fr.cnes.sirius.patrius.stela.propagation
Class StelaPartialDerivativesEquations

java.lang.Object
  fr.cnes.sirius.patrius.stela.propagation.StelaPartialDerivativesEquations

All Implemented Interfaces:

StelaAdditionalEquations

public class StelaPartialDerivativesEquations
extends Object
implements StelaAdditionalEquations

This class represents a set of additional equations computing the partial derivatives of the state (orbit) with respect to initial state.

Since:

1.3

Version:

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

Author:

Tiziana Sabatini

Concurrency :

not thread-safe

Concurrency comment :

use of mutable attributes

Constructor Summary

StelaPartialDerivativesEquations(List<AbstractStelaGaussContribution> forcesG, List<AbstractStelaLagrangeContribution> forcesL, int recomputeStepIn, StelaGTOPropagator inStelaPropagator)
Simple constructor.

Method Summary

SpacecraftState	addInitialAdditionalState(SpacecraftState state)
void	computeDerivatives(StelaEquinoctialOrbit orbit, double[] p, double[] pDot) Compute the derivatives related to the additional state parameters.
Map<StelaForceModel,double[][]>	getDerivatives() Returns derivatives map .
int	getEquationsDimension()
double[][]	getMeanMotion() Returns mean motion from state transition matrix.
String	getName() Get the name of the additional state.
void	updateStepCounter() update step counter

Methods inherited from class java.lang.Object

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

Constructor Detail

StelaPartialDerivativesEquations

public StelaPartialDerivativesEquations(List<AbstractStelaGaussContribution> forcesG,
                                        List<AbstractStelaLagrangeContribution> forcesL,
                                        int recomputeStepIn,
                                        StelaGTOPropagator inStelaPropagator)

Simple constructor.

Parameters:

forcesG - the list of Gauss forces associated to the propagator

forcesL - the list of Lagrange forces associated to the propagator

recomputeStepIn - recompute every recomputeStepIn steps

inStelaPropagator - Stela propagator

Method Detail

getEquationsDimension

public int getEquationsDimension()

Specified by:

getEquationsDimension in interface StelaAdditionalEquations

Returns:

the additional equations dimension

getName

public String getName()

Description copied from interface: StelaAdditionalEquations

Get the name of the additional state.

Specified by:

getName in interface StelaAdditionalEquations

Returns:

name of the additional state

computeDerivatives

public void computeDerivatives(StelaEquinoctialOrbit orbit,
                               double[] p,
                               double[] pDot)
                        throws OrekitException

Description copied from interface: StelaAdditionalEquations

Compute the derivatives related to the additional state parameters.

Specified by:

computeDerivatives in interface StelaAdditionalEquations

Parameters:

orbit - current orbit information: date, kinematics

p - current value of the additional parameters

pDot - placeholder where the derivatives of the additional parameters should be put

Throws:

OrekitException - if some specific error occurs

getDerivatives

public Map<StelaForceModel,double[][]> getDerivatives()

Returns derivatives map .

Returns:

derivatives map

getMeanMotion

public double[][] getMeanMotion()

Returns mean motion from state transition matrix.

Returns:

mean motion from state transition matrix

updateStepCounter

public void updateStepCounter()

update step counter

addInitialAdditionalState

public SpacecraftState addInitialAdditionalState(SpacecraftState state)
                                          throws OrekitException

Specified by:

addInitialAdditionalState in interface StelaAdditionalEquations

Parameters:

state - before adding additional state

Returns:

the initial additional state

Throws:

OrekitException - should not happen