Class PythonDragSensitive

    • Constructor Detail

      • PythonDragSensitive

        public PythonDragSensitive()
    • 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
      • dragAcceleration

        public Vector3D dragAcceleration​(AbsoluteDate date,
                                         Frame frame,
                                         Vector3D position,
                                         Rotation rotation,
                                         double mass,
                                         double density,
                                         Vector3D relativeVelocity,
                                         double[] parameters)
        Compute the acceleration due to drag. Extension point for Python.

        The computation includes all spacecraft specific characteristics like shape, area and coefficients.

        Specified by:
        dragAcceleration in interface DragSensitive
        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
        density - atmospheric density at spacecraft position
        relativeVelocity - relative velocity of atmosphere with respect to spacecraft, in the same inertial frame as spacecraft orbit (m/s)
        parameters - values of the force model parameters
        Returns:
        spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)
      • dragAcceleration

        public <T extends CalculusFieldElement<T>> FieldVector3D<T> dragAcceleration​(FieldAbsoluteDate<T> date,
                                                                                     Frame frame,
                                                                                     FieldVector3D<T> position,
                                                                                     FieldRotation<T> rotation,
                                                                                     T mass,
                                                                                     T density,
                                                                                     FieldVector3D<T> relativeVelocity,
                                                                                     T[] parameters)
        Compute the acceleration due to drag. Connects to dragAcceleration_FFFFTTFT for Python extension.

        The computation includes all spacecraft specific characteristics like shape, area and coefficients.

        Specified by:
        dragAcceleration in interface DragSensitive
        Type Parameters:
        T - instance of a 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
        density - atmospheric density at spacecraft position
        relativeVelocity - relative velocity of atmosphere with respect to spacecraft, in the same inertial frame as spacecraft orbit (m/s)
        parameters - values of the force model parameters
        Returns:
        spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)
        Since:
        9.0