Class PythonPropulsionModel

    • Constructor Detail

      • PythonPropulsionModel

        public PythonPropulsionModel()
    • 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
      • init

        public void init​(SpacecraftState initialState,
                         AbsoluteDate target)
        Initialization method. Called in when Maneuver.init(...) is called (from ForceModel.init(...))
        Specified by:
        init in interface PropulsionModel
        Parameters:
        initialState - initial spacecraft state (at the start of propagation).
        target - date of propagation. Not equal to initialState.getDate().
      • getAcceleration

        public Vector3D getAcceleration​(SpacecraftState s,
                                        Attitude maneuverAttitude,
                                        double[] parameters)
        Get the acceleration of the spacecraft during maneuver and in maneuver frame.
        Specified by:
        getAcceleration in interface PropulsionModel
        Parameters:
        s - current spacecraft state
        maneuverAttitude - current attitude in maneuver
        parameters - propulsion model parameters
        Returns:
        acceleration
      • getAcceleration

        public <T extends CalculusFieldElement<T>> FieldVector3D<T> getAcceleration​(FieldSpacecraftState<T> s,
                                                                                    FieldAttitude<T> maneuverAttitude,
                                                                                    T[] parameters)
        Get the acceleration of the spacecraft during maneuver and in maneuver frame.
        Specified by:
        getAcceleration in interface PropulsionModel
        Type Parameters:
        T - extends CalculusFieldElement<T>
        Parameters:
        s - current spacecraft state
        maneuverAttitude - current attitude in maneuver
        parameters - propulsion model parameters
        Returns:
        acceleration
      • getMassDerivatives

        public double getMassDerivatives​(SpacecraftState s,
                                         double[] parameters)
        Get the mass derivative (i.e. flow rate in kg/s) during maneuver.
        Specified by:
        getMassDerivatives in interface PropulsionModel
        Parameters:
        s - current spacecraft state
        parameters - propulsion model parameters
        Returns:
        mass derivative in kg/s
      • getMassDerivatives

        public <T extends CalculusFieldElement<T>> T getMassDerivatives​(FieldSpacecraftState<T> s,
                                                                        T[] parameters)
        Get the mass derivative (i.e. flow rate in kg/s) during maneuver.
        Specified by:
        getMassDerivatives in interface PropulsionModel
        Type Parameters:
        T - extends CalculusFieldElement<T>
        Parameters:
        s - current spacecraft state
        parameters - propulsion model parameters
        Returns:
        mass derivative in kg/s