Interface DragSensitive

    • Field Detail

      • GLOBAL_DRAG_FACTOR

        static final String GLOBAL_DRAG_FACTOR
        Parameter name for global multiplicative factor.
        Since:
        12.0
        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

      • dependsOnAttitudeRate

        default boolean dependsOnAttitudeRate()
        Check if model depends on attitude's rotation rate or acceleration at a given, fixed date. If false, it essentially means that at most the attitude's rotation is used when computing the acceleration vector. The default implementation returns false as common models for orbital mechanics do not.
        Returns:
        true if force model depends on attitude derivatives
        Since:
        12.1
      • getDragParametersDrivers

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

        Vector3D dragAcceleration​(SpacecraftState state,
                                  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:
        state - current state
        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:
        12.0
      • dragAcceleration

        <T extends CalculusFieldElement<T>> FieldVector3D<T> dragAcceleration​(FieldSpacecraftState<T> state,
                                                                              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:
        state - current state
        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:
        12.0