnt5/(((0.5*t3)-((1.0/6.0)*t1*t6))*e*t6+t2);
+};
+
+constRealmeanAnomaly_rad=aMeanAnomaly.inRadians();
+
+constRealM=meanAnomaly_rad;
+constRealMnorm=std::fmod(M,2.0*M_PI);
+
+RealE=Real::Undefined();
+
+RealE0=keplerstart3(anEccentricity,Mnorm);
+RealdE=aTolerance+1.0;
+Sizecount=0;
+
+while(dE>aTolerance)
+{
+E=E0-eps3(anEccentricity,Mnorm,E0);
+dE=std::abs(E-E0);
+E0=E;
+
+count++;
+
+if(count>1000)//Failedtoconverge,thisonlyhappensfornearlyparabolicorbits
+{
+throwostk::core::error::RuntimeError(
+"Cannotconvergetosolution({},{},{}).",
+aMeanAnomaly.toString(32),
+anEccentricity.toString(32),
+aTolerance.toString(32)
+);
+}
+}
+
+returnAngle::Radians(E);
+}
+
+AngleCOE::TrueAnomalyFromMeanAnomaly(constAngle&aMeanAnomly,constReal&anEccentricity,constReal&aTolerance)
+{
+returnTrueAnomalyFromEccentricAnomaly(
+EccentricAnomalyFromMeanAnomaly(aMeanAnomly,anEccentricity,aTolerance),anEccentricity
+);
+}
+
+RealCOE::ComputeSemiLatusRectum(constReal&aSemiMajorAxis,constReal&anEccentricity)
+{
+returnaSemiMajorAxis*(1.0-(anEccentricity*anEccentricity));
+}
+
+RealCOE::ComputeRadialDistance(constReal&aSemiMajorAxis,constReal&anEccentricity,constReal&aTrueAnomaly)
+{
+returnComputeSemiLatusRectum(aSemiMajorAxis,anEccentricity)/(1.0+anEccentricity*std::cos(aTrueAnomaly));
+}
+
+RealCOE::ComputeAngularMomentum(
+constReal&aSemiMajorAxis,constReal&anEccentricity,constDerived&aGravitationalParameter
+)
+{
+constRealmu_SI=aGravitationalParameter.in(GravitationalParameterSIUnit);
+
+returnstd::sqrt(mu_SI*ComputeSemiLatusRectum(aSemiMajorAxis,anEccentricity));
+}
+
+RealCOE::ComputeAngularMomentum(constReal&aSemiLatusRectum,constDerived&aGravitationalParameter)
+{
+constRealmu_SI=aGravitationalParameter.in(GravitationalParameterSIUnit);
 
-//JulianDateofJ2000.0
-constRealjulianDate_J2000=2451545.0;
+returnstd::sqrt(mu_SI*aSemiLatusRectum);
+}
 
-//NumberofJuliancenturiesfromJ2000.0
-constRealT_UT1=(julianDate-julianDate_J2000)/36525.0;
-
-//MeanlongitudeoftheSun
-constRealsunMeanLongitude_deg=std::fmod(280.460+36000.771*T_UT1,360.0);
-
-//MeananomalyoftheSun
-constRealsunMeanAnomaly_rad=Angle::Degrees(std::fmod(357.5291092+35999.05034*T_UT1,360.0)).inRadians();
-
-//EclipticlatitudeoftheSun
-constRealsunEclipticLatitude_rad=
-Angle::Degrees(std::fmod(
-sunMeanLongitude_deg+1.914666471*std::sin(sunMeanAnomaly_rad)+
-0.019994643*std::sin(2.0*sunMeanAnomaly_rad),
-360.0
-))
-.inRadians();
-
-//Computetheequationoftime
-constRealequationOfTime_deg=
--1.914666471*std::sin(sunMeanAnomaly_rad)-0.019994643*std::sin(2.0*sunMeanAnomaly_rad)+
-2.466*std::sin(2.0*sunEclipticLatitude_rad)-0.0053*std::sin(4.0*sunEclipticLatitude_rad);
+TimeCOE::ComputeMeanLTAN(constAngle&raan,constInstant&anInstant,constSun&aSun)
+{
+//Calculatesunposition
+constVector3dsunDirectionGCRF=aSun.getPositionIn(Frame::GCRF(),anInstant).getCoordinates();
+
+//Calculatesunapparentlocaltime
+constAngleapparentSolarTime=Angle::Radians(std::atan2(sunDirectionGCRF.y(),sunDirectionGCRF.x()));
+
+//Getequationoftime
+constAngleequationOfTime=COE::ComputeEquationOfTime(anInstant);
+
+//Computesunmeanlocaltime
+constAnglesmlt=apparentSolarTime+equationOfTime;
+
+//Getanglebetweensunandascendingnode
+constRealalpha=std::fmod((raan-smlt).inRadians(),2.0*M_PI);
+
+//GetMeanLTAN
+constRealmeanLTAN=std::fmod((alpha*12.0/M_PI)+12.0,24.0);
+
+returnTime::Hours(meanLTAN);
+}
 
-returnAngle::Degrees(equationOfTime_deg);
-}
-
-}//namespacekepler
-}//namespacemodel
-}//namespaceorbit
-}//namespacetrajectory
-}//namespaceastrodynamics
-}//namespaceostk
+TimeCOE::ComputeLTAN(constAngle&raan,constInstant&anInstant,constSun&aSun)
+{
+//Calculatesunposition
+constVector3dsunDirectionGCRF=aSun.getPositionIn(Frame::GCRF(),anInstant).getCoordinates();
+
+//Calculatesunapparentlocaltime
+constAngleapparentSolarTime=Angle::Radians(std::atan2(sunDirectionGCRF.y(),sunDirectionGCRF.x()));
+
+//Getanglebetweensunandascendingnode
+constRealalpha=std::fmod((raan-apparentSolarTime).inRadians(),2.0*M_PI);
+
+//GetLTAN
+constRealLTAN=std::fmod((alpha*12.0/M_PI)+12.0,24.0);
+
+returnTime::Hours(LTAN);
+}
+
+StringCOE::StringFromElement(constCOE::Element&anElement)
+{
+switch(anElement)
+{
+caseCOE::Element::SemiMajorAxis:
+return"SemiMajorAxis";
+caseCOE::Element::Eccentricity:
+return"Eccentricity";
+caseCOE::Element::Inclination:
+return"Inclination";
+caseCOE::Element::Aop:
+return"Aop";
+caseCOE::Element::Raan:
+return"Raan";
+caseCOE::Element::TrueAnomaly:
+return"TrueAnomaly";
+caseCOE::Element::MeanAnomaly:
+return"MeanAnomaly";
+caseCOE::Element::EccentricAnomaly:
+return"EccentricAnomaly";
+}
+
+throwostk::core::error::runtime::Wrong("Element");
+}
+
+COE::COE(
+constLength&aSemiMajorAxis,
+constReal&anEccentricity,
+constAngle&anInclination,
+constAngle&aRaan,
+constAngle&anAop,
+constAngle&anAnomaly,
+constAnomalyType&anAnomalyType
+)
+:semiMajorAxis_(aSemiMajorAxis),
+eccentricity_(anEccentricity),
+inclination_(anInclination),
+raan_(aRaan),
+aop_(anAop),
+anomaly_(anAnomaly),
+anomalyType_(anAnomalyType)
+{
+}
+
+AngleCOE::ConvertAnomaly(
+constAngle&anAnomaly,
+constReal&anEccentricity,
+constAnomalyType&fromAnomalyType,
+constAnomalyType&toAnomalyType,
+constReal&aTolerance
+)
+{
+switch(fromAnomalyType)
+{
+case(AnomalyType::True):
+{
+switch(toAnomalyType)
+{
+case(AnomalyType::True):
+returnanAnomaly;
+case(AnomalyType::Eccentric):
+returnEccentricAnomalyFromTrueAnomaly(anAnomaly,anEccentricity);
+case(AnomalyType::Mean):
+returnMeanAnomalyFromEccentricAnomaly(
+EccentricAnomalyFromTrueAnomaly(anAnomaly,anEccentricity),anEccentricity
+);
+default:
+throwostk::core::error::runtime::Wrong("ToAnomalytype");
+}
+}
+
+case(AnomalyType::Eccentric):
+{
+switch(toAnomalyType)
+{
+case(AnomalyType::True):
+returnTrueAnomalyFromEccentricAnomaly(anAnomaly,anEccentricity);
+case(AnomalyType::Eccentric):
+returnanAnomaly;
+case(AnomalyType::Mean):
+returnMeanAnomalyFromEccentricAnomaly(anAnomaly,anEccentricity);
+default:
+throwostk::core::error::runtime::Wrong("ToAnomalytype");
+}
+}
+
+case(AnomalyType::Mean):
+{
+switch(toAnomalyType)
+{
+case(AnomalyType::True):
+returnTrueAnomalyFromMeanAnomaly(anAnomaly,anEccentricity,aTolerance);
+case(AnomalyType::Eccentric):
+returnEccentricAnomalyFromMeanAnomaly(anAnomaly,anEccentricity,aTolerance);
+case(AnomalyType::Mean):
+returnanAnomaly;
+default:
+throwostk::core::error::runtime::Wrong("ToAnomalytype");
+}
+}
+
+default:
+throwostk::core::error::runtime::Wrong("FromAnomalytype");
+}
+}
+
+AngleCOE::ComputeEquationOfTime(constInstant&anInstant)
+{
+//Assumeinstantisadatetimeobject
+constRealjulianDate=anInstant.getJulianDate(Scale::UTC);
+
+//JulianDateofJ2000.0
+constRealjulianDate_J2000=2451545.0;
+
+//NumberofJuliancenturiesfromJ2000.0
+constRealT_UT1=(julianDate-julianDate_J2000)/36525.0;
+
+//MeanlongitudeoftheSun
+constRealsunMeanLongitude_deg=std::fmod(280.460+36000.771*T_UT1,360.0);
+
+//MeananomalyoftheSun
+constRealsunMeanAnomaly_rad=Angle::Degrees(std::fmod(357.5291092+35999.05034*T_UT1,360.0)).inRadians();
+
+//EclipticlatitudeoftheSun
+constRealsunEclipticLatitude_rad=
+Angle::Degrees(std::fmod(
+sunMeanLongitude_deg+1.914666471*std::sin(sunMeanAnomaly_rad)+
+0.019994643*std::sin(2.0*sunMeanAnomaly_rad),
+360.0
+))
+.inRadians();
+
+//Computetheequationoftime
+constRealequationOfTime_deg=
+-1.914666471*std::sin(sunMeanAnomaly_rad)-0.019994643*std::sin(2.0*sunMeanAnomaly_rad)+
+2.466*std::sin(2.0*sunEclipticLatitude_rad)-0.0053*std::sin(4.0*sunEclipticLatitude_rad);
+
+returnAngle::Degrees(equationOfTime_deg);
+}
+
+}//namespacekepler
+}//namespacemodel
+}//namespaceorbit
+}//namespacetrajectory
+}//namespaceastrodynamics
+}//namespaceostk
     
