Class PythonAbstractGaussianContribution

    • Constructor Detail

      • PythonAbstractGaussianContribution

        public PythonAbstractGaussianContribution​(String coefficientsKeyPrefix,
                                                  double threshold,
                                                  ForceModel contribution,
                                                  double mu)
        Build a new instance.
        Parameters:
        coefficientsKeyPrefix - prefix for coefficients keys
        threshold - tolerance for the choice of the Gauss quadrature order
        contribution - the ForceModel to be numerically averaged
    • Method Detail

      • pythonExtension

        public void pythonExtension​(long pythonObject)
        Part of JCC Python interface to object
      • pythonExtension

        public long pythonExtension()
        Part of JCC Python interface to object
      • pythonDecRef

        public void pythonDecRef()
        Part of JCC Python interface to object
      • getLLimits

        public double[] getLLimits​(SpacecraftState state,
                                   AuxiliaryElements auxiliaryElements)
        Compute the limits in L, the true longitude, for integration.
        Specified by:
        getLLimits in class AbstractGaussianContribution
        Parameters:
        state - current state information: date, kinematics, attitude
        auxiliaryElements - auxiliary elements related to the current orbit
        Returns:
        the integration limits in L
      • getLLimits

        public <T extends CalculusFieldElement<T>> T[] getLLimits​(FieldSpacecraftState<T> state,
                                                                  FieldAuxiliaryElements<T> auxiliaryElements)
        Compute the limits in L, the true longitude, for integration.
        Specified by:
        getLLimits in class AbstractGaussianContribution
        Type Parameters:
        T - type of the elements
        Parameters:
        state - current state information: date, kinematics, attitude
        auxiliaryElements - auxiliary elements related to the current orbit
        Returns:
        the integration limits in L