fr.cnes.sirius.patrius.forces.radiation

Class RediffusedRadiationPressure

java.lang.Object

fr.cnes.sirius.patrius.math.parameter.Parameterizable

fr.cnes.sirius.patrius.math.parameter.JacobiansParameterizable

fr.cnes.sirius.patrius.forces.radiation.RediffusedRadiationPressure

All Implemented Interfaces:

ForceModel, GradientModel, IJacobiansParameterizable, IParameterizable, Serializable

public final class RediffusedRadiationPressure
extends JacobiansParameterizable
implements ForceModel, GradientModel

Class that represents a rediffused radiative force.

The implementation of this class enables the computation of partial derivatives with respect to K0 albedo global coefficient, K0 infrared global coefficient, absorption, specular reflection or diffusion reflection coefficients.

Since:

1.2

Version:

$Id: RediffusedRadiationPressure.java 17582 2017-05-10 12:58:16Z bignon $

Author:

clauded

See Also:

Serialized Form

Concurrency :

conditionally thread-safe

Concurrency comment :

thread-safe if the CelestialBody attribute is.

Constructor Summary

Constructors

Constructor and Description
RediffusedRadiationPressure(CelestialBody inSun, Frame inBodyFrame, int inCorona, int inMeridian, IEmissivityModel inEmissivityModel, RediffusedRadiationSensitive inModel) Constructor.
RediffusedRadiationPressure(CelestialBody inSun, Frame inBodyFrame, int inCorona, int inMeridian, IEmissivityModel inEmissivityModel, RediffusedRadiationSensitive inModel, boolean computePD) Constructor.

Method Summary

Methods

Modifier and Type	Method and Description
void	addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
Vector3D	computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
boolean	computeGradientPosition() This method returns true if the acceleration partial derivatives with respect to position have to be computed.
boolean	computeGradientVelocity() This method returns true if the acceleration partial derivatives with respect to velocity have to be computed.
EventDetector[]	getEventsDetectors() Get the discrete events related to the model.

Methods inherited from class fr.cnes.sirius.patrius.math.parameter.JacobiansParameterizable

addJacobiansParameter, addJacobiansParameter, addJacobiansParameter, supportsJacobianParameter

Methods inherited from class fr.cnes.sirius.patrius.math.parameter.Parameterizable

addParameter, getParameters, supportsParameter

Methods inherited from class java.lang.Object

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

Methods inherited from interface fr.cnes.sirius.patrius.math.parameter.IParameterizable

getParameters, supportsParameter

Constructor Detail

RediffusedRadiationPressure

public RediffusedRadiationPressure(CelestialBody inSun,
                           Frame inBodyFrame,
                           int inCorona,
                           int inMeridian,
                           IEmissivityModel inEmissivityModel,
                           RediffusedRadiationSensitive inModel)
                            throws PatriusException

Constructor.

Parameters:

inSun - coordinate of sun

inBodyFrame - boby frame

inCorona - number of corona

inMeridian - number of meridian

inEmissivityModel - emissivity model

inModel - redistributed radiative model

Throws:

PatriusException - thrown if no radiative properties found

RediffusedRadiationPressure

public RediffusedRadiationPressure(CelestialBody inSun,
                           Frame inBodyFrame,
                           int inCorona,
                           int inMeridian,
                           IEmissivityModel inEmissivityModel,
                           RediffusedRadiationSensitive inModel,
                           boolean computePD)
                            throws PatriusException

Constructor.

Parameters:

inSun - coordinate of sun

inBodyFrame - boby frame

inCorona - number of corona

inMeridian - number of meridian

inEmissivityModel - emissivity model

inModel - redistributed radiative model

computePD - true if partial derivatives wrt position have to be computed

Throws:

PatriusException - thrown if no radiative properties found

Method Detail

addContribution

public void addContribution(SpacecraftState s,
                   TimeDerivativesEquations adder)
                     throws PatriusException

Compute the contribution of the force model to the perturbing acceleration.

Specified by:

addContribution in interface ForceModel

Parameters:

s - current state information: date, kinematics, attitude

adder - object where the contribution should be added

Throws:

PatriusException - if some specific error occurs

computeAcceleration

public Vector3D computeAcceleration(SpacecraftState s)
                             throws PatriusException

Compute the acceleration due to the force.

Specified by:

computeAcceleration in interface ForceModel

Parameters:

s - current state information: date, kinematics, attitude

Returns:

acceleration in the SpacecraftState frame

Throws:

PatriusException - if some specific error occurs

getEventsDetectors

public EventDetector[] getEventsDetectors()

Get the discrete events related to the model.

Specified by:

getEventsDetectors in interface ForceModel

Returns:

array of events detectors or null if the model is not related to any discrete events

addDAccDState

public void addDAccDState(SpacecraftState s,
                 double[][] dAccdPos,
                 double[][] dAccdVel)
                   throws PatriusException

Compute acceleration derivatives with respect to state parameters.

Specified by:

addDAccDState in interface IJacobiansParameterizable

Parameters:

s - spacecraft state

dAccdPos - acceleration derivatives with respect to position

dAccdVel - acceleration derivatives with respect to velocity

Throws:

PatriusException - if derivatives cannot be computed

addDAccDParam

public void addDAccDParam(SpacecraftState s,
                 Parameter param,
                 double[] dAccdParam)
                   throws PatriusException

Compute acceleration derivatives with respect to additional parameters.
K0ALBEDO_COEFFICIENT -->derivatives with respect to the K0 albedo global coefficient
K0IR_COEFFICIENT --> derivatives with respect to the K0 infrared global coefficient
ABSORPTION_COEFFICIENT --> derivatives with respect to the absorption coefficient
SPECULAR_COEFFICIENT --> derivatives with respect to the specular reflection coefficient
DIFFUSION_COEFFICIENT --> derivatives with respect to the diffusion reflection coefficient

Specified by:

addDAccDParam in interface IJacobiansParameterizable

Parameters:

s - spacecraft state

param - the parameter with respect to which derivatives are required

dAccdParam - acceleration derivatives with respect to specified parameters

Throws:

PatriusException - if derivatives cannot be computed

computeGradientPosition

public boolean computeGradientPosition()

This method returns true if the acceleration partial derivatives with respect to position have to be computed.

Specified by:

computeGradientPosition in interface GradientModel

Returns:

true if the derivatives have to be computed, false otherwise

computeGradientVelocity

public boolean computeGradientVelocity()

This method returns true if the acceleration partial derivatives with respect to velocity have to be computed.

Specified by:

computeGradientVelocity in interface GradientModel

Returns:

true if the derivatives have to be computed, false otherwise