org.orekit.forces.radiation

Interface RadiationSensitive

All Known Implementing Classes:

BoxAndSolarArraySpacecraft, IsotropicRadiationClassicalConvention, IsotropicRadiationCNES95Convention, IsotropicRadiationSingleCoefficient, SphericalSpacecraft

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
double	getAbsorptionCoefficient() Get the absorption coefficient.
double	getReflectionCoefficient() Get the specular reflection coefficient.
org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure>	radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> position, org.apache.commons.math3.geometry.euclidean.threed.FieldRotation<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> rotation, org.apache.commons.math3.analysis.differentiation.DerivativeStructure mass, org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> flux) Compute the acceleration due to radiation pressure, with state derivatives.
org.apache.commons.math3.geometry.euclidean.threed.Vector3D	radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.apache.commons.math3.geometry.euclidean.threed.Vector3D position, org.apache.commons.math3.geometry.euclidean.threed.Rotation rotation, double mass, org.apache.commons.math3.geometry.euclidean.threed.Vector3D flux) Compute the acceleration due to radiation pressure.
org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure>	radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.apache.commons.math3.geometry.euclidean.threed.Vector3D position, org.apache.commons.math3.geometry.euclidean.threed.Rotation rotation, double mass, org.apache.commons.math3.geometry.euclidean.threed.Vector3D flux, String paramName) Compute the acceleration due to radiation pressure, with parameters derivatives.
void	setAbsorptionCoefficient(double value) Set the absorption coefficient.
void	setReflectionCoefficient(double value) Set the specular reflection coefficient.

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

radiationPressureAcceleration

org.apache.commons.math3.geometry.euclidean.threed.Vector3D radiationPressureAcceleration(AbsoluteDate date,
                                                                                          Frame frame,
                                                                                          org.apache.commons.math3.geometry.euclidean.threed.Vector3D position,
                                                                                          org.apache.commons.math3.geometry.euclidean.threed.Rotation rotation,
                                                                                          double mass,
                                                                                          org.apache.commons.math3.geometry.euclidean.threed.Vector3D flux)
                                                                                   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

Returns:

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

Throws:

OrekitException - if acceleration cannot be computed

radiationPressureAcceleration

org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> radiationPressureAcceleration(AbsoluteDate date,
                                                                                                                                                                      Frame frame,
                                                                                                                                                                      org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> position,
                                                                                                                                                                      org.apache.commons.math3.geometry.euclidean.threed.FieldRotation<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> rotation,
                                                                                                                                                                      org.apache.commons.math3.analysis.differentiation.DerivativeStructure mass,
                                                                                                                                                                      org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> flux)
                                                                                                                                                               throws OrekitException

Compute the acceleration due to radiation pressure, with state 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 - 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)

Throws:

OrekitException - if acceleration cannot be computed

radiationPressureAcceleration

org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> radiationPressureAcceleration(AbsoluteDate date,
                                                                                                                                                                      Frame frame,
                                                                                                                                                                      org.apache.commons.math3.geometry.euclidean.threed.Vector3D position,
                                                                                                                                                                      org.apache.commons.math3.geometry.euclidean.threed.Rotation rotation,
                                                                                                                                                                      double mass,
                                                                                                                                                                      org.apache.commons.math3.geometry.euclidean.threed.Vector3D flux,
                                                                                                                                                                      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

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

setAbsorptionCoefficient

void setAbsorptionCoefficient(double value)

Set the absorption coefficient.

Parameters:

value - absorption coefficient

getAbsorptionCoefficient

double getAbsorptionCoefficient()

Get the absorption coefficient.

Returns:

absorption coefficient

setReflectionCoefficient

void setReflectionCoefficient(double value)

Set the specular reflection coefficient.

Parameters:

value - specular reflection coefficient

getReflectionCoefficient

double getReflectionCoefficient()

Get the specular reflection coefficient.

Returns:

reflection coefficient