     
   
diff --git a/xml/_c_o_e_8hpp.xml b/xml/_c_o_e_8hpp.xml
index 44dc166cb..b2abdc877 100644
--- a/xml/_c_o_e_8hpp.xml
+++ b/xml/_c_o_e_8hpp.xml
@@ -245,167 +245,190 @@
 usingostk::physics::coordinate::Frame;
 usingostk::physics::coordinate::Position;
 usingostk::physics::coordinate::Velocity;
-usingostk::physics::environment::object::celestial::Sun;
-usingostk::physics::time::Duration;
-usingostk::physics::time::Instant;
-usingostk::physics::time::Time;
-usingostk::physics::unit::Angle;
-usingostk::physics::unit::Derived;
-usingostk::physics::unit::Length;
-
-classCOE
-{
-public:
-enumclassElement
-{
-SemiMajorAxis,
-Eccentricity,
-Inclination,
-Raan,
-Aop,
-TrueAnomaly,
-MeanAnomaly,
-EccentricAnomaly
-};
-
-enumclassAnomalyType
-{
-True,
-Mean,
-Eccentric,
-};
-
-typedefPair<Position,Velocity>CartesianState;
-
-COE(constLength&aSemiMajorAxis,
-constReal&anEccentricity,
-constAngle&anInclination,
-constAngle&aRaan,
-constAngle&anAop,
-constAngle&aTrueAnomaly);
-
-booloperator==(constCOE&aCOE)const;
-
-booloperator!=(constCOE&aCOE)const;
-
-friendstd::ostream&operator<<(std::ostream&anOutputStream,constCOE&aCOE);
-
-boolisDefined()const;
-
-LengthgetSemiMajorAxis()const;
-
-RealgetEccentricity()const;
-
-AnglegetInclination()const;
-
-AnglegetRaan()const;
-
-AnglegetAop()const;
-
-virtualAnglegetTrueAnomaly()const;
-
-virtualAnglegetMeanAnomaly()const;
-
-virtualAnglegetEccentricAnomaly()const;
-
-LengthgetPeriapsisRadius()const;
-
-LengthgetApoapsisRadius()const;
-
-LengthgetSemiLatusRectum()const;
-
-LengthgetRadialDistance()const;
-
-DerivedgetAngularMomentum(constDerived&aGravitationalParameter)const;
-
-DerivedgetMeanMotion(constDerived&aGravitationalParameter)const;
-
-DerivedgetNodalPrecessionRate(
-constDerived&aGravitationalParameter,constLength&anEquatorialRadius,constReal&aJ2Parameter
-)const;
-
-DurationgetOrbitalPeriod(constDerived&aGravitationalParameter)const;
-
-COE::CartesianStategetCartesianState(constDerived&aGravitationalParameter,constShared<constFrame>&aFrameSPtr)
-const;
-
-Vector6dgetSIVector(constAnomalyType&anAnomalyType)const;
-
-voidprint(std::ostream&anOutputStream,booldisplayDecorator=true)const;
-
-staticCOEUndefined();
-
-staticCOECartesian(constCOE::CartesianState&aCartesianState,constDerived&aGravitationalParameter);
-
-staticCOEFromSIVector(constVector6d&aCOEVector,constAnomalyType&anAnomalyType);
-
-staticAngleEccentricAnomalyFromTrueAnomaly(constAngle&aTrueAnomaly,constReal&anEccentricity);
-
-staticAngleTrueAnomalyFromEccentricAnomaly(constAngle&anEccentricAnomaly,constReal&anEccentricity);
-
-staticAngleMeanAnomalyFromEccentricAnomaly(constAngle&anEccentricAnomaly,constReal&anEccentricity);
-
-staticAngleEccentricAnomalyFromMeanAnomaly(
-constAngle&aMeanAnomaly,constReal&anEccentricity,constReal&aTolerance
-);
-
-staticAngleTrueAnomalyFromMeanAnomaly(
-constAngle&aMeanAnomly,constReal&anEccentricity,constReal&aTolerance
-);
-
-staticRealComputeSemiLatusRectum(constReal&aSemiMajorAxis,constReal&anEccentricity);
-
-staticRealComputeAngularMomentum(
-constReal&aSemiMajorAxis,constReal&anEccentricity,constDerived&aGravitationalParameter
-);
-
-staticRealComputeAngularMomentum(constReal&aSemiLatusRectum,constDerived&aGravitationalParameter);
-
-staticRealComputeRadialDistance(constReal&aSemiMajorAxis,constReal&anEccentricity,constReal&trueAnomaly);
-
-staticTimeComputeMeanLTAN(constAngle&raan,constInstant&anInstant,constSun&sun=Sun::Default());
-
-staticTimeComputeLTAN(constAngle&raan,constInstant&anInstant,constSun&sun=Sun::Default());
-
-staticStringStringFromElement(constCOE::Element&anElement);
-
-protected:
-LengthsemiMajorAxis_;
-Realeccentricity_;
-Angleinclination_;
-Angleraan_;
-Angleaop_;
-Angleanomaly_;
-AnomalyTypeanomalyType_;
-
-COE(constLength&aSemiMajorAxis,
-constReal&anEccentricity,
-constAngle&anInclination,
-constAngle&aRaan,
-constAngle&anAop,
-constAngle&anAnomaly,
-constAnomalyType&anAnomalyType);
-
-private:
-staticAngleConvertAnomaly(
-constAngle&anAnomaly,
-constReal&anEccentricity,
-constAnomalyType&fromAnomalyType,
-constAnomalyType&toAnomalyType,
-constReal&aTolerance
-);
-
-staticAngleComputeEquationOfTime(constInstant&anInstant);
-};
-
-}//namespacekepler
-}//namespacemodel
-}//namespaceorbit
-}//namespacetrajectory
-}//namespaceastrodynamics
-}//namespaceostk
-
-#endif
+usingostk::physics::environment::object::Celestial;
+usingostk::physics::environment::object::celestial::Sun;
+usingostk::physics::time::Duration;
+usingostk::physics::time::Instant;
+usingostk::physics::time::Time;
+usingostk::physics::unit::Angle;
+usingostk::physics::unit::Derived;
+usingostk::physics::unit::Length;
+
+classCOE
+{
+public:
+enumclassElement
+{
+SemiMajorAxis,
+Eccentricity,
+Inclination,
+Raan,
+Aop,
+TrueAnomaly,
+MeanAnomaly,
+EccentricAnomaly
+};
+
+enumclassAnomalyType
+{
+True,
+Mean,
+Eccentric,
+};
+
+typedefPair<Position,Velocity>CartesianState;
+
+COE(constLength&aSemiMajorAxis,
+constReal&anEccentricity,
+constAngle&anInclination,
+constAngle&aRaan,
+constAngle&anAop,
+constAngle&aTrueAnomaly);
+
+booloperator==(constCOE&aCOE)const;
+
+booloperator!=(constCOE&aCOE)const;
+
+friendstd::ostream&operator<<(std::ostream&anOutputStream,constCOE&aCOE);
+
+boolisDefined()const;
+
+LengthgetSemiMajorAxis()const;
+
+RealgetEccentricity()const;
+
+AnglegetInclination()const;
+
+AnglegetRaan()const;
+
+AnglegetAop()const;
+
+virtualAnglegetTrueAnomaly()const;
+
+virtualAnglegetMeanAnomaly()const;
+
+virtualAnglegetEccentricAnomaly()const;
+
+LengthgetPeriapsisRadius()const;
+
+LengthgetApoapsisRadius()const;
+
+LengthgetSemiLatusRectum()const;
+
+LengthgetRadialDistance()const;
+
+DerivedgetAngularMomentum(constDerived&aGravitationalParameter)const;
+
+DerivedgetMeanMotion(constDerived&aGravitationalParameter)const;
+
+DerivedgetNodalPrecessionRate(
+constDerived&aGravitationalParameter,constLength&anEquatorialRadius,constReal&aJ2Parameter
+)const;
+
+DurationgetOrbitalPeriod(constDerived&aGravitationalParameter)const;
+
+COE::CartesianStategetCartesianState(constDerived&aGravitationalParameter,constShared<constFrame>&aFrameSPtr)
+const;
+
+Vector6dgetSIVector(constAnomalyType&anAnomalyType)const;
+
+voidprint(std::ostream&anOutputStream,booldisplayDecorator=true)const;
+
+staticCOEUndefined();
+
+staticCOECartesian(constCOE::CartesianState&aCartesianState,constDerived&aGravitationalParameter);
+
+staticCOEFromSIVector(constVector6d&aCOEVector,constAnomalyType&anAnomalyType);
+
+staticCOEFrozenOrbit(
+constLength&aSemiMajorAxis,
+constShared<constCelestial>&aCelestialObjectSPtr,
+constReal&anEccentricity=Real::Undefined(),
+constAngle&anInclination=Angle::Undefined(),
+constAngle&aRaan=Angle::Degrees(0.0),
+constAngle&anAop=Angle::Undefined(),
+constAngle&aTrueAnomaly=Angle::Degrees(0.0)
+);
+
+staticCOEFrozenOrbit(
+constLength&aSemiMajorAxis,
+constLength&anEquatorialRadius,
+constReal&aJ2,
+constReal&aJ3,
+constReal&anEccentricity=Real::Undefined(),
+constAngle&anInclination=Angle::Undefined(),
+constAngle&aRaan=Angle::Degrees(0.0),
+constAngle&anAop=Angle::Undefined(),
+constAngle&aTrueAnomaly=Angle::Degrees(0.0)
+);
+
+staticAngleEccentricAnomalyFromTrueAnomaly(constAngle&aTrueAnomaly,constReal&anEccentricity);
+
+staticAngleTrueAnomalyFromEccentricAnomaly(constAngle&anEccentricAnomaly,constReal&anEccentricity);
+
+staticAngleMeanAnomalyFromEccentricAnomaly(constAngle&anEccentricAnomaly,constReal&anEccentricity);
+
+staticAngleEccentricAnomalyFromMeanAnomaly(
+constAngle&aMeanAnomaly,constReal&anEccentricity,constReal&aTolerance
+);
+
+staticAngleTrueAnomalyFromMeanAnomaly(
+constAngle&aMeanAnomly,constReal&anEccentricity,constReal&aTolerance
+);
+
+staticRealComputeSemiLatusRectum(constReal&aSemiMajorAxis,constReal&anEccentricity);
+
+staticRealComputeAngularMomentum(
+constReal&aSemiMajorAxis,constReal&anEccentricity,constDerived&aGravitationalParameter
+);
+
+staticRealComputeAngularMomentum(constReal&aSemiLatusRectum,constDerived&aGravitationalParameter);
+
+staticRealComputeRadialDistance(constReal&aSemiMajorAxis,constReal&anEccentricity,constReal&trueAnomaly);
+
+staticTimeComputeMeanLTAN(constAngle&raan,constInstant&anInstant,constSun&sun=Sun::Default());
+
+staticTimeComputeLTAN(constAngle&raan,constInstant&anInstant,constSun&sun=Sun::Default());
+
+staticStringStringFromElement(constCOE::Element&anElement);
+
+protected:
+LengthsemiMajorAxis_;
+Realeccentricity_;
+Angleinclination_;
+Angleraan_;
+Angleaop_;
+Angleanomaly_;
+AnomalyTypeanomalyType_;
+
+COE(constLength&aSemiMajorAxis,
+constReal&anEccentricity,
+constAngle&anInclination,
+constAngle&aRaan,
+constAngle&anAop,
+constAngle&anAnomaly,
+constAnomalyType&anAnomalyType);
+
+private:
+staticAngleConvertAnomaly(
+constAngle&anAnomaly,
+constReal&anEccentricity,
+constAnomalyType&fromAnomalyType,
+constAnomalyType&toAnomalyType,
+constReal&aTolerance
+);
+
+staticAngleComputeEquationOfTime(constInstant&anInstant);
+};
+
+}//namespacekepler
+}//namespacemodel
+}//namespaceorbit
+}//namespacetrajectory
+}//namespaceastrodynamics
+}//namespaceostk
+
+#endif
     
