fr.cnes.sirius.patrius.stela.forces.gravity

Class StelaTesseralAttraction

java.lang.Object

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

fr.cnes.sirius.patrius.stela.forces.gravity.StelaTesseralAttraction

All Implemented Interfaces:

StelaForceModel, Serializable

public final class StelaTesseralAttraction
extends AbstractStelaLagrangeContribution

This class represent the tesseral perturbations

Since:

1.3

Version:

$Id$

Author:

Rami Houdroge

See Also:

Serialized Form

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.AbstractStelaLagrangeContribution

dPot

Constructor Summary

Constructors

Constructor and Description
StelaTesseralAttraction(PotentialCoefficientsProvider provider) Constructor.
StelaTesseralAttraction(PotentialCoefficientsProvider provider, int tesseralOrder, int qMax, double step, int nStep) Constructor.

Method Summary

Modifier and Type	Method and Description
protected void	computeCurrentQuad(Orbit orbit, double puser, int n, int m, int p, int q, double pP) Private method to reduce cyclomatic complexity.
protected double[]	computeEccentricityFunction(StelaEquinoctialOrbit orbit, TesseralQuad quad) Compute eccentricity function G(e) terms eabs(q)cos(qω), eabs(q)sin(qω) and its derivatives with respect to ex and ey.
protected double[]	computeF(StelaEquinoctialOrbit orbit, TesseralQuad quad) Compute inclination function F and its partial derivatives with respect to ix and iy.
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.
List<TesseralQuad>	getQuadsList() Getter for the quad list.
void	updateQuads(Orbit orbit) Compute quads (n, m, p, q).

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

StelaTesseralAttraction

public StelaTesseralAttraction(PotentialCoefficientsProvider provider)

Constructor.

Parameters:

provider - potential coefficients provider

StelaTesseralAttraction

public StelaTesseralAttraction(PotentialCoefficientsProvider provider,
                               int tesseralOrder,
                               int qMax,
                               double step,
                               int nStep)

Constructor.

Parameters:

provider - potential coefficients provider

tesseralOrder - the max order in the Kaula developpement

qMax - the maximum value of Q in the Kaula formulation

step - integration step

nStep - number of integration step

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

computeEccentricityFunction

protected double[] computeEccentricityFunction(StelaEquinoctialOrbit orbit,
                                               TesseralQuad quad)

Compute eccentricity function G(e) terms e^abs(q)cos(qω), e^abs(q)sin(qω) and its derivatives with respect to e_x and e_y.

Parameters:

orbit - position velocity in type 8

quad - quad (n, m, p, q)

Returns:

eccentricity function G(e) terms e^abs(q)cos(qω), e^abs(q)sin(qω) and its derivatives with respect to e_x and e_y

computeF

protected double[] computeF(StelaEquinoctialOrbit orbit,
                            TesseralQuad quad)

Compute inclination function F and its partial derivatives with respect to i_x and i_y.

Parameters:

orbit - orbit

quad - quad (n, m, p, q)

Returns:

inclination function F and its partial derivatives

updateQuads

public void updateQuads(Orbit orbit)

Compute quads (n, m, p, q).

Parameters:

orbit - orbit

computeCurrentQuad

protected void computeCurrentQuad(Orbit orbit,
                                  double puser,
                                  int n,
                                  int m,
                                  int p,
                                  int q,
                                  double pP)
                           throws PatriusException

Private method to reduce cyclomatic complexity.

Parameters:

orbit - orbit

puser - current puser

n - current n

m - current m

p - current p

q - current n

pP - current pP

Throws:

PatriusException - error when creating the TesseralQuad

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

getQuadsList

public List<TesseralQuad> getQuadsList()

Getter for the quad list.

Returns:

the quadsList