Package org.orekit.forces.gravity

Class ThirdBodyAttraction

java.lang.Object

org.orekit.forces.gravity.AbstractBodyAttraction

org.orekit.forces.gravity.ThirdBodyAttraction

All Implemented Interfaces:

ForceModel, EventDetectorsProvider, ParameterDriversProvider

Direct Known Subclasses:

ThirdBodyAttractionEpoch

public class ThirdBodyAttraction
extends AbstractBodyAttraction

Third body attraction force model.

Author:

Fabien Maussion, Véronique Pommier-Maurussane

Field Summary

Fields inherited from class org.orekit.forces.gravity.AbstractBodyAttraction

ATTRACTION_COEFFICIENT_SUFFIX

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

DATATION_ACCURACY

Constructor Summary

Constructors

Constructor	Description
ThirdBodyAttraction(CelestialBody body)	Simple 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.

Methods inherited from class org.orekit.forces.gravity.AbstractBodyAttraction

dependsOnPositionOnly, getBody, getBodyName, getParametersDrivers

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.forces.ForceModel

addContribution, addContribution, getEventDetectors, getFieldEventDetectors, init, init

Methods inherited from interface org.orekit.utils.ParameterDriversProvider

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

Constructor Detail

ThirdBodyAttraction

public ThirdBodyAttraction(CelestialBody body)

Simple constructor.

Parameters:

body - the third body to consider (ex: CelestialBodies.getSun() or CelestialBodies.getMoon())

Method Detail

acceleration

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

Compute acceleration.

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)

Compute acceleration.

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