fr.cnes.sirius.patrius.forces.radiation

Interface RadiationSensitive

All Superinterfaces:

JacobianParametersProvider, Serializable

All Known Implementing Classes:

DirectRadiativeModel

public interface RadiationSensitive
extends Serializable, JacobianParametersProvider

Interface for spacecraft that are sensitive to radiation pressure forces.

Author:

Luc Maisonobe, Pascal Parraud

See Also:

SolarRadiationPressureCircular

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.
Vector3D	radiationPressureAcceleration(SpacecraftState state, Vector3D flux) Compute the acceleration due to radiation pressure.

Methods inherited from interface fr.cnes.sirius.patrius.propagation.numerical.JacobianParametersProvider

getJacobianParameters

Method Detail

radiationPressureAcceleration

Vector3D radiationPressureAcceleration(SpacecraftState state,
                                     Vector3D flux)
                                       throws PatriusException

Compute the acceleration due to radiation pressure.

The computation includes all spacecraft specific characteristics like shape, area and coefficients.

Parameters:

state - current state information: date, kinematics, attitude

flux - radiation flux in the same inertial frame as spacecraft orbit

Returns:

spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)

Throws:

PatriusException - if acceleration cannot be computed

addDSRPAccDParam

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

Compute acceleration derivatives with respect to additional parameters.

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

addDSRPAccDState

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

Compute acceleration derivatives with respect to state parameters.

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