fr.cnes.sirius.patrius.stela.forces.noninertial
Class NonInertialContribution

java.lang.Object
  fr.cnes.sirius.patrius.stela.forces.AbstractStelaGaussContribution
      fr.cnes.sirius.patrius.stela.forces.noninertial.NonInertialContribution

All Implemented Interfaces:

StelaForceModel

public class NonInertialContribution
extends AbstractStelaGaussContribution

Class representing the non-inertial contribution for STELA propagator.

Since:

3.0

Version:

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

Author:

Emmanuel Bignon

Concurrency :

thread-safe

Field Summary

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

dPert

Constructor Summary

NonInertialContribution(int quadPointsIn, Frame referenceSystemIn)
Constructor.

Method Summary

Vector3D	computeOmega(AbsoluteDate date, Frame frame1, Frame frame2) Compute rotation vector of frame2 with respect to frame1 expressed in frame2, which is the rotation vector from frame1 to frame2.
Vector3D	computeOmegaDerivative(AbsoluteDate date, Frame frame1, Frame frame2, double dt) Compute rotation vector derivative from frame1 to frame2 using finite differences.
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.

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

NonInertialContribution

public NonInertialContribution(int quadPointsIn,
                               Frame referenceSystemIn)

Constructor.

Parameters:

quadPointsIn - number of points for Simpson' squaring (must be odd)

referenceSystemIn - reference system

Method Detail

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

computeOmegaDerivative

public Vector3D computeOmegaDerivative(AbsoluteDate date,
                                       Frame frame1,
                                       Frame frame2,
                                       double dt)
                                throws OrekitException

Compute rotation vector derivative from frame1 to frame2 using finite differences.

Parameters:

date - a date

frame1 - reference frame

frame2 - expression frame

dt - time difference for finite differences (s)

Returns:

rotation vector derivative from frame1 to frame2

Throws:

OrekitException - thrown if conversion is not available

computeOmega

public Vector3D computeOmega(AbsoluteDate date,
                             Frame frame1,
                             Frame frame2)
                      throws OrekitException

Compute rotation vector of frame2 with respect to frame1 expressed in frame2, which is the rotation vector from frame1 to frame2. Currently coded conversion are:

• Frame 1 (reference system): CIRF, ICRF, MOD
• Frame 2 (expression/integration frame): CIRF

Parameters:

date - a date

frame1 - reference frame

frame2 - expression frame

Returns:

rotation vector of frame2 with respect to frame1 expressed in frame2

Throws:

OrekitException - thrown if conversion is not available