Interface DragSensitive

    • Field Detail

      • DRAG_COEFFICIENT

        static final String DRAG_COEFFICIENT
        Parameter name for drag coefficient enabling Jacobian processing.
        See Also:
        Constant Field Values
      • LIFT_RATIO

        static final String LIFT_RATIO
        Parameter name for lift ration enabling Jacobian processing.

        The lift ratio is the proportion of atmosphere modecules that will experience specular reflection when hitting spacecraft instead of experiencing diffuse reflection. The ratio is between 0 and 1, 0 meaning there are no specular reflection, only diffuse reflection, and hence no lift effect.

        Since:
        9.0
        See Also:
        Constant Field Values
    • Method Detail

      • getDragParametersDrivers

        List<ParameterDriver> getDragParametersDrivers()
        Get the drivers for supported parameters.
        Returns:
        parameters drivers
        Since:
        8.0
      • dragAcceleration

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

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

        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

        <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.

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

        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