Package org.orekit.forces.maneuvers

Class Maneuver

java.lang.Object

org.orekit.forces.maneuvers.Maneuver

All Implemented Interfaces:

ForceModel, EventDetectorsProvider, ParameterDriversProvider

Direct Known Subclasses:

ConfigurableLowThrustManeuver, ConstantThrustManeuver

public class Maneuver
extends Object
implements ForceModel

A generic model for maneuvers with finite-valued acceleration magnitude, as opposed to instantaneous changes in the velocity vector which are defined via detectors (in ImpulseManeuver and FieldImpulseManeuver). It contains: - An attitude override, this is the attitude used during the maneuver, it can be different from the one used for propagation; - A maneuver triggers object from the trigger sub-package. It defines the triggers used to start and stop the maneuvers (dates or events for example). - A propulsion model from sub-package propulsion. It defines the thrust or ΔV, isp, flow rate etc.. Both the propulsion model and the maneuver triggers can contain parameter drivers (for estimation). The convention here is that the propulsion model drivers are given before the maneuver triggers when calling the method getParametersDrivers()

Since:

10.2

Author:

Maxime Journot

Field Summary

Fields inherited from interface org.orekit.propagation.events.EventDetectorsProvider

DATATION_ACCURACY

Constructor Summary

Constructors

Constructor	Description
Maneuver(AttitudeProvider attitudeOverride, ManeuverTriggers maneuverTriggers, PropulsionModel propulsionModel)	Generic maneuver constructor.

Method Summary

Modifier and Type	Method	Description
<T extends CalculusFieldElement<T>> FieldVector3D<T>	acceleration(FieldSpacecraftState<T> s, T[] parameters)	Compute acceleration.
Vector3D	acceleration(SpacecraftState s, double[] parameters)	Compute acceleration.
<T extends CalculusFieldElement<T>> void	addContribution(FieldSpacecraftState<T> s, FieldTimeDerivativesEquations<T> adder)	Compute the contribution of the force model to the perturbing acceleration.
void	addContribution(SpacecraftState s, TimeDerivativesEquations adder)	Compute the contribution of the force model to the perturbing acceleration.
boolean	dependsOnPositionOnly()	Check if force models depends on position only.
AttitudeProvider	getAttitudeOverride()	Get the attitude override used for the maneuver.
Control3DVectorCostType	getControl3DVectorCostType()	Get the control vector's cost type.
Stream<EventDetector>	getEventDetectors()	Get the discrete events related to the model.
<T extends CalculusFieldElement<T>> Stream<FieldEventDetector<T>>	getFieldEventDetectors(Field<T> field)	Get the discrete events related to the model.
ManeuverTriggers	getManeuverTriggers()	Get the maneuver triggers.
String	getName()	Get the name of the maneuver.
List<ParameterDriver>	getParametersDrivers()	Get the drivers for parameters.
PropulsionModel	getPropulsionModel()	Get the propulsion model.
<T extends CalculusFieldElement<T>> void	init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)	Initialize the force model at the start of propagation.
void	init(SpacecraftState initialState, AbsoluteDate target)	Initialize the force model at the start of propagation.

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Methods inherited from interface org.orekit.propagation.events.EventDetectorsProvider

getEventDetectors, getFieldEventDetectors

Methods inherited from interface org.orekit.utils.ParameterDriversProvider

getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported

Constructor Detail

Maneuver

public Maneuver(AttitudeProvider attitudeOverride,
                ManeuverTriggers maneuverTriggers,
                PropulsionModel propulsionModel)

Generic maneuver constructor.

Parameters:

attitudeOverride - attitude provider for the attitude during the maneuver

maneuverTriggers - maneuver triggers

propulsionModel - propulsion model

Method Detail

getName

public String getName()

Get the name of the maneuver. The name can be in the propulsion model, in the maneuver triggers or both. If it is in both it should be the same since it refers to the same maneuver. The name is inferred from the propulsion model first, then from the maneuver triggers if the propulsion model had an empty name.

Returns:

the name

getAttitudeOverride

public AttitudeProvider getAttitudeOverride()

Get the attitude override used for the maneuver.

Returns:

the attitude override

getControl3DVectorCostType

public Control3DVectorCostType getControl3DVectorCostType()

Get the control vector's cost type.

Returns:

control cost type

Since:

12.0

getPropulsionModel

public PropulsionModel getPropulsionModel()

Get the propulsion model.

Returns:

the propulsion model

getManeuverTriggers

public ManeuverTriggers getManeuverTriggers()

Get the maneuver triggers.

