org.orekit.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:
SolarRadiationPressure

Method Summary
 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 org.orekit.propagation.numerical.JacobianParametersProvider
getJacobianParameters
 

Method Detail

radiationPressureAcceleration

Vector3D radiationPressureAcceleration(SpacecraftState state,
                                       Vector3D flux)
                                       throws OrekitException
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:
OrekitException - if acceleration cannot be computed

addDSRPAccDParam

void addDSRPAccDParam(SpacecraftState s,
                      Parameter param,
                      double[] dAccdParam,
                      Vector3D satSunVector)
                      throws OrekitException
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:
OrekitException - if derivatives cannot be computed

addDSRPAccDState

void addDSRPAccDState(SpacecraftState s,
                      double[][] dAccdPos,
                      double[][] dAccdVel,
                      Vector3D satSunVector)
                      throws OrekitException
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:
OrekitException - if derivatives cannot be computed


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