Class PythonAbstractConstantThrustPropulsionModel

    • Constructor Detail

      • PythonAbstractConstantThrustPropulsionModel

        public PythonAbstractConstantThrustPropulsionModel​(double thrust,
                                                           double isp,
                                                           Vector3D direction,
                                                           String name)
        Generic constructor.
        Parameters:
        thrust - initial thrust value (N)
        isp - initial isp value (s)
        direction - initial thrust direction in S/C frame
        name - name of the maneuver
    • Method Detail

      • getThrustVector

        public Vector3D getThrustVector​(double[] parameters)
        Get the thrust vector in spacecraft frame (N). Here it does not depend on current S/C state.
        Specified by:
        getThrustVector in class AbstractConstantThrustPropulsionModel
        Parameters:
        parameters - propulsion model parameters
        Returns:
        thrust vector in spacecraft frame (N)
      • getFlowRate

        public double getFlowRate​(double[] parameters)
        Get the flow rate (kg/s). Here it does not depend on current S/C state.
        Specified by:
        getFlowRate in class AbstractConstantThrustPropulsionModel
        Parameters:
        parameters - propulsion model parameters
        Returns:
        flow rate (kg/s)
      • getThrustVector

        public <T extends CalculusFieldElement<T>> FieldVector3D<T> getThrustVector​(T[] parameters)
        Get the thrust vector in spacecraft frame (N). Here it does not depend on current S/C state.
        Specified by:
        getThrustVector in class AbstractConstantThrustPropulsionModel
        Type Parameters:
        T - extends CalculusFieldElement<T>
        Parameters:
        parameters - propulsion model parameters
        Returns:
        thrust vector in spacecraft frame (N)
      • getThrustVector_T

        public <T extends CalculusFieldElement<T>> FieldVector3D<T> getThrustVector_T​(T[] parameters)
        Get the thrust vector in spacecraft frame (N). Here it does not depend on current S/C state.
        Parameters:
        parameters - propulsion model parameters
        Returns:
        thrust vector in spacecraft frame (N)
      • getFlowRate

        public <T extends CalculusFieldElement<T>> T getFlowRate​(T[] parameters)
        Get the flow rate (kg/s). Here it does not depend on current S/C state.
        Specified by:
        getFlowRate in class AbstractConstantThrustPropulsionModel
        Type Parameters:
        T - extends CalculusFieldElement<T>
        Parameters:
        parameters - propulsion model parameters
        Returns:
        flow rate (kg/s)
      • getFlowRate_T

        public <T extends CalculusFieldElement<T>> T getFlowRate_T​(T[] parameters)
        Get the flow rate (kg/s). Here it does not depend on current S/C state.
        Parameters:
        parameters - propulsion model parameters
        Returns:
        flow rate (kg/s)
      • 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().