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

Class SRPPotential

java.lang.Object

fr.cnes.sirius.patrius.stela.forces.AbstractStelaLagrangeContribution

fr.cnes.sirius.patrius.stela.forces.radiation.SRPPotential

All Implemented Interfaces:

StelaForceModel, Serializable

public class SRPPotential
extends AbstractStelaLagrangeContribution

This class represents the PRS Lagrange contribution in the STELA propagator context.

Note that short periods are not available with this model.

Since:

1.3

Version:

$Id$

Author:

Cédric Dental, Rami Houdroge

See Also:

Serialized Form

Concurrency :

conditionally thread-safe

Concurrency comment :

thread safe if the CelestialBody used is thread safe

Field Summary

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

dPot

Constructor Summary

Constructors

Constructor and Description
SRPPotential(PVCoordinatesProvider sun, double m, double s, double c) create a SRP Potential model using the sun and spacecraft characteristics.

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

getdPot, getType

Methods inherited from class java.lang.Object

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

Constructor Detail

SRPPotential

public SRPPotential(PVCoordinatesProvider sun,
                    double m,
                    double s,
                    double c)

create a SRP Potential model using the sun and spacecraft characteristics.

Parameters:

sun - sun as a celestial body

m - mass of spacecraft

s - surface of spacecraft

c - relexion coefficient of spacecraft

Method Detail

computePerturbation

public double[] computePerturbation(StelaEquinoctialOrbit orbit)
                             throws PatriusException

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:

PatriusException - if perturbation computation fails

computeShortPeriods

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

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

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