Class PythonRadiationSensitive

    • Constructor Detail

      • PythonRadiationSensitive

        public PythonRadiationSensitive()
    • Method Detail

      • pythonExtension

        public void pythonExtension​(long pythonObject)
        Part of JCC Python interface to object
      • pythonExtension

        public long pythonExtension()
        Part of JCC Python interface to object
      • pythonDecRef

        public void pythonDecRef()
        Part of JCC Python interface to object
      • 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 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
        parameters - values of the force model parameters
        Returns:
        spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)
      • 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 interface RadiationSensitive
        Type Parameters:
        T - extends CalculusFieldElement
        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)
      • 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 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)