Class PythonAbstractConstantThrustPropulsionModel

    • Field Detail

      • pythonObject

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

      • PythonAbstractConstantThrustPropulsionModel

        public PythonAbstractConstantThrustPropulsionModel​(double thrust,
                                                           double isp,
                                                           Vector3D direction,
                                                           Control3DVectorCostType control3DVectorCostType,
                                                           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

      • pythonExtension

        public void pythonExtension​(long pythonObject)
      • pythonExtension

        public long pythonExtension()
      • pythonDecRef

        public void pythonDecRef()
      • getThrustVector

        public Vector3D getThrustVector()
        Get the thrust vector in spacecraft frame (N). Here it does not depend on current S/C state.
        Specified by:
        getThrustVector in class AbstractConstantThrustPropulsionModel
        Returns:
        thrust vector in spacecraft frame (N), will throw an exception if used on driver containing several value spans
      • getThrustVector

        public Vector3D getThrustVector​(AbsoluteDate date)
        Description copied from class: AbstractConstantThrustPropulsionModel
        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:
        date - date at which the thrust vector wants to be known, often the date parameter will not be important and can be whatever if the thrust parameter driver as only value estimated over the all orbit determination interval
        Returns:
        thrust vector in spacecraft frame (N)
      • getFlowRate

        public double getFlowRate()
        Get the flow rate (kg/s). Here it does not depend on current S/C.
        Specified by:
        getFlowRate in class AbstractConstantThrustPropulsionModel
        Returns:
        flow rate (kg/s) will throw an exception if used on driver containing several value spans
      • getFlowRate

        public double getFlowRate​(AbsoluteDate date)
        Get the flow rate (kg/s). Here it does not depend on current S/C.
        Specified by:
        getFlowRate in class AbstractConstantThrustPropulsionModel
        Parameters:
        date - date at which the thrust vector wants to be known, often the date parameter will not be important and can be whatever if the thrust parameter driver as only value estimated over the all orbit determination interval
        Returns:
        flow rate (kg/s)
      • 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)
      • 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)
      • getParametersDrivers

        public List<ParameterDriver> getParametersDrivers()
        Get the drivers for parameters.
        Returns:
        drivers for parameters