org.orekit.forces.radiation

Class IsotropicRadiationSingleCoefficient

java.lang.Object

org.orekit.forces.radiation.IsotropicRadiationSingleCoefficient

All Implemented Interfaces:

RadiationSensitive

public class IsotropicRadiationSingleCoefficient
extends Object
implements RadiationSensitive

This class represents the features of a simplified spacecraft.

This model uses a single coefficient cr, considered to be a RadiationSensitive.REFLECTION_COEFFICIENT.

Since:

7.1

Author:

Luc Maisonobe

See Also:

BoxAndSolarArraySpacecraft, IsotropicDrag, IsotropicRadiationCNES95Convention

Field Summary

Fields inherited from interface org.orekit.forces.radiation.RadiationSensitive

ABSORPTION_COEFFICIENT, REFLECTION_COEFFICIENT

Constructor Summary

Constructors

Constructor and Description
IsotropicRadiationSingleCoefficient(double crossSection, double cr) Simple constructor.

Method Summary

Modifier and Type	Method and Description
ParameterDriver[]	getRadiationParametersDrivers() Get the drivers for supported parameters.
FieldVector3D<DerivativeStructure>	radiationPressureAcceleration(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass, FieldVector3D<DerivativeStructure> flux) Compute the acceleration due to radiation pressure, with state derivatives.
Vector3D	radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux) Compute the acceleration due to radiation pressure.
FieldVector3D<DerivativeStructure>	radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, String paramName) Compute the acceleration due to radiation pressure, with parameters derivatives.

Methods inherited from class java.lang.Object

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

Methods inherited from interface org.orekit.forces.radiation.RadiationSensitive

getAbsorptionCoefficient, getRadiationParametersNames, getReflectionCoefficient, setAbsorptionCoefficient, setReflectionCoefficient

Constructor Detail

IsotropicRadiationSingleCoefficient

public IsotropicRadiationSingleCoefficient(double crossSection,
                                           double cr)

Simple constructor.

Parameters:

crossSection - Surface (m²)

cr - reflection coefficient

Method Detail

getRadiationParametersDrivers

public ParameterDriver[] getRadiationParametersDrivers()

Get the drivers for supported parameters.

Specified by:

getRadiationParametersDrivers in interface RadiationSensitive

Returns:

parameters drivers

radiationPressureAcceleration

public Vector3D radiationPressureAcceleration(AbsoluteDate date,
                                              Frame frame,
                                              Vector3D position,
                                              Rotation rotation,
                                              double mass,
                                              Vector3D flux)

Compute the acceleration due to radiation pressure.

Specified by:

radiationPressureAcceleration in interface RadiationSensitive

Parameters:

date - current date

frame - inertial reference frame for state (both orbit and attitude)

position - position of spacecraft in reference frame

rotation - orientation (attitude) of the spacecraft with respect to reference frame

mass - current mass

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

Returns:

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

radiationPressureAcceleration

public FieldVector3D<DerivativeStructure> radiationPressureAcceleration(AbsoluteDate date,
                                                                        Frame frame,
                                                                        FieldVector3D<DerivativeStructure> position,
                                                                        FieldRotation<DerivativeStructure> rotation,
                                                                        DerivativeStructure mass,
                                                                        FieldVector3D<DerivativeStructure> flux)

Compute the acceleration due to radiation pressure, with state derivatives.

Specified by:

radiationPressureAcceleration in interface RadiationSensitive

Parameters:

date - current date

frame - inertial reference frame for state (both orbit and attitude)

position - position of spacecraft in reference frame

rotation - orientation (attitude) of the spacecraft with respect to reference frame

mass - spacecraft mass

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

Returns:

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

radiationPressureAcceleration

public FieldVector3D<DerivativeStructure> radiationPressureAcceleration(AbsoluteDate date,
                                                                        Frame frame,
                                                                        Vector3D position,
                                                                        Rotation rotation,
                                                                        double mass,
                                                                        Vector3D flux,
                                                                        String paramName)
                                                                 throws OrekitException

Compute the acceleration due to radiation pressure, with parameters derivatives.

Specified by:

radiationPressureAcceleration in interface RadiationSensitive

Parameters:

date - current date

frame - inertial reference frame for state (both orbit and attitude)

position - position of spacecraft in reference frame

rotation - orientation (attitude) of the spacecraft with respect to reference frame

mass - current mass

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

paramName - name of the parameter with respect to which derivatives are required

Returns:

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

Throws:

OrekitException - if acceleration cannot be computed