     
   
diff --git a/xml/_orbit_8cpp.xml b/xml/_orbit_8cpp.xml
index 3e45fddee..02e5b649f 100644
--- a/xml/_orbit_8cpp.xml
+++ b/xml/_orbit_8cpp.xml
@@ -1560,344 +1560,380 @@
 return{orbitalModel,aCelestialObjectSPtr};
 }
 
-StringOrbit::StringFromFrameType(constOrbit::FrameType&aFrameType)
-{
-switch(aFrameType)
-{
-caseOrbit::FrameType::Undefined:
-return"Undefined";
-
-caseOrbit::FrameType::NED:
-return"NED";
-
-caseOrbit::FrameType::LVLH:
-return"LVLH";
-
-caseOrbit::FrameType::VVLH:
-return"VVLH";
-
-caseOrbit::FrameType::LVLHGD:
-return"LVLHGD";
-
-caseOrbit::FrameType::LVLHGDGT:
-return"LVLHGDGT";
-
-caseOrbit::FrameType::QSW:
-return"QSW";
-
-caseOrbit::FrameType::TNW:
-return"TNW";
-
-caseOrbit::FrameType::VNC:
-return"VNC";
+OrbitOrbit::Frozen(
+constInstant&anEpoch,
+constLength&anAltitude,
+constShared<constCelestial>&aCelestialObjectSPtr,
+constReal&anEccentricity,
+constAngle&anInclination,
+constAngle&aRaan,
+constAngle&anAop,
+constAngle&aTrueAnomaly
+)
+{
+if(!anEpoch.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Epoch");
+}
+if(!anAltitude.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Altitude");
+}
+if((aCelestialObjectSPtr==nullptr)||(!aCelestialObjectSPtr->isDefined()))
+{
+throwostk::core::error::runtime::Undefined("Celestialobject");
+}
+
+constLengthequatorialRadius=aCelestialObjectSPtr->getEquatorialRadius();
+constLengthsemiMajorAxis=equatorialRadius+anAltitude;
+
+constCOEcoe=COE::FrozenOrbit(
+semiMajorAxis,aCelestialObjectSPtr,anEccentricity,anInclination,aRaan,anAop,aTrueAnomaly
+);
 
-default:
-throwostk::core::error::runtime::Wrong("Frametype");
-break;
-}
+constKeplerorbitalModel={coe,anEpoch,{*aCelestialObjectSPtr},Kepler::PerturbationType::J2,false};
+
+return{orbitalModel,aCelestialObjectSPtr};
+}
 
-returnString::Empty();
-}
-
-StringOrbit::generateFrameName(constOrbit::FrameType&aFrameType)const
-{
-std::stringstreamstringStream;
-stringStream<<this;
-
-returnString::Format("{}@Orbit[{}]",Orbit::StringFromFrameType(aFrameType),stringStream.str());
-}
-
-Array<Pair<Index,Pass>>Orbit::ComputePasses(constArray<State>&aStateArray,constInteger&anInitialRevolutionNumber)
-{
-if(!anInitialRevolutionNumber.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Initialrevolutionnumber");
-}
-
-if(aStateArray.getSize()<2)
-{
-throwostk::core::error::RuntimeError(
-"Greaterthan2statesrequiredtocomputepasses:{}",aStateArray.getSize()
-);
-}
+StringOrbit::StringFromFrameType(constOrbit::FrameType&aFrameType)
+{
+switch(aFrameType)
+{
+caseOrbit::FrameType::Undefined:
+return"Undefined";
+
+caseOrbit::FrameType::NED:
+return"NED";
+
+caseOrbit::FrameType::LVLH:
+return"LVLH";
+
+caseOrbit::FrameType::VVLH:
+return"VVLH";
+
+caseOrbit::FrameType::LVLHGD:
+return"LVLHGD";
+
+caseOrbit::FrameType::LVLHGDGT:
+return"LVLHGDGT";
+
+caseOrbit::FrameType::QSW:
+return"QSW";
 
