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, Serializable

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.

Short periods are computed only using squaring model.

Since:

1.3

Version:

$Id$

Author:

Rami Houdroge

See Also:

SRPSquaring, SRPPotential, Serialized Form

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

Constructors

Constructor and Description
StelaSRPSquaring(double mass, double surface, double reflectionCoef, int quadraturePoints, CelestialPoint sun) Create an instance of the SRP force Stela model.
StelaSRPSquaring(double mass, double surface, double reflectionCoef, int quadraturePoints, CelestialPoint sun, double earthRadius, double dRef, double pRef) Create an instance of the SRP force Stela model.
StelaSRPSquaring(double mass, double surface, double reflectionCoef, int quadraturePoints, CelestialPoint sun, double earthRadius, double dRef, double pRef, int orderFS) Create an instance of the SRP force Stela model.

Method Summary

Modifier and Type	Method and Description
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, OrbitNatureConverter converter) Compute the short periodic variations for a given spacecraft state.

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

computeCoeffs, computeGaussDerivativeEquations, computeGaussEquations, computeQuadElements, evaluateFS, 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,
                        CelestialPoint sun)
                 throws PatriusException

Create an instance of the SRP force Stela model.

Fourier Series order for short periods computation is set to default value: 10.

Parameters:

mass - mass of spacecraft

surface - radiative surface of spacecraft

reflectionCoef - reflection coefficient of spacecraft

quadraturePoints - number of quadrature points

sun - Sun

Throws:

PatriusException - if the mass is negative (PatriusMessages.MASS_ARGUMENT_IS_NEGATIVE)

StelaSRPSquaring

public StelaSRPSquaring(double mass,
                        double surface,
                        double reflectionCoef,
                        int quadraturePoints,
                        CelestialPoint sun,
                        double earthRadius,
                        double dRef,
                        double pRef)
                 throws PatriusException

Create an instance of the SRP force Stela model.

Fourier Series order for short periods computation is set to default value: 10.

Parameters:

mass - mass of spacecraft

surface - radiative surface of spacecraft

reflectionCoef - reflection coefficient of spacecraft

sun - Sun

quadraturePoints - number of quadrature points

earthRadius - earth radius

dRef - reference distant

pRef - reference solar pressure at dRef

Throws:

PatriusException - if the mass is negative (PatriusMessages.MASS_ARGUMENT_IS_NEGATIVE)

StelaSRPSquaring

public StelaSRPSquaring(double mass,
                        double surface,
                        double reflectionCoef,
                        int quadraturePoints,
                        CelestialPoint sun,
                        double earthRadius,
                        double dRef,
                        double pRef,
                        int orderFS)
                 throws PatriusException

Create an instance of the SRP force Stela model.

Parameters:

mass - mass of spacecraft

surface - radiative surface of spacecraft

reflectionCoef - reflection coefficient of spacecraft

sun - Sun

quadraturePoints - number of quadrature points

earthRadius - earth radius

dRef - reference distant

pRef - reference solar pressure at dRef

orderFS - Fourier Series order for short periods computation

Throws:

PatriusException - if the mass is negative (PatriusMessages.MASS_ARGUMENT_IS_NEGATIVE)

Method Detail

computeShortPeriods

public double[] computeShortPeriods(StelaEquinoctialOrbit orbit,
                                    OrbitNatureConverter converter)
                             throws PatriusException

Compute the short periodic variations for a given spacecraft state.

Parameters:

orbit - current orbit information: date, kinematics

converter - converter necessary in some specific case (drag short periods computation)

Returns:

the short periodic variations of the current force

Throws:

PatriusException - if short periods computation fails

computePartialDerivatives

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

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:

PatriusException - if partial derivatives computation fails

computePerturbation

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

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:

PatriusException - if perturbation computation fails

computePotentialPerturbation

public double[] computePotentialPerturbation(StelaEquinoctialOrbit orbit)
                                      throws PatriusException

Parameters:

orbit - the stela equinoctial orbit

Returns:

the potential perturbation

Throws:

PatriusException - the Orekit exception