Returns:

the maneuver triggers

dependsOnPositionOnly

public boolean dependsOnPositionOnly()

Check if force models depends on position only.

Specified by:

dependsOnPositionOnly in interface ForceModel

Returns:

true if force model depends on position only, false if it depends on velocity, either directly or due to a dependency on attitude

init

public void init(SpacecraftState initialState,
                 AbsoluteDate target)

Initialize the force model at the start of propagation. This method will be called before any calls to ForceModel.addContribution(SpacecraftState, TimeDerivativesEquations), ForceModel.addContribution(FieldSpacecraftState, FieldTimeDerivativesEquations), ForceModel.acceleration(SpacecraftState, double[]) or ForceModel.acceleration(FieldSpacecraftState, CalculusFieldElement[])

The default implementation of this method does nothing.

Specified by:

init in interface ForceModel

Parameters:

initialState - spacecraft state at the start of propagation.

target - date of propagation. Not equal to initialState.getDate().

init

public <T extends CalculusFieldElement<T>> void init(FieldSpacecraftState<T> initialState,
                                                     FieldAbsoluteDate<T> target)

Initialize the force model at the start of propagation. This method will be called before any calls to ForceModel.addContribution(SpacecraftState, TimeDerivativesEquations), ForceModel.addContribution(FieldSpacecraftState, FieldTimeDerivativesEquations), ForceModel.acceleration(SpacecraftState, double[]) or ForceModel.acceleration(FieldSpacecraftState, CalculusFieldElement[])

The default implementation of this method does nothing.

Specified by:

init in interface ForceModel

Type Parameters:

T - type of the elements

Parameters:

initialState - spacecraft state at the start of propagation.

target - date of propagation. Not equal to initialState.getDate().

addContribution

public void addContribution(SpacecraftState s,
                            TimeDerivativesEquations adder)

Compute the contribution of the force model to the perturbing acceleration.

The default implementation simply adds the acceleration as a non-Keplerian acceleration.

Specified by:

addContribution in interface ForceModel

Parameters:

s - current state information: date, kinematics, attitude

adder - object where the contribution should be added

addContribution

public <T extends CalculusFieldElement<T>> void addContribution(FieldSpacecraftState<T> s,
                                                                FieldTimeDerivativesEquations<T> adder)

Compute the contribution of the force model to the perturbing acceleration.

Specified by:

addContribution in interface ForceModel

Type Parameters:

T - type of the elements

Parameters:

s - current state information: date, kinematics, attitude

adder - object where the contribution should be added

acceleration

public Vector3D acceleration(SpacecraftState s,
                             double[] parameters)

Description copied from interface: ForceModel

Compute acceleration.

Specified by:

acceleration in interface ForceModel

Parameters:

s - current state information: date, kinematics, attitude

parameters - values of the force model parameters at state date, only 1 value for each parameterDriver

Returns:

acceleration in same frame as state

acceleration

public <T extends CalculusFieldElement<T>> FieldVector3D<T> acceleration(FieldSpacecraftState<T> s,
                                                                         T[] parameters)

Description copied from interface: ForceModel

Compute acceleration.

Specified by:

acceleration in interface ForceModel

Type Parameters:

T - type of the elements

Parameters:

s - current state information: date, kinematics, attitude

parameters - values of the force model parameters at state date, only 1 value for each parameterDriver

Returns:

acceleration in same frame as state

getEventDetectors

public Stream<EventDetector> getEventDetectors()

Get the discrete events related to the model.

This method is not intended to be called several time, only once by a propagator, as it has the side effect of rebuilding the events detectors when called.

Specified by:

getEventDetectors in interface EventDetectorsProvider

Specified by:

getEventDetectors in interface ForceModel

Returns:

stream of event detectors

getFieldEventDetectors

public <T extends CalculusFieldElement<T>> Stream<FieldEventDetector<T>> getFieldEventDetectors(Field<T> field)

Get the discrete events related to the model.

This method is not intended to be called several time, only once by a propagator, as it has the side effect of rebuilding the events detectors when called.

Specified by:

getFieldEventDetectors in interface EventDetectorsProvider

Specified by:

getFieldEventDetectors in interface ForceModel

Type Parameters:

T - extends CalculusFieldElement<T>

Parameters:

field - field to which the state belongs

Returns:

stream of event detectors

getParametersDrivers

public List<ParameterDriver> getParametersDrivers()

Description copied from interface: ParameterDriversProvider

Get the drivers for parameters.

Specified by:

getParametersDrivers in interface ParameterDriversProvider

Returns:

drivers for parameters