-for(Indexi=1;i<aStateArray.getSize();++i)
-{
-if(aStateArray[i-1].accessInstant()>aStateArray[i].accessInstant())
-{
-throwostk::core::error::RuntimeError("Statesarenotinchronologicalorder.");
-}
-}
-
-constorbit::model::Tabulatedtabulated=
-orbit::model::Tabulated(aStateArray,anInitialRevolutionNumber,Interpolator::Type::BarycentricRational);
+caseOrbit::FrameType::TNW:
+return"TNW";
+
+caseOrbit::FrameType::VNC:
+return"VNC";
+
+default:
+throwostk::core::error::runtime::Wrong("Frametype");
+break;
+}
 
-constArray<Pass>passes=Orbit::ComputePassesWithModel(
-tabulated,
-aStateArray.accessFirst().accessInstant(),
-aStateArray.accessLast().accessInstant(),
-anInitialRevolutionNumber
-);
-
-Array<Pair<Index,Pass>>passMap;
-passMap.reserve(passes.getSize());
-
-IndexstateIndex=0;
-IndexpassIndex=0;
-
-while(stateIndex<aStateArray.getSize())
+returnString::Empty();
+}
+
+StringOrbit::generateFrameName(constOrbit::FrameType&aFrameType)const
+{
+std::stringstreamstringStream;
+stringStream<<this;
+
+returnString::Format("{}@Orbit[{}]",Orbit::StringFromFrameType(aFrameType),stringStream.str());
+}
+
+Array<Pair<Index,Pass>>Orbit::ComputePasses(constArray<State>&aStateArray,constInteger&anInitialRevolutionNumber)
+{
+if(!anInitialRevolutionNumber.isDefined())
 {
-constInstant&stateInstant=aStateArray[stateIndex].accessInstant();
-
-if(passes[passIndex].accessInstantAtPassBreak().isDefined()&&
-stateInstant>=passes[passIndex].accessInstantAtPassBreak())
-{
-passMap.add({stateIndex,passes[passIndex]});
-++passIndex;
-}
-
-stateIndex++;
-}
-
-passMap.add({stateIndex,passes.accessLast()});
-
-returnpassMap;
-}
-
-Array<Pass>Orbit::ComputePassesWithModel(
-constorbit::Model&aModel,
-constInstant&aStartInstant,
-constInstant&anEndInstant,
-constInteger&aRevolutionNumber
-)
-{
-//[TBI]Dealw/z_ECIalwaysequalto0.0case(equatorialorbit)
-
-if(!aModel.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Model");
-}
+throwostk::core::error::runtime::Undefined("Initialrevolutionnumber");
+}
+
+if(aStateArray.getSize()<2)
+{
+throwostk::core::error::RuntimeError(
+"Greaterthan2statesrequiredtocomputepasses:{}",aStateArray.getSize()
+);
+}
+
+for(Indexi=1;i<aStateArray.getSize();++i)
+{
+if(aStateArray[i-1].accessInstant()>aStateArray[i].accessInstant())
+{
+throwostk::core::error::RuntimeError("Statesarenotinchronologicalorder.");
+}
+}
+
+constorbit::model::Tabulatedtabulated=
+orbit::model::Tabulated(aStateArray,anInitialRevolutionNumber,Interpolator::Type::BarycentricRational);
+
+constArray<Pass>passes=Orbit::ComputePassesWithModel(
+tabulated,
+aStateArray.accessFirst().accessInstant(),
+aStateArray.accessLast().accessInstant(),
+anInitialRevolutionNumber
+);
+
+Array<Pair<Index,Pass>>passMap;
+passMap.reserve(passes.getSize());
 
-if(!aRevolutionNumber.isDefined())
-{
-throwostk::core::error::runtime::Undefined("Revolutionnumber");
-}
-
-Array<Pass>passes=Array<Pass>::Empty();
+IndexstateIndex=0;
+IndexpassIndex=0;
+
+while(stateIndex<aStateArray.getSize())
+{
+constInstant&stateInstant=aStateArray[stateIndex].accessInstant();
 
-IntegerrevolutionNumber=aRevolutionNumber;
-InstantpreviousInstant=aStartInstant;
-StatepreviousState=aModel.calculateStateAt(previousInstant);
-
-InstantpreviousPassEndInstant=(Real(previousState.getPosition().accessCoordinates().z()).isNear(0.0,epsilon))
-?previousState.accessInstant()
-:Instant::Undefined();
-
-InstantnorthPointCrossing=Instant::Undefined();
-InstantdescendingNodeCrossing=Instant::Undefined();
-InstantsouthPointCrossing=Instant::Undefined();
-InstantpassBreakCrossing=Instant::Undefined();
-
-constboolisForwardPropagated=aStartInstant<anEndInstant;
-DurationstepDuration=Duration::Minutes(5.0);
-
-while(true)
-{
-if((isForwardPropagated&&(previousInstant>=anEndInstant))||
-(!isForwardPropagated&&(previousInstant<=anEndInstant)))
-{
-break;
-}
+if(passes[passIndex].accessInstantAtPassBreak().isDefined()&&
+stateInstant>=passes[passIndex].accessInstantAtPassBreak())
+{
+passMap.add({stateIndex,passes[passIndex]});
+++passIndex;
+}
+
+stateIndex++;
+}
+
+passMap.add({stateIndex,passes.accessLast()});
+
+returnpassMap;
+}
+
+Array<Pass>Orbit::ComputePassesWithModel(
+constorbit::Model&aModel,
+constInstant&aStartInstant,
+constInstant&anEndInstant,
+constInteger&aRevolutionNumber
+)
+{
+//[TBI]Dealw/z_ECIalwaysequalto0.0case(equatorialorbit)
 
-std::tie(northPointCrossing,descendingNodeCrossing,southPointCrossing,passBreakCrossing)=
-Orbit::ComputeCrossings(aModel,previousInstant,stepDuration,isForwardPropagated,anEndInstant);
-
-Passpass={
-revolutionNumber,
-isForwardPropagated?previousPassEndInstant:passBreakCrossing,
-northPointCrossing,
-descendingNodeCrossing,
-southPointCrossing,
-isForwardPropagated?passBreakCrossing:previousPassEndInstant,
-};
+if(!aModel.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Model");
+}
+
+if(!aRevolutionNumber.isDefined())
+{
+throwostk::core::error::runtime::Undefined("Revolutionnumber");
+}
+
+Array<Pass>passes=Array<Pass>::Empty();
 
