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

第三体引力模型。这个类是 ThirdBodyAttraction 类的一个副本。已添加了关于加速度相对于历元的导数的计算。

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) 简单构造函数。

Method Summary

Modifier and Type	Method and Description
double[]	getDerivativesToEpoch(SpacecraftState s, double[] parameters) 计算状态相对于历元的导数。

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)

简单构造函数。

参数：

body - 要考虑的第三体（例如：CelestialBodyFactory.getSun() 或 CelestialBodyFactory.getMoon()）

Method Detail

getDerivativesToEpoch

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

计算状态相对于历元的导数。

参数：

s - 当前状态信息：日期、运动学、姿态

parameters - 力模型参数的值

返回：

导数