fr.cnes.sirius.patrius.stela.forces.drag
Class StelaAtmosphericDrag

java.lang.Object
  fr.cnes.sirius.patrius.stela.forces.AbstractStelaGaussContribution
      fr.cnes.sirius.patrius.stela.forces.drag.StelaAtmosphericDrag

All Implemented Interfaces:

StelaForceModel

public class StelaAtmosphericDrag
extends AbstractStelaGaussContribution

Class representing the atmospheric drag for the Stela GTO extrapolator.

Since:

1.3

Version:

$Id: StelaAtmosphericDrag.java 16763 2016-10-10 09:31:17Z bignon $

Author:

Tiziana Sabatini

See Also:

StelaAeroModel

Concurrency :

not thread-safe

Concurrency comment :

not thread-safe due to use of mutable attributes

Field Summary

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

dPert

Constructor Summary

StelaAtmosphericDrag(DragSensitive inSpacecraft, Atmosphere inAtmosphere, int inSquaringPoints, double inEarthRadius, double inAtmoThreshold, int inDragRecomputeStep)
Constructor.

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[]	computeShortPeriods(StelaEquinoctialOrbit orbit) Compute the short periodic variations for a given spacecraft state.
int	getDragRecomputeStep()
void	setTransMatComputationFlag(boolean inTransMatFlag) Setter for the switch indicating whether the drag term of the transition matrix has to be computed.

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

StelaAtmosphericDrag

public StelaAtmosphericDrag(DragSensitive inSpacecraft,
                            Atmosphere inAtmosphere,
                            int inSquaringPoints,
                            double inEarthRadius,
                            double inAtmoThreshold,
                            int inDragRecomputeStep)

Constructor.

Parameters:

inSpacecraft - the drag sensitive spacecraft.

inAtmosphere - the atmospheric model.

inSquaringPoints - number of points for Simpson' Squaring.

inEarthRadius - the Earth radius.

inAtmoThreshold - the altitude of the upper atmospheric boundary.

inDragRecomputeStep - drag will be re-computed every inDragRecomputeStep steps (if value is 0, computed every substep)

Method Detail

getDragRecomputeStep

public int getDragRecomputeStep()

Returns:

the dragRecomputeStep

computePerturbation

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

Description copied from class: AbstractStelaGaussContribution

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

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

setTransMatComputationFlag

public void setTransMatComputationFlag(boolean inTransMatFlag)

Setter for the switch indicating whether the drag term of the transition matrix has to be computed.

Parameters:

inTransMatFlag - flag to set