-passes.add(pass);
-
-//ifforwardpropagatingandthepasshasanundefinedPassBreak,thenwehavecrossedtheendoftheinterval
-//ifbackwardpropagatingandthepasshasanundefinedAscendingNode,thenwehavecrossedtheendofthe
-//interval
-if((isForwardPropagated&&!pass.accessInstantAtPassBreak().isDefined())||
-(!isForwardPropagated&&!pass.accessInstantAtAscendingNode().isDefined()))
-{
-break;
-}
-
-revolutionNumber+=isForwardPropagated?1:-1;
-previousPassEndInstant=passBreakCrossing;
-
-if(pass.isComplete())
-{
-Array<Duration>durations={
-(pass.accessInstantAtNorthPoint()-pass.accessInstantAtAscendingNode()),
-(pass.accessInstantAtDescendingNode()-pass.accessInstantAtNorthPoint()),
-(pass.accessInstantAtSouthPoint()-pass.accessInstantAtDescendingNode()),
-(pass.accessInstantAtPassBreak()-pass.accessInstantAtSouthPoint()),
-};
-stepDuration=*std::min_element(durations.begin(),durations.end())/2.0;
-}
-
-previousInstant=isForwardPropagated?pass.accessInstantAtPassBreak()+Duration::Microseconds(1.0)
-:pass.accessInstantAtAscendingNode()-Duration::Microseconds(1.0);
-}
-
-returnpasses;
-}
-
-InstantOrbit::GetCrossingInstant(
-constInstant&anEpoch,
-constInstant&previousInstant,
-constInstant&currentInstant,
-conststd::function<double(double)>&getValue
-)
-{
-constRootSolver::Solutionsolution=
-rootSolver.bisection(getValue,(previousInstant-anEpoch).inSeconds(),(currentInstant-anEpoch).inSeconds());
-
-if(!solution.hasConverged)
-{
-throwostk::core::error::RuntimeError("Rootsolverdidnotconverge.");
-}
+IntegerrevolutionNumber=aRevolutionNumber;
+InstantpreviousInstant=aStartInstant;
+StatepreviousState=aModel.calculateStateAt(previousInstant);
+
+InstantpreviousPassEndInstant=(Real(previousState.getPosition().accessCoordinates().z()).isNear(0.0,epsilon))
+?previousState.accessInstant()
+:Instant::Undefined();
+
+InstantnorthPointCrossing=Instant::Undefined();
+InstantdescendingNodeCrossing=Instant::Undefined();
+InstantsouthPointCrossing=Instant::Undefined();
+InstantpassBreakCrossing=Instant::Undefined();
+
+constboolisForwardPropagated=aStartInstant<anEndInstant;
+DurationstepDuration=Duration::Minutes(5.0);
+
+while(true)
+{
+if((isForwardPropagated&&(previousInstant>=anEndInstant))||
+(!isForwardPropagated&&(previousInstant<=anEndInstant)))
+{
+break;
+}
+
+std::tie(northPointCrossing,descendingNodeCrossing,southPointCrossing,passBreakCrossing)=
+Orbit::ComputeCrossings(aModel,previousInstant,stepDuration,isForwardPropagated,anEndInstant);
+
+Passpass={
+revolutionNumber,
+isForwardPropagated?previousPassEndInstant:passBreakCrossing,
+northPointCrossing,
+descendingNodeCrossing,
+southPointCrossing,
+isForwardPropagated?passBreakCrossing:previousPassEndInstant,
+};
+
+passes.add(pass);
+
+//ifforwardpropagatingandthepasshasanundefinedPassBreak,thenwehavecrossedtheendoftheinterval
+//ifbackwardpropagatingandthepasshasanundefinedAscendingNode,thenwehavecrossedtheendofthe
+//interval
+if((isForwardPropagated&&!pass.accessInstantAtPassBreak().isDefined())||
+(!isForwardPropagated&&!pass.accessInstantAtAscendingNode().isDefined()))
+{
+break;
+}
 
-returnanEpoch+Duration::Seconds(solution.root);
-}
+revolutionNumber+=isForwardPropagated?1:-1;
+previousPassEndInstant=passBreakCrossing;
 
-Tuple<Instant,Instant,Instant,Instant>Orbit::ComputeCrossings(
-constorbit::Model&aModel,
-InstantpreviousInstant,
-constDuration&aStepDuration,
-constbool&isForwardPropagated,
-constInstant&anEndInstant
-)
-{
-InstantnorthPointCrossing=Instant::Undefined();
-InstantsouthPointCrossing=Instant::Undefined();
-InstantdescendingNodeCrossing=Instant::Undefined();
-InstantpassBreakCrossing=Instant::Undefined();
-
-if(anEndInstant.isDefined())
-{
-if((isForwardPropagated&&(previousInstant>=anEndInstant))||
-(!isForwardPropagated&&(previousInstant<=anEndInstant)))
-{
-return{northPointCrossing,descendingNodeCrossing,southPointCrossing,passBreakCrossing};
-}
-}
-
-constInstantepoch=aModel.getEpoch();
-
-constStatepreviousState=aModel.calculateStateAt(previousInstant);
-RealpreviousStateCoordinates_ECI_z=previousState.getPosition().accessCoordinates().z();
-RealpreviousStateCoordinates_ECI_zdot=previousState.getVelocity().accessCoordinates().z();
+if(pass.isComplete())
+{
+Array<Duration>durations={
+(pass.accessInstantAtNorthPoint()-pass.accessInstantAtAscendingNode()),
+(pass.accessInstantAtDescendingNode()-pass.accessInstantAtNorthPoint()),
+(pass.accessInstantAtSouthPoint()-pass.accessInstantAtDescendingNode()),
+(pass.accessInstantAtPassBreak()-pass.accessInstantAtSouthPoint()),
+};
+stepDuration=*std::min_element(durations.begin(),durations.end())/2.0;
+}
+
+previousInstant=isForwardPropagated?pass.accessInstantAtPassBreak()+Duration::Microseconds(1.0)
+:pass.accessInstantAtAscendingNode()-Duration::Microseconds(1.0);
+}
+
+returnpasses;
+}
+
+InstantOrbit::GetCrossingInstant(
+constInstant&anEpoch,
+constInstant&previousInstant,
+constInstant&currentInstant,
+conststd::function<double(double)>&getValue
+)
+{
+constRootSolver::Solutionsolution=
+rootSolver.bisection(getValue,(previousInstant-anEpoch).inSeconds(),(currentInstant-anEpoch).inSeconds());
 
-constautogetZ=[&aModel,&epoch](constdouble&aDurationInSeconds)->Real
+if(!solution.hasConverged)
 {
-returnaModel.calculateStateAt(epoch+Duration::Seconds(aDurationInSeconds))
-.getPosition()
-.accessCoordinates()
-.z();
-};
+throwostk::core::error::RuntimeError("Rootsolverdidnotconverge.");
+}
+
+returnanEpoch+Duration::Seconds(solution.root);
+}
 
-constautogetZDot=[&aModel,&epoch](constdouble&aDurationInSeconds)->Real
-{
-returnaModel.calculateStateAt(epoch+Duration::Seconds(aDurationInSeconds))
-.getVelocity()
-.accessCoordinates()
-.z();
-};
-
-constDurationstepDuration=isForwardPropagated?aStepDuration:-aStepDuration;
-
-boollastStep=false;
-
-while(!passBreakCrossing.isDefined()&&!lastStep)
-{
-InstantcurrentInstant=previousInstant+stepDuration;
-
-if(anEndInstant.isDefined())
+Tuple<Instant,Instant,Instant,Instant>Orbit::ComputeCrossings(
+constorbit::Model&aModel,
+InstantpreviousInstant,
+constDuration&aStepDuration,
+constbool&isForwardPropagated,
+constInstant&anEndInstant
+)
+{
+InstantnorthPointCrossing=Instant::Undefined();
+InstantsouthPointCrossing=Instant::Undefined();
+InstantdescendingNodeCrossing=Instant::Undefined();
+InstantpassBreakCrossing=Instant::Undefined();
+
+if(anEndInstant.isDefined())
+{
+if((isForwardPropagated&&(previousInstant>=anEndInstant))||
+(!isForwardPropagated&&(previousInstant<=anEndInstant)))
 {
-if((isForwardPropagated&&(currentInstant>=anEndInstant))||
-(!isForwardPropagated&&(currentInstant<=anEndInstant)))
-{
-currentInstant=anEndInstant;
-lastStep=true;
-}
-}
-
-constStatecurrentState=aModel.calculateStateAt(currentInstant);
-constRealcurrentStateCoordinates_ECI_z=currentState.getPosition().accessCoordinates().z();
-constRealcurrentStateCoordinates_ECI_zdot=currentState.getVelocity().accessCoordinates().z();
-
-if((previousStateCoordinates_ECI_z==0.0)&&(currentStateCoordinates_ECI_z==0.0))
-{
-throwostk::core::error::runtime::ToBeImplemented("Equatorialorbitsupport.");
-}
-
-if(((previousStateCoordinates_ECI_zdot>0.0)&&(currentStateCoordinates_ECI_zdot<=0.0))||
-((previousStateCoordinates_ECI_zdot<0.0)&&(currentStateCoordinates_ECI_zdot>=0.0)))
-{
-if(currentStateCoordinates_ECI_z>0.0)
-{
-northPointCrossing=Orbit::GetCrossingInstant(epoch,previousInstant,currentInstant,getZDot);
-}
-else
-{
-southPointCrossing=Orbit::GetCrossingInstant(epoch,previousInstant,currentInstant,getZDot);
-}
-}
+return{northPointCrossing,descendingNodeCrossing,southPointCrossing,passBreakCrossing};
+}
+}
+
+constInstantepoch=aModel.getEpoch();
+
+constStatepreviousState=aModel.calculateStateAt(previousInstant);
+RealpreviousStateCoordinates_ECI_z=previousState.getPosition().accessCoordinates().z();
+RealpreviousStateCoordinates_ECI_zdot=previousState.getVelocity().accessCoordinates().z();
+
+constautogetZ=[&aModel,&epoch](constdouble&aDurationInSeconds)->Real
+{
+returnaModel.calculateStateAt(epoch+Duration::Seconds(aDurationInSeconds))
+.getPosition()
+.accessCoordinates()
+.z();
+};
+
+constautogetZDot=[&aModel,&epoch](constdouble&aDurationInSeconds)->Real
+{
+returnaModel.calculateStateAt(epoch+Duration::Seconds(aDurationInSeconds))
+.getVelocity()
+.accessCoordinates()
+.z();
+};
+
+constDurationstepDuration=isForwardPropagated?aStepDuration:-aStepDuration;
+
+boollastStep=false;
 
