Class IsotropicDrag

    • Constructor Detail

      • IsotropicDrag

        public IsotropicDrag​(double crossSection,
                             double dragCoeff)
        Constructor with drag coefficient min/max set to ±∞.
        Parameters:
        crossSection - Surface (m²)
        dragCoeff - drag coefficient
      • IsotropicDrag

        public IsotropicDrag​(double crossSection,
                             double dragCoeff,
                             double dragCoeffMin,
                             double dragCoeffMax)
        Constructor with drag coefficient min/max set by user.
        Parameters:
        crossSection - Surface (m²)
        dragCoeff - drag coefficient
        dragCoeffMin - Minimum value of drag coefficient
        dragCoeffMax - Maximum value of drag coefficient
    • Method Detail

      • dragAcceleration

        public 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.

        Specified by:
        dragAcceleration in interface DragSensitive
        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)
      • dragAcceleration

        public <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.

        Specified by:
        dragAcceleration in interface DragSensitive
        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)