Package org.orekit.forces.gravity
Class ThirdBodyAttractionEpoch
- java.lang.Object
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- org.orekit.forces.gravity.AbstractBodyAttraction
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- org.orekit.forces.gravity.ThirdBodyAttraction
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- org.orekit.forces.gravity.ThirdBodyAttractionEpoch
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- All Implemented Interfaces:
ForceModel
,EventDetectorsProvider
,ParameterDriversProvider
public class ThirdBodyAttractionEpoch extends ThirdBodyAttraction
Third body attraction force model. This class is a copy ofThirdBodyAttraction
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
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Field Summary
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Fields inherited from class org.orekit.forces.gravity.AbstractBodyAttraction
ATTRACTION_COEFFICIENT_SUFFIX
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Fields inherited from interface org.orekit.propagation.events.EventDetectorsProvider
DATATION_ACCURACY
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Constructor Summary
Constructors Constructor Description ThirdBodyAttractionEpoch(CelestialBody body)
Simple constructor.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method 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
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Methods inherited from class org.orekit.forces.gravity.AbstractBodyAttraction
dependsOnPositionOnly, getBody, getBodyName, getBodyPosition, getBodyPosition, getBodyPVCoordinates, getBodyPVCoordinates, getParametersDrivers
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Methods inherited from class java.lang.Object
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
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Methods inherited from interface org.orekit.propagation.events.EventDetectorsProvider
getEventDetectors, getFieldEventDetectors
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Methods inherited from interface org.orekit.forces.ForceModel
addContribution, addContribution, dependsOnAttitudeRate, getEventDetectors, getFieldEventDetectors, init, init
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Methods inherited from interface org.orekit.utils.ParameterDriversProvider
getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported
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Constructor Detail
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ThirdBodyAttractionEpoch
public ThirdBodyAttractionEpoch(CelestialBody body)
Simple constructor.- Parameters:
body
- the third body to consider (ex:CelestialBodyFactory.getSun()
orCelestialBodyFactory.getMoon()
)
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Method Detail
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getDerivativesToEpoch
public double[] getDerivativesToEpoch(SpacecraftState s, double[] parameters)
Compute derivatives of the state w.r.t epoch.- Parameters:
s
- current state information: date, kinematics, attitudeparameters
- values of the force model parameters- Returns:
- derivatives
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