Class IsotropicRadiationClassicalConvention

    • Constructor Detail

      • IsotropicRadiationClassicalConvention

        public IsotropicRadiationClassicalConvention​(double crossSection,
                                                     double ca,
                                                     double cs)
        Simple constructor.
        Parameters:
        crossSection - Surface (m²)
        ca - absorption coefficient Ca between 0.0 an 1.0
        cs - specular reflection coefficient Cs between 0.0 an 1.0
    • Method Detail

      • radiationPressureAcceleration

        public Vector3D radiationPressureAcceleration​(AbsoluteDate date,
                                                      Frame frame,
                                                      Vector3D position,
                                                      Rotation rotation,
                                                      double mass,
                                                      Vector3D flux,
                                                      double[] parameters)
        Compute the acceleration due to radiation pressure.
        Specified by:
        radiationPressureAcceleration in interface RadiationSensitive
        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

        public <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.
        Specified by:
        radiationPressureAcceleration in interface RadiationSensitive
        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)