Package org.orekit.forces.radiation
Class PythonRadiationSensitive
- java.lang.Object
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- org.orekit.forces.radiation.PythonRadiationSensitive
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- All Implemented Interfaces:
RadiationSensitive
public class PythonRadiationSensitive extends Object implements RadiationSensitive
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Field Summary
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Fields inherited from interface org.orekit.forces.radiation.RadiationSensitive
ABSORPTION_COEFFICIENT, REFLECTION_COEFFICIENT
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Constructor Summary
Constructors Constructor Description PythonRadiationSensitive()
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description void
finalize()
Part of JCC Python interface to objectList<ParameterDriver>
getRadiationParametersDrivers()
Get the drivers for supported parameters.void
pythonDecRef()
Part of JCC Python interface to objectlong
pythonExtension()
Part of JCC Python interface to objectvoid
pythonExtension(long pythonObject)
Part of JCC Python interface to objectVector3D
radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, double[] parameters)
Compute the acceleration due to radiation pressure.<T extends CalculusFieldElement<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.<T extends CalculusFieldElement<T>>
FieldVector3D<T>radiationPressureAcceleration_FFFFTFT(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.
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Method Detail
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pythonExtension
public void pythonExtension(long pythonObject)
Part of JCC Python interface to object
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pythonExtension
public long pythonExtension()
Part of JCC Python interface to object
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finalize
public void finalize() throws Throwable
Part of JCC Python interface to object
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pythonDecRef
public void pythonDecRef()
Part of JCC Python interface to object
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getRadiationParametersDrivers
public List<ParameterDriver> getRadiationParametersDrivers()
Get the drivers for supported parameters.- Specified by:
getRadiationParametersDrivers
in interfaceRadiationSensitive
- Returns:
- parameters drivers
- Since:
- 8.0
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radiationPressureAcceleration
public Vector3D radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, double[] parameters)
Compute the acceleration due to radiation pressure.- Specified by:
radiationPressureAcceleration
in interfaceRadiationSensitive
- Parameters:
date
- current dateframe
- inertial reference frame for state (both orbit and attitude)position
- position of spacecraft in reference framerotation
- orientation (attitude) of the spacecraft with respect to reference framemass
- current massflux
- radiation flux in the same inertial frame as spacecraft orbitparameters
- values of the force model parameters- Returns:
- spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)
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radiationPressureAcceleration
public <T extends CalculusFieldElement<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.- Specified by:
radiationPressureAcceleration
in interfaceRadiationSensitive
- Type Parameters:
T
- extends CalculusFieldElement- Parameters:
date
- current dateframe
- inertial reference frame for state (both orbit and attitude)position
- position of spacecraft in reference framerotation
- orientation (attitude) of the spacecraft with respect to reference framemass
- current massflux
- radiation flux in the same inertial frame as spacecraft orbitparameters
- values of the force model parameters- Returns:
- spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)
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radiationPressureAcceleration_FFFFTFT
public <T extends CalculusFieldElement<T>> FieldVector3D<T> radiationPressureAcceleration_FFFFTFT(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.- Parameters:
date
- current dateframe
- inertial reference frame for state (both orbit and attitude)position
- position of spacecraft in reference framerotation
- orientation (attitude) of the spacecraft with respect to reference framemass
- current massflux
- radiation flux in the same inertial frame as spacecraft orbitparameters
- values of the force model parameters- Returns:
- spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)
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