org.orekit.propagation.semianalytical.dsst.forces

Class DSSTThirdBody

java.lang.Object

org.orekit.propagation.semianalytical.dsst.forces.DSSTThirdBody

All Implemented Interfaces:

DSSTForceModel

public class DSSTThirdBody
extends Object
implements DSSTForceModel

Third body attraction perturbation to the DSSTPropagator.

Author:

Romain Di Costanzo, Pascal Parraud

Constructor Summary

Constructors

Constructor and Description
DSSTThirdBody(CelestialBody body) Complete constructor.

Method Summary

Methods

Modifier and Type	Method and Description
CelestialBody	getBody() Get third body.
EventDetector[]	getEventsDetectors() Get the discrete events related to the model.
double[]	getMeanElementRate(SpacecraftState currentState) Computes the mean equinoctial elements rates dai / dt.
double[]	getShortPeriodicVariations(AbsoluteDate date, double[] meanElements) Computes the short periodic variations.
void	initialize(AuxiliaryElements aux) Computes the highest power of the eccentricity and the highest power of a/R3 to appear in the truncated analytical power series expansion.
void	initializeStep(AuxiliaryElements aux) Performs initialization at each integration step for the current force model.

Methods inherited from class java.lang.Object

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

Constructor Detail

DSSTThirdBody

public DSSTThirdBody(CelestialBody body)

Complete constructor.

Parameters:

body - the 3rd body to consider

See Also:

CelestialBodyFactory

Method Detail

getBody

public CelestialBody getBody()

Get third body.

Returns:

third body

initialize

public void initialize(AuxiliaryElements aux)
                throws OrekitException

Computes the highest power of the eccentricity and the highest power of a/R3 to appear in the truncated analytical power series expansion.

This method computes the upper value for the 3rd body potential and determines the maximal powers for the eccentricity and a/R3 producing potential terms bigger than a defined tolerance.

Specified by:

initialize in interface DSSTForceModel

Parameters:

aux - auxiliary elements related to the current orbit

Throws:

OrekitException - if some specific error occurs

initializeStep

public void initializeStep(AuxiliaryElements aux)
                    throws OrekitException

Performs initialization at each integration step for the current force model.

This method aims at being called before mean elements rates computation.

Specified by:

initializeStep in interface DSSTForceModel

Parameters:

aux - auxiliary elements related to the current orbit

Throws:

OrekitException - if some specific error occurs

getMeanElementRate

public double[] getMeanElementRate(SpacecraftState currentState)
                            throws OrekitException

Computes the mean equinoctial elements rates da_i / dt.

Specified by:

getMeanElementRate in interface DSSTForceModel

Parameters:

currentState - current state information: date, kinematics, attitude

Returns:

the mean element rates dai/dt

Throws:

OrekitException - if some specific error occurs

getShortPeriodicVariations

public double[] getShortPeriodicVariations(AbsoluteDate date,
                                  double[] meanElements)
                                    throws OrekitException

Computes the short periodic variations.

Specified by:

getShortPeriodicVariations in interface DSSTForceModel

Parameters:

date - current date

meanElements - mean elements at current date

Returns:

the short periodic variations

Throws:

OrekitException - if some specific error occurs

getEventsDetectors

public EventDetector[] getEventsDetectors()

Get the discrete events related to the model.

Specified by:

getEventsDetectors in interface DSSTForceModel

Returns:

array of events detectors or null if the model is not related to any discrete events