-if((previousStateCoordinates_ECI_z>0.0)&&(currentStateCoordinates_ECI_z<=0.0))
-{
-constInstantcrossingInstant=Orbit::GetCrossingInstant(epoch,previousInstant,currentInstant,getZ);
+while(!passBreakCrossing.isDefined()&&!lastStep)
+{
+InstantcurrentInstant=previousInstant+stepDuration;
 
-if(isForwardPropagated)
-{
-descendingNodeCrossing=crossingInstant;
-}
-else
-{
-passBreakCrossing=crossingInstant;
+if(anEndInstant.isDefined())
+{
+if((isForwardPropagated&&(currentInstant>=anEndInstant))||
+(!isForwardPropagated&&(currentInstant<=anEndInstant)))
+{
+currentInstant=anEndInstant;
+lastStep=true;
 }
 }
 
-if((previousStateCoordinates_ECI_z<0.0)&&(currentStateCoordinates_ECI_z>=0.0))
-{
-constInstantcrossingInstant=Orbit::GetCrossingInstant(epoch,previousInstant,currentInstant,getZ);
-if(isForwardPropagated)
-{
-passBreakCrossing=crossingInstant;
-}
-else
-{
-descendingNodeCrossing=crossingInstant;
-}
-}
-
-previousStateCoordinates_ECI_z=currentStateCoordinates_ECI_z;
-previousStateCoordinates_ECI_zdot=currentStateCoordinates_ECI_zdot;
-previousInstant=currentInstant;
-}
-
-return{
-northPointCrossing,
-descendingNodeCrossing,
-southPointCrossing,
-passBreakCrossing,
-};
-}
+constStatecurrentState=aModel.calculateStateAt(currentInstant);
+constRealcurrentStateCoordinates_ECI_z=currentState.getPosition().accessCoordinates().z();
+constRealcurrentStateCoordinates_ECI_zdot=currentState.getVelocity().accessCoordinates().z();
+
+if((previousStateCoordinates_ECI_z==0.0)&&(currentStateCoordinates_ECI_z==0.0))
+{
+throwostk::core::error::runtime::ToBeImplemented("Equatorialorbitsupport.");
+}
+
+if(((previousStateCoordinates_ECI_zdot>0.0)&&(currentStateCoordinates_ECI_zdot<=0.0))||
+((previousStateCoordinates_ECI_zdot<0.0)&&(currentStateCoordinates_ECI_zdot>=0.0)))
+{
+if(currentStateCoordinates_ECI_z>0.0)
+{
+northPointCrossing=Orbit::GetCrossingInstant(epoch,previousInstant,currentInstant,getZDot);
+}
+else
+{
+southPointCrossing=Orbit::GetCrossingInstant(epoch,previousInstant,currentInstant,getZDot);
+}
+}
+
+if((previousStateCoordinates_ECI_z>0.0)&&(currentStateCoordinates_ECI_z<=0.0))
+{
+constInstantcrossingInstant=Orbit::GetCrossingInstant(epoch,previousInstant,currentInstant,getZ);
 
-}//namespacetrajectory
-}//namespaceastrodynamics
-}//namespaceostk
+if(isForwardPropagated)
+{
+descendingNodeCrossing=crossingInstant;
+}
+else
+{
+passBreakCrossing=crossingInstant;
+}
+}
+
+if((previousStateCoordinates_ECI_z<0.0)&&(currentStateCoordinates_ECI_z>=0.0))
+{
+constInstantcrossingInstant=Orbit::GetCrossingInstant(epoch,previousInstant,currentInstant,getZ);
+if(isForwardPropagated)
+{
+passBreakCrossing=crossingInstant;
+}
+else
+{
+descendingNodeCrossing=crossingInstant;
+}
+}
+
+previousStateCoordinates_ECI_z=currentStateCoordinates_ECI_z;
+previousStateCoordinates_ECI_zdot=currentStateCoordinates_ECI_zdot;
+previousInstant=currentInstant;
+}
+
+return{
+northPointCrossing,
+descendingNodeCrossing,
+southPointCrossing,
+passBreakCrossing,
+};
+}
+
+}//namespacetrajectory
+}//namespaceastrodynamics
+}//namespaceostk
     
     
   
diff --git a/xml/_orbit_8hpp.xml b/xml/_orbit_8hpp.xml
index f8cda6de3..94f9042e1 100644
--- a/xml/_orbit_8hpp.xml
+++ b/xml/_orbit_8hpp.xml
@@ -481,50 +481,61 @@
 constAngle&anArgumentOfLatitude=Angle::Zero()
 );
 
-staticStringStringFromFrameType(constOrbit::FrameType&aFrameType);
-
-staticArray<Pair<Index,Pass>>ComputePasses(
-constArray<State>&aStateArray,constInteger&anInitialRevolutionNumber
-);
-
-staticArray<Pass>ComputePassesWithModel(
-constorbit::Model&aModel,
-constInstant&aStartInstant,
-constInstant&anEndInstant,
-constInteger&anInitialRevolutionNumber
-);
-
-private:
-constorbit::Model*modelPtr_;
-
-Shared<constCelestial>celestialObjectSPtr_;
-
-mutablestd::mutexmutex_;
-mutableMap<Integer,Pass>passMap_;
-
-StringgenerateFrameName(constOrbit::FrameType&aFrameType)const;
-
-staticInstantGetCrossingInstant(
-constInstant&anEpoch,
-constInstant&previousInstant,
-constInstant&currentInstant,
-conststd::function<double(double)>&getValue
-);
-
-staticTuple<Instant,Instant,Instant,Instant>ComputeCrossings(
+staticOrbitFrozen(
+constInstant&anEpoch,
+constLength&anAltitude,
+constShared<constCelestial>&aCelestialObjectSPtr,
+constReal&anEccentricity=Real::Undefined(),
+constAngle&anInclination=Angle::Undefined(),
+constAngle&aRaan=Angle::Degrees(0.0),
+constAngle&anAop=Angle::Undefined(),
+constAngle&aTrueAnomaly=Angle::Degrees(0.0)
+);
+
+staticStringStringFromFrameType(constOrbit::FrameType&aFrameType);
+
+staticArray<Pair<Index,Pass>>ComputePasses(
+constArray<State>&aStateArray,constInteger&anInitialRevolutionNumber
+);
+
+staticArray<Pass>ComputePassesWithModel(
 constorbit::Model&aModel,
-InstantpreviousInstant,
-constDuration&stepDuration,
-constbool&isForwardPropagated,
-constInstant&anEndInstant=Instant::Undefined()
-);
-};
-
-}//namespacetrajectory
-}//namespaceastrodynamics
-}//namespaceostk
-
-#endif
+constInstant&aStartInstant,
+constInstant&anEndInstant,
+constInteger&anInitialRevolutionNumber
+);
+
+private:
+constorbit::Model*modelPtr_;
+
+Shared<constCelestial>celestialObjectSPtr_;
+
+mutablestd::mutexmutex_;
+mutableMap<Integer,Pass>passMap_;
+
+StringgenerateFrameName(constOrbit::FrameType&aFrameType)const;
+
+staticInstantGetCrossingInstant(
+constInstant&anEpoch,
+constInstant&previousInstant,
+constInstant&currentInstant,
+conststd::function<double(double)>&getValue
+);
+
+staticTuple<Instant,Instant,Instant,Instant>ComputeCrossings(
+constorbit::Model&aModel,
+InstantpreviousInstant,
+constDuration&stepDuration,
+constbool&isForwardPropagated,
+constInstant&anEndInstant=Instant::Undefined()
+);
+};
+
+}//namespacetrajectory
+}//namespaceastrodynamics
+}//namespaceostk
+
+#endif
     
     
   
diff --git a/xml/classostk_1_1astrodynamics_1_1trajectory_1_1_orbit.xml b/xml/classostk_1_1astrodynamics_1_1trajectory_1_1_orbit.xml
index 37cfd0c60..76426b325 100644
--- a/xml/classostk_1_1astrodynamics_1_1trajectory_1_1_orbit.xml
+++ b/xml/classostk_1_1astrodynamics_1_1trajectory_1_1_orbit.xml
@@ -105,7 +105,7 @@
         
         
         
-        
+        
       
       
         Shared< const Celestial >
@@ -118,7 +118,7 @@
         
         
         
-        
+        
       
       
         std::mutex
@@ -131,7 +131,7 @@
         
         
         
-        
+        
       
       
         Map< Integer, Pass >
@@ -144,7 +144,7 @@
         
         
         
-        
+        
       
       
       
@@ -950,6 +950,138 @@
         
         
       
