org.orekit.forces.gravity

Class ThirdBodyAttractionEpoch

java.lang.Object

org.orekit.forces.gravity.ThirdBodyAttraction

org.orekit.forces.gravity.ThirdBodyAttractionEpoch

All Implemented Interfaces:

ForceModel, EventDetectorsProvider, ParameterDriversProvider

public class ThirdBodyAttractionEpoch
extends ThirdBodyAttraction

Third body attraction force model. This class is a copy of ThirdBodyAttraction class. The computation of derivatives of the acceleration w.r.t. the Epoch has been added.

Since:

10.2

Author:

Fabien Maussion, Véronique Pommier-Maurussane

Field Summary

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

ATTRACTION_COEFFICIENT_SUFFIX

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

DATATION_ACCURACY

Constructor Summary

Constructors

Constructor and Description
ThirdBodyAttractionEpoch(CelestialBody body) Simple constructor.

Method Summary

Modifier and Type	Method and Description
double[]	getDerivativesToEpoch(SpacecraftState s, double[] parameters) Compute derivatives of the state w.r.t epoch.

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

acceleration, acceleration, dependsOnPositionOnly, 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.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

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

getEventDetectors, getFieldEventDetectors

Constructor Detail

ThirdBodyAttractionEpoch

public ThirdBodyAttractionEpoch(CelestialBody body)

Simple constructor.

Parameters:

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

Method Detail

getDerivativesToEpoch

public double[] getDerivativesToEpoch(SpacecraftState s,
                                      double[] parameters)

Compute derivatives of the state w.r.t epoch.

Parameters:

s - current state information: date, kinematics, attitude

parameters - values of the force model parameters

Returns:

derivatives