org.orekit.forces.radiation

Interface RadiationSensitive

All Known Implementing Classes:

BoxAndSolarArraySpacecraft, IsotropicRadiationClassicalConvention, IsotropicRadiationCNES95Convention, IsotropicRadiationSingleCoefficient

public interface RadiationSensitive

Interface for spacecraft that are sensitive to radiation pressure forces.

Author:

Luc Maisonobe, Pascal Parraud

See Also:

SolarRadiationPressure

Field Summary

Fields

Modifier and Type	Field and Description
static String	ABSORPTION_COEFFICIENT Parameter name for absorption coefficient.
static String	REFLECTION_COEFFICIENT Parameter name for reflection coefficient.

Method Summary

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

Field Detail

ABSORPTION_COEFFICIENT

static final String ABSORPTION_COEFFICIENT

Parameter name for absorption coefficient.

See Also:

Constant Field Values

REFLECTION_COEFFICIENT

static final String REFLECTION_COEFFICIENT

Parameter name for reflection coefficient.

See Also:

Constant Field Values

Method Detail

getRadiationParametersDrivers

ParameterDriver[] getRadiationParametersDrivers()

Get the drivers for supported parameters.

Returns:

parameters drivers

Since:

8.0

radiationPressureAcceleration

Vector3D radiationPressureAcceleration(AbsoluteDate date,
                                       Frame frame,
                                       Vector3D position,
                                       Rotation rotation,
                                       double mass,
                                       Vector3D flux,
                                       double[] parameters)
                                throws OrekitException

Compute the acceleration due to radiation pressure.

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

parameters - values of the force model parameters

Returns:

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

Throws:

OrekitException - if acceleration cannot be computed

radiationPressureAcceleration

<T extends RealFieldElement<T>> FieldVector3D<T> radiationPressureAcceleration(FieldAbsoluteDate<T> date,
                                                                               Frame frame,
                                                                               FieldVector3D<T> position,
                                                                               FieldRotation<T> rotation,
                                                                               T mass,
                                                                               FieldVector3D<T> flux,
                                                                               T[] parameters)
                                                                        throws OrekitException

Compute the acceleration due to radiation pressure.

Type Parameters:

T - extends RealFieldElement

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

parameters - values of the force model parameters

Returns:

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

Throws:

OrekitException - if acceleration cannot be computed

radiationPressureAcceleration

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

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

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

parameters - values of the force model parameters

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