+      
+        Orbit
+        Orbit ostk::astrodynamics::trajectory::Orbit::Frozen
+        (const Instant &anEpoch, const Length &anAltitude, const Shared< const Celestial > &aCelestialObjectSPtr, const Real &anEccentricity=Real::Undefined(), const Angle &anInclination=Angle::Undefined(), const Angle &aRaan=Angle::Degrees(0.0), const Angle &anAop=Angle::Undefined(), const Angle &aTrueAnomaly=Angle::Degrees(0.0))
+        Frozen
+        
+          const Instant &
+          anEpoch
+        
+        
+          const Length &
+          anAltitude
+        
+        
+          const Shared< const Celestial > &
+          aCelestialObjectSPtr
+        
+        
+          const Real &
+          anEccentricity
+          Real::Undefined()
+        
+        
+          const Angle &
+          anInclination
+          Angle::Undefined()
+        
+        
+          const Angle &
+          aRaan
+          Angle::Degrees(0.0)
+        
+        
+          const Angle &
+          anAop
+          Angle::Undefined()
+        
+        
+          const Angle &
+          aTrueAnomaly
+          Angle::Degrees(0.0)
+        
+        
+Constructs a Frozen orbit. 
+        
+        
+Model: Kepler (J2 Perturbation)
+The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.
+At a minimum, an epoch, altitude, and celestial body with a defined J2 and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.
+Additionally, the following combinations of inputs are supported:
+AoP (inclination set to critical value, eccentricity derived)
+AoP and eccentricity (inclination derived)
+AoP and inclination, but at least one of them must be a critical value (eccentricity derived)
+Inclination (AoP set to critical value, eccentricity derived)
+Eccentricity (AoP set to critical value, inclination derived)
+
+
+Note that inclination and eccentricity cannot both be provided.
+RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting Orbit as they do not impact the frozen orbit condition.
+
+
+anEpoch
+
+
+An orbit epoch 
+
+
+
+
+anAltitude
+
+
+An orbit altitude (wrt. equatorial radius) 
+
+
+
+
+aCelestialObjectSPtr
+
+
+A shared pointer to a central celestial body 
+
+
+
+
+anEccentricity
+
+
+An eccentricity 
+
+
+
+
+anInclination
+
+
+An inclination 
+
+
+
+
+aRaan
+
+
+A raan 
+
+
+
+
+anAop
+
+
+An aop 
+
+
+
+
+aTrueAnomaly
+
+
+A true anomaly 
+
+
+
+Frozen orbit 
+
+
+        
+        
+        
+        
+      
       
         String
         String ostk::astrodynamics::trajectory::Orbit::StringFromFrameType
@@ -978,7 +1110,7 @@
         
         
         
-        
+        
       
       
         Array< Pair< Index, Pass > >
@@ -1020,7 +1152,7 @@
         
         
         
-        
+        
       
       
         Array< Pass >
@@ -1086,7 +1218,7 @@
         
         
         
-        
+        
       
       
       
@@ -1105,7 +1237,7 @@
         
         
         
-        
+        
       
       
       
@@ -1173,7 +1305,7 @@
         
         
         
-        
+        
       
       
         Tuple< Instant, Instant, Instant, Instant >
@@ -1252,7 +1384,7 @@
         
         
         
-        
+        
       
       
     
@@ -1285,7 +1417,7 @@
         
       
     
-    
+    
     
       ostk::astrodynamics::trajectory::OrbitaccessModel
       ostk::astrodynamics::trajectory::OrbitcelestialObjectSPtr_
@@ -1297,6 +1429,7 @@
       ostk::astrodynamics::trajectory::OrbitConstPassIterator
       ostk::astrodynamics::trajectory::OrbitEquatorial
       ostk::astrodynamics::trajectory::OrbitFrameType
+      ostk::astrodynamics::trajectory::OrbitFrozen
       ostk::astrodynamics::trajectory::OrbitgenerateFrameName
       ostk::astrodynamics::trajectory::OrbitGeoSynchronous
       ostk::astrodynamics::trajectory::OrbitGetCrossingInstant
diff --git a/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1blm_1_1_brouwer_lyddane_mean.xml b/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1blm_1_1_brouwer_lyddane_mean.xml
index 0541cfdb6..2f128dd21 100644
--- a/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1blm_1_1_brouwer_lyddane_mean.xml
+++ b/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1blm_1_1_brouwer_lyddane_mean.xml
@@ -351,6 +351,8 @@
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeaneccentricity_
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanElement
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanFromSIVector
+      ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanFrozenOrbit
+      ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanFrozenOrbit
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeangetAngularMomentum
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeangetAop
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeangetApoapsisRadius
diff --git a/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1blm_1_1_brouwer_lyddane_mean_long.xml b/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1blm_1_1_brouwer_lyddane_mean_long.xml
index 0fb8aa649..71693e13a 100644
--- a/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1blm_1_1_brouwer_lyddane_mean_long.xml
+++ b/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1blm_1_1_brouwer_lyddane_mean_long.xml
@@ -320,6 +320,8 @@
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanLongElement
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanLongFromSIVector
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanLongFromSIVector
+      ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanLongFrozenOrbit
+      ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanLongFrozenOrbit
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanLonggetAngularMomentum
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanLonggetAop
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanLonggetApoapsisRadius
diff --git a/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1blm_1_1_brouwer_lyddane_mean_short.xml b/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1blm_1_1_brouwer_lyddane_mean_short.xml
index e354c6a9e..da86641b3 100644
--- a/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1blm_1_1_brouwer_lyddane_mean_short.xml
+++ b/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1blm_1_1_brouwer_lyddane_mean_short.xml
@@ -320,6 +320,8 @@
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanShortElement
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanShortFromSIVector
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanShortFromSIVector
+      ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanShortFrozenOrbit
+      ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanShortFrozenOrbit
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanShortgetAngularMomentum
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanShortgetAop
       ostk::astrodynamics::trajectory::orbit::model::blm::BrouwerLyddaneMeanShortgetApoapsisRadius
diff --git a/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1kepler_1_1_c_o_e.xml b/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1kepler_1_1_c_o_e.xml
index 28503b3fb..4ce75cf81 100644
--- a/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1kepler_1_1_c_o_e.xml
+++ b/xml/classostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1kepler_1_1_c_o_e.xml
@@ -70,7 +70,7 @@
         
         
         
-        
+        
       
       
         
@@ -102,7 +102,7 @@
         
         
         
-        
+        
       
       
         Pair< Position, Velocity >
@@ -115,7 +115,7 @@
         
         
         
-        
+        
       
       
       
@@ -130,7 +130,7 @@
         
         
         
-        
+        
       
       
         Real
@@ -143,7 +143,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -156,7 +156,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -169,7 +169,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -182,7 +182,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -195,7 +195,7 @@
         
         
         
-        
+        
       
       
         AnomalyType
@@ -208,7 +208,7 @@
         
         
         
-        
+        
       
       
       
@@ -298,7 +298,7 @@
         
         
         
-        
+        
       
       
         bool
@@ -328,7 +328,7 @@
         
         
         
-        
+        
       
       
         bool
@@ -358,7 +358,7 @@
         
         
         
-        
+        
       
       
         bool
@@ -375,7 +375,7 @@
         
         
         
-        
+        
       
       
         Length
@@ -392,7 +392,7 @@
         
         
         
-        
+        
       
       
         Real
@@ -409,7 +409,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -426,7 +426,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -443,7 +443,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -460,7 +460,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -478,7 +478,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -496,7 +496,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -514,7 +514,7 @@
         
         
         
-        
+        
       
       
         Length
@@ -531,7 +531,7 @@
         
         
         
-        
+        
       
       
         Length
@@ -548,7 +548,7 @@
         
         
         
-        
+        
       
       
         Length
@@ -565,7 +565,7 @@
         
         
         
-        
+        
       
       
         Length
@@ -582,7 +582,7 @@
         
         
         
-        
+        
       
       
         Derived
@@ -612,7 +612,7 @@
         
         
         
-        
+        
       
       
         Derived
@@ -642,7 +642,7 @@
         
         
         
-        
+        
       
       
         Derived
@@ -696,7 +696,7 @@
         
         
         
-        
+        
       
       
         Duration
@@ -726,7 +726,7 @@
         
         
         
-        
+        
       
       
         COE::CartesianState
@@ -768,7 +768,7 @@
         
         
         
-        
+        
       
       
         Vector6d
@@ -798,7 +798,7 @@
         
         
         
-        
+        
       
       
         void
@@ -839,7 +839,7 @@
         
         
         
-        
+        
       
       
       
@@ -885,7 +885,7 @@
         
         
         
-        
+        
       
       
       
@@ -906,7 +906,7 @@
         
         
         
-        
+        
       
       
         COE
@@ -948,7 +948,7 @@
         
         
         
-        
+        
       
       
         COE
@@ -990,7 +990,269 @@
         
         
         
