fr.cnes.sirius.patrius.assembly.models

Class DirectRadiativeModel

java.lang.Object

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

fr.cnes.sirius.patrius.assembly.models.DirectRadiativeModel

All Implemented Interfaces:

RadiationSensitive, IParameterizable, JacobianParametersProvider, Serializable

public final class DirectRadiativeModel
extends Parameterizable
implements RadiationSensitive

Class that represents a radiative model, based on the vehicle.

Since:

1.1

Version:

$Id: DirectRadiativeModel.java 18530 2017-11-28 08:31:18Z bignon $

Author:

mercadierg

See Also:

Serialized Form

Concurrency :

not thread-safe

Concurrency comment :

The use of a frame (Assembly attribute) linked to the tree of frames in each of the parts makes this class not thread-safe.

Field Summary

Fields

Modifier and Type	Field and Description
static String	K0_COEFFICIENT Parameter name for K0 coefficient.

Constructor Summary

Constructors

Constructor and Description
DirectRadiativeModel(Assembly inAssembly) Radiative model (the acceleration is computed from all the sub parts of the vehicle).
DirectRadiativeModel(Assembly inAssembly, double inK0Albedo) Radiative model (the acceleration is computed from all the sub parts of the vehicle).
DirectRadiativeModel(Assembly inAssembly, Parameter inK0Albedo) Radiative model (the acceleration is computed from all the sub parts of the vehicle).

Method Summary

Methods

Modifier and Type	Method and Description
void	addDSRPAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam, Vector3D satSunVector) Compute acceleration derivatives with respect to additional parameters.
void	addDSRPAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel, Vector3D satSunVector) Compute acceleration derivatives with respect to state parameters.
protected static Vector3D	forceOnFacet(SpacecraftState state, IPart part, Vector3D flux) Method to compute the force for a plane model.
protected static Vector3D	forceOnSphere(SpacecraftState state, IPart part, Vector3D flux, Frame mainPartFrame) Method to compute the force for a spherical model.
ArrayList<Parameter>	getJacobianParameters() Get the list of all jacobian parameters supported.
Vector3D	radiationPressureAcceleration(SpacecraftState state, Vector3D flux) Method to compute the radiation pressure acceleration, based on the assembly.

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

Field Detail

K0_COEFFICIENT

public static final String K0_COEFFICIENT

Parameter name for K0 coefficient.

See Also:

Constant Field Values

Constructor Detail

DirectRadiativeModel

public DirectRadiativeModel(Assembly inAssembly)

Radiative model (the acceleration is computed from all the sub parts of the vehicle).

Parameters:

inAssembly - The considered vehicle.

DirectRadiativeModel

public DirectRadiativeModel(Assembly inAssembly,
                    double inK0Albedo)

Radiative model (the acceleration is computed from all the sub parts of the vehicle).

Parameters:

inAssembly - The considered vehicle.

inK0Albedo - albedo global multiplicative factor

DirectRadiativeModel

public DirectRadiativeModel(Assembly inAssembly,
                    Parameter inK0Albedo)

Radiative model (the acceleration is computed from all the sub parts of the vehicle).

Parameters:

inAssembly - The considered vehicle.

inK0Albedo - albedo global multiplicative factor

Method Detail

radiationPressureAcceleration

public Vector3D radiationPressureAcceleration(SpacecraftState state,
                                     Vector3D flux)
                                       throws PatriusException

Method to compute the radiation pressure acceleration, based on the assembly.

Specified by:

radiationPressureAcceleration in interface RadiationSensitive

Parameters:

state - the current state of the spacecraft.

flux - the incoming flux.

Returns:

the acceleration applied on the assembly.

Throws:

PatriusException - when an error occurs.

addDSRPAccDState

public void addDSRPAccDState(SpacecraftState s,
                    double[][] dAccdPos,
                    double[][] dAccdVel,
                    Vector3D satSunVector)
                      throws PatriusException

Compute acceleration derivatives with respect to state parameters.

Specified by:

addDSRPAccDState in interface RadiationSensitive

Parameters:

s - spacecraft state

dAccdPos - acceleration derivatives with respect to position parameters

dAccdVel - acceleration derivatives with respect to velocity parameters

satSunVector - satellite to sun vector, expressed in the spacecraft frame

Throws:

PatriusException - if derivatives cannot be computed

addDSRPAccDParam

public void addDSRPAccDParam(SpacecraftState s,
                    Parameter param,
                    double[] dAccdParam,
                    Vector3D satSunVector)
                      throws PatriusException

Compute acceleration derivatives with respect to additional parameters.

Specified by:

addDSRPAccDParam in interface RadiationSensitive

Parameters:

s - spacecraft state

param - the parameter with respect to which derivatives are required

dAccdParam - acceleration derivatives with respect to additional parameters

satSunVector - satellite to sun vector, expressed in the spacecraft frame

Throws:

PatriusException - if derivatives cannot be computed

forceOnSphere

protected static Vector3D forceOnSphere(SpacecraftState state,
                     IPart part,
                     Vector3D flux,
                     Frame mainPartFrame)
                                 throws PatriusException

Method to compute the force for a spherical model.

Parameters:

state - the current state of the spacecraft.

part - the current part of the assembly.

flux - the incoming flux.

mainPartFrame - mainPartFrame

Returns:

the force applied on the part (cylinder, parallelepiped, sphere).

Throws:

PatriusException - thrown if computation failed

forceOnFacet

protected static Vector3D forceOnFacet(SpacecraftState state,
                    IPart part,
                    Vector3D flux)
                                throws PatriusException

Method to compute the force for a plane model.

Parameters:

state - the current state of the spacecraft.

part - the current part of the assembly.

flux - the incoming flux.

Returns:

the force applied on the plane.

Throws:

PatriusException - orekit frame exception

getJacobianParameters

public ArrayList<Parameter> getJacobianParameters()

Get the list of all jacobian parameters supported.

Specified by:

getJacobianParameters in interface JacobianParametersProvider

Returns:

the list of additional parameters for which the jacobians can be computed.