Class IntelsatElevenElementsPropagator

  • All Implemented Interfaces:
    Propagator, PVCoordinatesProvider

    public class IntelsatElevenElementsPropagator
    extends AbstractAnalyticalPropagator
    This class provides elements to propagate Intelsat's 11 elements.

    Intelsat's 11 elements propagation is defined in ITU-R S.1525 standard.

    Since:
    12.1
    Author:
    Bryan Cazabonne
    • Constructor Detail

      • IntelsatElevenElementsPropagator

        public IntelsatElevenElementsPropagator​(IntelsatElevenElements elements,
                                                Frame inertialFrame,
                                                Frame ecefFrame)
        Constructor.

        The attitude provider is set by default to be aligned with the inertial frame.
        The mass is set by default to the DEFAULT_MASS.

        Parameters:
        elements - Intelsat's 11 elements
        inertialFrame - inertial frame for the output orbit
        ecefFrame - ECEF frame related to the Intelsat's 11 elements
      • IntelsatElevenElementsPropagator

        public IntelsatElevenElementsPropagator​(IntelsatElevenElements elements,
                                                Frame inertialFrame,
                                                Frame ecefFrame,
                                                AttitudeProvider attitudeProvider,
                                                double mass)
        Constructor.
        Parameters:
        elements - Intelsat's 11 elements
        inertialFrame - inertial frame for the output orbit
        ecefFrame - ECEF frame related to the Intelsat's 11 elements
        attitudeProvider - attitude provider
        mass - spacecraft mass
    • Method Detail

      • propagateInEcef

        public PVCoordinates propagateInEcef​(AbsoluteDate date)
        Converts the Intelsat's 11 elements into Position/Velocity coordinates in ECEF.
        Parameters:
        date - computation epoch
        Returns:
        Position/Velocity coordinates in ECEF
      • 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
      • getEastLongitudeDegrees

        public UnivariateDerivative2 getEastLongitudeDegrees()
        Get the computed satellite's east longitude.
        Returns:
        the satellite's east longitude in degrees
      • getGeocentricLatitudeDegrees

        public UnivariateDerivative2 getGeocentricLatitudeDegrees()
        Get the computed satellite's geocentric latitude.
        Returns:
        the satellite's geocentric latitude in degrees
      • getOrbitRadius

        public UnivariateDerivative2 getOrbitRadius()
        Get the computed satellite's orbit.
        Returns:
        satellite's orbit radius in meters
      • getIntelsatElevenElements

        public IntelsatElevenElements getIntelsatElevenElements()
        Get the Intelsat's 11 elements used by the propagator.
        Returns:
        the Intelsat's 11 elements used by the propagator