-        
+        
+      
+      
+        COE
+        COE ostk::astrodynamics::trajectory::orbit::model::kepler::COE::FrozenOrbit
+        (const Length &aSemiMajorAxis, const Shared< const Celestial > &aCelestialObjectSPtr, const Real &anEccentricity=Real::Undefined(), const Angle &anInclination=Angle::Undefined(), const Angle &aRaan=Angle::Degrees(0.0), const Angle &anAop=Angle::Undefined(), const Angle &aTrueAnomaly=Angle::Degrees(0.0))
+        FrozenOrbit
+        
+          const Length &
+          aSemiMajorAxis
+        
+        
+          const Shared< const Celestial > &
+          aCelestialObjectSPtr
+        
+        
+          const Real &
+          anEccentricity
+          Real::Undefined()
+        
+        
+          const Angle &
+          anInclination
+          Angle::Undefined()
+        
+        
+          const Angle &
+          aRaan
+          Angle::Degrees(0.0)
+        
+        
+          const Angle &
+          anAop
+          Angle::Undefined()
+        
+        
+          const Angle &
+          aTrueAnomaly
+          Angle::Degrees(0.0)
+        
+        
+Construct a frozen orbit from an incomplete set of COEs. 
+        
+        
+The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.
+At a minimum, a semi-major axis and shared pointer to a central celestial body with a defined J2 and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.
+Additionally, the following combinations of inputs are supported:
+AoP (inclination set to critical value, eccentricity derived)
+AoP and eccentricity (inclination derived)
+AoP and inclination, but at least one of them must be a critical value (eccentricity derived)
+Inclination (AoP set to critical value, eccentricity derived)
+Eccentricity (AoP set to critical value, inclination derived)
+
+
+Note that inclination and eccentricity cannot both be provided.
+RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting COE as they do not impact the frozen orbit condition.
+
+
+aSemiMajorAxis
+
+
+A semi-major axis 
+
+
+
+
+aCelestialObjectSPtr
+
+
+A shared pointer to a central celestial body 
+
+
+
+
+anEccentricity
+
+
+An eccentricity 
+
+
+
+
+anInclination
+
+
+An inclination 
+
+
+
+
+aRaan
+
+
+A raan 
+
+
+
+
+anAop
+
+
+An aop 
+
+
+
+
+aTrueAnomaly
+
+
+A true anomaly 
+
+
+
+COE 
+
+
+        
+        
+        
+        
+      
+      
+        COE
+        COE ostk::astrodynamics::trajectory::orbit::model::kepler::COE::FrozenOrbit
+        (const Length &aSemiMajorAxis, const Length &anEquatorialRadius, const Real &aJ2, const Real &aJ3, const Real &anEccentricity=Real::Undefined(), const Angle &anInclination=Angle::Undefined(), const Angle &aRaan=Angle::Degrees(0.0), const Angle &anAop=Angle::Undefined(), const Angle &aTrueAnomaly=Angle::Degrees(0.0))
+        FrozenOrbit
+        
+          const Length &
+          aSemiMajorAxis
+        
+        
+          const Length &
+          anEquatorialRadius
+        
+        
+          const Real &
+          aJ2
+        
+        
+          const Real &
+          aJ3
+        
+        
+          const Real &
+          anEccentricity
+          Real::Undefined()
+        
+        
+          const Angle &
+          anInclination
+          Angle::Undefined()
+        
+        
+          const Angle &
+          aRaan
+          Angle::Degrees(0.0)
+        
+        
+          const Angle &
+          anAop
+          Angle::Undefined()
+        
+        
+          const Angle &
+          aTrueAnomaly
+          Angle::Degrees(0.0)
+        
+        
+Construct a frozen orbit from an incomplete set of COEs. 
+        
+        
+The critical angles for inclination are 63.4349 degrees and 116.5651 degrees. The critical angles for AoP are 90.0 degrees and 270.0 degrees.
+At a minimum, a semi-major axis, equatorial radius, J2, and J3 must be provided. In this case, the inclination and AoP are set to critical angles, and the eccentricity is derived from inclination. RAAN and true anomaly default to zero degrees.
+Additionally, the following combinations of inputs are supported:
+AoP (inclination set to critical value, eccentricity derived)
+AoP and eccentricity (inclination derived)
+AoP and inclination, but at least one of them must be a critical value (eccentricity derived)
+Inclination (AoP set to critical value, eccentricity derived)
+Eccentricity (AoP set to critical value, inclination derived)
+
+
+Note that inclination and eccentricity cannot both be provided.
+RAAN and True Anomaly may be provided alongside any of these arguments, and will be passed through to the resulting COE as they do not impact the frozen orbit condition.
+
+
+aSemiMajorAxis
+
+
+A semi-major axis 
+
+
+
+
+anEquatorialRadius
+
+
+An equatorial radius 
+
+
+
+
+aJ2
+
+
+A J2 
+
+
+
+
+aJ3
+
+
+A J3 
+
+
+
+
+anEccentricity
+
+
+An eccentricity 
+
+
+
+
+anInclination
+
+
+An inclination 
+
+
+
+
+aRaan
+
+
+A raan 
+
+
+
+
+anAop
+
+
+An aop 
+
+
+
+
+aTrueAnomaly
+
+
+A true anomaly 
+
+
+
+COE 
+
+
+        
+        
+        
+        
       
       
         Angle
@@ -1032,7 +1294,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -1074,7 +1336,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -1116,7 +1378,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -1170,7 +1432,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -1224,7 +1486,7 @@
         
         
         
-        
+        
       
       
         Real
@@ -1266,7 +1528,7 @@
         
         
         
-        
+        
       
       
         Real
@@ -1320,7 +1582,7 @@
         
         
         
-        
+        
       
       
         Real
@@ -1362,7 +1624,7 @@
         
         
         
-        
+        
       
       
         Real
@@ -1416,7 +1678,7 @@
         
         
         
-        
+        
       
       
         Time
@@ -1463,7 +1725,7 @@
         
         
         
-        
+        
       
       
         Time
@@ -1510,7 +1772,7 @@
         
         
         
-        
+        
       
       
         String
@@ -1540,7 +1802,7 @@
         
         
         
-        
+        
       
       
       
@@ -1642,7 +1904,7 @@
         
         
         
-        
+        
       
       
       
@@ -1722,7 +1984,7 @@
         
         
         
-        
+        
       
       
         Angle
@@ -1752,7 +2014,7 @@
         
         
         
-        
+        
       
       
     
@@ -1812,7 +2074,7 @@
         
       
     
-    
+    
     
       ostk::astrodynamics::trajectory::orbit::model::kepler::COEanomaly_
       ostk::astrodynamics::trajectory::orbit::model::kepler::COEAnomalyType
@@ -1835,6 +2097,8 @@
       ostk::astrodynamics::trajectory::orbit::model::kepler::COEeccentricity_
       ostk::astrodynamics::trajectory::orbit::model::kepler::COEElement
       ostk::astrodynamics::trajectory::orbit::model::kepler::COEFromSIVector
+      ostk::astrodynamics::trajectory::orbit::model::kepler::COEFrozenOrbit
+      ostk::astrodynamics::trajectory::orbit::model::kepler::COEFrozenOrbit
       ostk::astrodynamics::trajectory::orbit::model::kepler::COEgetAngularMomentum
       ostk::astrodynamics::trajectory::orbit::model::kepler::COEgetAop
       ostk::astrodynamics::trajectory::orbit::model::kepler::COEgetApoapsisRadius
diff --git a/xml/index.xml b/xml/index.xml
index 8a2bdedae..79f5ba42b 100644
--- a/xml/index.xml
+++ b/xml/index.xml
@@ -236,6 +236,8 @@
     Undefined
     Cartesian
     FromSIVector
+    FrozenOrbit
+    FrozenOrbit
     EccentricAnomalyFromTrueAnomaly
     TrueAnomalyFromEccentricAnomaly
     MeanAnomalyFromEccentricAnomaly
@@ -779,6 +781,7 @@
     CircularEquatorial
     GeoSynchronous
     SunSynchronous
+    Frozen
     StringFromFrameType
     ComputePasses
     ComputePassesWithModel
diff --git a/xml/namespaceostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1kepler.xml b/xml/namespaceostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1kepler.xml
index e80eb3ee4..bf25747a5 100644
--- a/xml/namespaceostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1kepler.xml
+++ b/xml/namespaceostk_1_1astrodynamics_1_1trajectory_1_1orbit_1_1model_1_1kepler.xml
@@ -15,7 +15,7 @@
         
         
         
-        
+        
       
       
         ostk::physics::environment::gravitational::Earth
@@ -28,7 +28,7 @@
         
         
         
-        
+        
       
       
       
@@ -44,7 +44,7 @@
         
         
         
-        
+        
       
       
         const Derived::Unit
@@ -58,7 +58,7 @@
         
         
         
-        
+        
       
       
         const Derived::Unit
@@ -72,7 +72,7 @@
         
         
         
-        
+        
       
       
         const Derived::Unit
@@ -97,7 +97,7 @@
         
         
         
-        
+        
       
       
       
@@ -142,7 +142,7 @@
         
         
         
-        
+