Class PythonRadiationSensitive

    • Field Detail

      • pythonObject

        protected long pythonObject
        Part of JCC Python interface to object
    • Constructor Detail

      • PythonRadiationSensitive

        public PythonRadiationSensitive()
    • Method Detail

      • pythonExtension

        public void pythonExtension​(long pythonObject)
      • pythonExtension

        public long pythonExtension()
      • pythonDecRef

        public void pythonDecRef()
      • radiationPressureAcceleration

        public Vector3D radiationPressureAcceleration​(SpacecraftState state,
                                                      Vector3D flux,
                                                      double[] parameters)
        Compute the acceleration due to radiation pressure.
        Specified by:
        radiationPressureAcceleration in interface RadiationSensitive
        Parameters:
        state - current state
        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​(FieldSpacecraftState<T> state,
                                                                                                  FieldVector3D<T> flux,
                                                                                                  T[] parameters)
        Compute the acceleration due to radiation pressure.
        Specified by:
        radiationPressureAcceleration in interface RadiationSensitive
        Type Parameters:
        T - extends CalculusFieldElement
        Parameters:
        state - current state
        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)