Package org.orekit.files.general

Interface EphemerisFile.SatelliteEphemeris<C extends TimeStampedPVCoordinates,​S extends EphemerisFile.EphemerisSegment<C>>

    • Method Detail

      • getId

        String getId()
        Get the satellite ID. The satellite ID is unique only within the same ephemeris file.
        Returns:
        the satellite's ID, never null.

      • getMu

        double getMu()
        Get the standard gravitational parameter for the satellite.
        Returns:
        the gravitational parameter used in getPropagator(AttitudeProvider), in m³/s².

      • getSegments

        List<S> getSegments()
        Get the segments of the ephemeris.

        Ephemeris segments are typically used to split an ephemeris around discontinuous events, such as maneuvers.

        Returns:
        the segments contained in the ephemeris file for this satellite.

      • getStart

        AbsoluteDate getStart()
        Get the start date of the ephemeris.

        The date returned by this method is equivalent to getPropagator().getMinDate().

        Returns:
        ephemeris start date.

      • getStop

        AbsoluteDate getStop()
        Get the end date of the ephemeris.

        The date returned by this method is equivalent to getPropagator().getMaxDate().

        Returns:
        ephemeris end date.

      • getPropagator

        default BoundedPropagator getPropagator()
        View this ephemeris as a propagator, combining data from all segments.

        In order to view the ephemeris for this satellite as a Propagator several conditions must be met. An Orekit Frame must be constructable from the frame specification in the ephemeris file. This condition is met when EphemerisFile.EphemerisSegment.getFrame() return normally for all segments. If there are multiple segments they must be adjacent such that there are no duplicates or gaps in the ephemeris. The definition of adjacent depends on the ephemeris format as some formats define usable start and stop times that are different from the ephemeris data start and stop times. If these conditions are not met an OrekitException may be thrown by this method or by one of the methods of the returned Propagator.

        The attitude provider used is a FrameAlignedProvider aligned with the inertial frame from the first segment.

        Each call to this method creates a new propagator.

        Returns:
        a propagator for all the data in this ephemeris file.

      • getPropagator

        default BoundedPropagator getPropagator​(AttitudeProvider attitudeProvider)
        View this ephemeris as a propagator, combining data from all segments.

        In order to view the ephemeris for this satellite as a Propagator several conditions must be met. An Orekit Frame must be constructable from the frame specification in the ephemeris file. This condition is met when EphemerisFile.EphemerisSegment.getFrame() return normally for all segments. If there are multiple segments they must be adjacent such that there are no duplicates or gaps in the ephemeris. The definition of adjacent depends on the ephemeris format as some formats define usable start and stop times that are different from the ephemeris data start and stop times. If these conditions are not met an OrekitException may be thrown by this method or by one of the methods of the returned Propagator.

        Each call to this method creates a new propagator.

        Parameters:
        attitudeProvider - provider for attitude computation
        Returns:
        a propagator for all the data in this ephemeris file.
        Since:
        12.0