fr.cnes.sirius.patrius.stela.forces.gravity
Class StelaThirdBodyAttraction

java.lang.Object
  fr.cnes.sirius.patrius.stela.forces.AbstractStelaLagrangeContribution
      fr.cnes.sirius.patrius.stela.forces.gravity.StelaThirdBodyAttraction

All Implemented Interfaces:

StelaForceModel

public class StelaThirdBodyAttraction
extends AbstractStelaLagrangeContribution

Class computing third body attraction perturbations.

It computes third body perturbations, short periods and partial derivatives depending on the degree of development asked.

Since:

1.3

Version:

$Id: StelaThirdBodyAttraction.java 13436 2015-05-19 12:31:36Z maggiorani $

Author:

Tiziana Sabatini

Concurrency :

not thread-safe

Concurrency comment :

not thread-safe because two threads can simultaneously modify attributes of the class

Field Summary

Fields inherited from class fr.cnes.sirius.patrius.stela.forces.AbstractStelaLagrangeContribution

dPot

Constructor Summary

StelaThirdBodyAttraction(CelestialBody thirdBody, int inThirdBodyDegreeMaxPerturbation, int inThirdBodyDegreeMaxShortPeriods, int inThirdBodyDegreeMaxPD)
Creates a Stela third body attraction force model.

Method Summary

double[][]	computePartialDerivatives(StelaEquinoctialOrbit orbit) Compute the partial derivatives for a given spacecraft state.
double[]	computePerturbation(StelaEquinoctialOrbit orbit) Compute the dE/dt force derivatives for a given spacecraft state.
double[]	computeShortPeriods(StelaEquinoctialOrbit orbit) Compute the short periodic variations for a given spacecraft state.

Methods inherited from class fr.cnes.sirius.patrius.stela.forces.AbstractStelaLagrangeContribution

getdPot, getType

Methods inherited from class java.lang.Object

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

Constructor Detail

StelaThirdBodyAttraction

public StelaThirdBodyAttraction(CelestialBody thirdBody,
                                int inThirdBodyDegreeMaxPerturbation,
                                int inThirdBodyDegreeMaxShortPeriods,
                                int inThirdBodyDegreeMaxPD)
                         throws OrekitException

Creates a Stela third body attraction force model.

Parameters:

thirdBody - the celestial third body

inThirdBodyDegreeMaxPerturbation - the max degree of computation of the perturbation

inThirdBodyDegreeMaxShortPeriods - the max degree of computation of the short periods

inThirdBodyDegreeMaxPD - the max degree of computation of the partial derivatives

Throws:

OrekitException

Method Detail

computePerturbation

public double[] computePerturbation(StelaEquinoctialOrbit orbit)
                             throws OrekitException

Description copied from class: AbstractStelaLagrangeContribution

Compute the dE/dt force derivatives for a given spacecraft state.

Specified by:

computePerturbation in class AbstractStelaLagrangeContribution

Parameters:

orbit - current orbit information: date, kinematics

Returns:

the perturbation dE/dt for the current force

Throws:

OrekitException - if perturbation computation fails

computeShortPeriods

public double[] computeShortPeriods(StelaEquinoctialOrbit orbit)
                             throws OrekitException

Description copied from interface: StelaForceModel

Compute the short periodic variations for a given spacecraft state.

Parameters:

orbit - current orbit information: date, kinematics

Returns:

the short periodic variations of the current force

Throws:

OrekitException - if short periods computation fails

computePartialDerivatives

public double[][] computePartialDerivatives(StelaEquinoctialOrbit orbit)
                                     throws OrekitException

Description copied from interface: StelaForceModel

Compute the partial derivatives for a given spacecraft state.

Parameters:

orbit - current orbit information: date, kinematics

Returns:

the partial derivatives of the current force

Throws:

OrekitException - if partial derivatives computation fails