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.
org.hipparchus.geometry.euclidean.threed.Vector3D	radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters) Compute the acceleration due to radiation pressure.
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure>	radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters, String paramName) Compute the acceleration due to radiation pressure, with parameters derivatives.
<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>	radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position, org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation, T mass, org.hipparchus.geometry.euclidean.threed.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

org.hipparchus.geometry.euclidean.threed.Vector3D radiationPressureAcceleration(AbsoluteDate date,
                                                                                Frame frame,
                                                                                org.hipparchus.geometry.euclidean.threed.Vector3D position,
                                                                                org.hipparchus.geometry.euclidean.threed.Rotation rotation,
                                                                                double mass,
                                                                                org.hipparchus.geometry.euclidean.threed.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 org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> radiationPressureAcceleration(FieldAbsoluteDate<T> date,
                                                                                                                                       Frame frame,
                                                                                                                                       org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
                                                                                                                                       org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation,
                                                                                                                                       T mass,
                                                                                                                                       org.hipparchus.geometry.euclidean.threed.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

org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> radiationPressureAcceleration(AbsoluteDate date,
                                                                                                                                                  Frame frame,
                                                                                                                                                  org.hipparchus.geometry.euclidean.threed.Vector3D position,
                                                                                                                                                  org.hipparchus.geometry.euclidean.threed.Rotation rotation,
                                                                                                                                                  double mass,
                                                                                                                                                  org.hipparchus.geometry.euclidean.threed.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