Class SBASPropagator

    • Method Detail

      • propagateInEcef

        public PVCoordinates propagateInEcef​(AbsoluteDate date)
        Gets the PVCoordinates of the GNSS SV in ECEF frame.

        The algorithm uses automatic differentiation to compute velocity and acceleration.

        Parameters:
        date - the computation date
        Returns:
        the GNSS SV PVCoordinates in ECEF frame
      • getMU

        public double getMU()
        Get the Earth gravity coefficient used for SBAS propagation.
        Returns:
        the Earth gravity coefficient.
      • getECI

        public Frame getECI()
        Gets the Earth Centered Inertial frame used to propagate the orbit.
        Returns:
        the ECI frame
      • getECEF

        public Frame getECEF()
        Gets the Earth Centered Earth Fixed frame used to propagate GNSS orbits.
        Returns:
        the ECEF frame
      • getSBASOrbitalElements

        public SBASOrbitalElements getSBASOrbitalElements()
        Get the underlying SBAS orbital elements.
        Returns:
        the underlying SBAS orbital elements
      • resetIntermediateState

        protected void resetIntermediateState​(SpacecraftState state,
                                              boolean forward)
        Reset an intermediate state.
        Specified by:
        resetIntermediateState in class AbstractAnalyticalPropagator
        Parameters:
        state - new intermediate state to consider
        forward - if true, the intermediate state is valid for propagations after itself