fr.cnes.sirius.patrius.stela.forces.radiation
Class StelaSRPSquaring

java.lang.Object
  fr.cnes.sirius.patrius.stela.forces.AbstractStelaGaussContribution
      fr.cnes.sirius.patrius.stela.forces.radiation.StelaSRPSquaring

All Implemented Interfaces:

StelaForceModel

public class StelaSRPSquaring
extends AbstractStelaGaussContribution

This class represents the Stela SRP model, which computes perturbations using the squaring method and the partial derivatives using the potential approximation.

Since:

1.3

Version:

$Id: StelaSRPSquaring.java 17584 2017-05-10 13:26:39Z bignon $

Author:

Rami Houdroge

See Also:

SRPSquaring, SRPPotential

Concurrency :

conditionally thread-safe

Concurrency comment :

thread-safe if the SRPSquaring and SRPPotential models are thread-safe.

Field Summary

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

dPert

Constructor Summary

StelaSRPSquaring(double mass, double surface, double reflectionCoef, int quadraturePoints, CelestialBody sunBody)
Create an instance of the SRP force Stela model.

StelaSRPSquaring(double mass, double surface, double reflectionCoef, int quadraturePoints, CelestialBody sunBody, double earthRadius, double dRef, double pRef)
Create an instance of the SRP force Stela model.

Method Summary

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

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

computeGaussDerivativeEquations, computeGaussEquations, getdPert, getType

Methods inherited from class java.lang.Object

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

Constructor Detail

StelaSRPSquaring

public StelaSRPSquaring(double mass,
                        double surface,
                        double reflectionCoef,
                        int quadraturePoints,
                        CelestialBody sunBody)
                 throws OrekitException

Create an instance of the SRP force Stela model.

Parameters:

mass - mass of spacecraft

surface - radiative surface of spacecraft

reflectionCoef - reflection coefficient of spacecraft

quadraturePoints - number of quadrature points

sunBody - sun as a celestialbody

Throws:

OrekitException - if the mass is negative (OrekitMessages.MASS_ARGUMENT_IS_NEGATIVE)

StelaSRPSquaring

public StelaSRPSquaring(double mass,
                        double surface,
                        double reflectionCoef,
                        int quadraturePoints,
                        CelestialBody sunBody,
                        double earthRadius,
                        double dRef,
                        double pRef)
                 throws OrekitException

Create an instance of the SRP force Stela model.

Parameters:

mass - mass of spacecraft

surface - radiative surface of spacecraft

reflectionCoef - reflection coefficient of spacecraft

sunBody - sun as a celestialbody

quadraturePoints - number of quadrature points

earthRadius - earth radius

dRef - reference distant

pRef - reference solar pressure at dRef

Throws:

OrekitException - if the mass is negative (OrekitMessages.MASS_ARGUMENT_IS_NEGATIVE)

Method Detail

computeShortPeriods

public double[] computeShortPeriods(StelaEquinoctialOrbit orbit)
                             throws OrekitException

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

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

computePerturbation

public double[] computePerturbation(StelaEquinoctialOrbit orbit,
                                    OrbitNatureConverter converter)
                             throws OrekitException

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

Specified by:

computePerturbation in class AbstractStelaGaussContribution

Parameters:

orbit - current orbit information: date, kinematics

converter - mean / osculating parameters converter

Returns:

the perturbation dE/dt for the current force

Throws:

OrekitException - if perturbation computation fails

computePotentialPerturbation

public double[] computePotentialPerturbation(StelaEquinoctialOrbit orbit)
                                      throws OrekitException

Parameters:

orbit - the stela equinoctial orbit

Returns:

the potential perturbation

Throws:

OrekitException - the Orekit exception