Interface RadiationSensitive

    • Field Detail

      • ABSORPTION_COEFFICIENT

        static final String ABSORPTION_COEFFICIENT
        Parameter name for absorption coefficient.
        See Also:
        Constant Field Values
      • REFLECTION_COEFFICIENT

        static final String REFLECTION_COEFFICIENT
        Parameter name for reflection coefficient.
        See Also:
        Constant Field Values
    • Method Detail

      • getRadiationParametersDrivers

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

        Vector3D radiationPressureAcceleration​(AbsoluteDate date,
                                               Frame frame,
                                               Vector3D position,
                                               Rotation rotation,
                                               double mass,
                                               Vector3D flux,
                                               double[] parameters)
        Compute the acceleration due to radiation pressure.
        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
        flux - radiation flux in the same inertial frame as spacecraft orbit
        parameters - values of the force model parameters
        Returns:
        spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)
      • radiationPressureAcceleration

        <T extends CalculusFieldElement<T>> FieldVector3D<T> radiationPressureAcceleration​(FieldAbsoluteDate<T> date,
                                                                                           Frame frame,
                                                                                           FieldVector3D<T> position,
                                                                                           FieldRotation<T> rotation,
                                                                                           T mass,
                                                                                           FieldVector3D<T> flux,
                                                                                           T[] parameters)
        Compute the acceleration due to radiation pressure.
        Type Parameters:
        T - extends 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
        flux - radiation flux in the same inertial frame as spacecraft orbit
        parameters - values of the force model parameters
        Returns:
        spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)