Package org.orekit.files.general

Interface EphemerisFile.EphemerisSegment<C extends TimeStampedPVCoordinates>

    • Method Detail

      • getMu

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

      • getFrame

        Frame getFrame()
        Get the reference frame for this ephemeris segment. The defining frame for getCoordinates().
        Returns:
        the reference frame for this segment. Never null.

      • getInertialFrame

        default Frame getInertialFrame()
        Get the inertial reference frame for this ephemeris segment. Defines the propagation frame for getPropagator(AttitudeProvider).

        The default implementation returns getFrame() if it is inertial. Otherwise it returns Frame.getRoot(). Implementors are encouraged to override this default implementation if a more suitable inertial frame is available.

        Returns:
        an reference frame that is inertial, i.e. Frame.isPseudoInertial() is true. May be the same as getFrame() if it is inertial.

      • getInterpolationSamples

        int getInterpolationSamples()
        Get the number of samples to use in interpolation.
        Returns:
        the number of points to use for interpolation.

      • getAvailableDerivatives

        CartesianDerivativesFilter getAvailableDerivatives()
        Get which derivatives of position are available in this ephemeris segment.

        While getCoordinates() always returns position, velocity, and acceleration the return value from this method indicates which of those are in the ephemeris file and are actually valid.

        Returns:
        a value indicating if the file contains velocity and/or acceleration data.

      • getCoordinates

        List<C> getCoordinates()
        Get the coordinates for this ephemeris segment in getFrame().
        Returns:
        a list of state vectors in chronological order. The coordinates are not necessarily evenly spaced in time. The value of getAvailableDerivatives() indicates if the velocity or accelerations were specified in the file. Any position, velocity, or acceleration coordinates that are not specified in the ephemeris file are zero in the returned values.

      • getStart

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

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

        Returns:
        ephemeris segment start date.

      • getStop

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

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

        Returns:
        ephemeris segment end date.

      • getPropagator

        default BoundedPropagator getPropagator()
        View this ephemeris segment as a propagator.

        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 getFrame() return normally. Additionally, getMu() must return a valid value. 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

        Each call to this method creates a new propagator.

        Returns:
        a propagator for this ephemeris segment.

      • getPropagator

        default BoundedPropagator getPropagator​(AttitudeProvider attitudeProvider)
        View this ephemeris segment as a propagator.

        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 getFrame() return normally. Additionally, getMu() must return a valid value. 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 this ephemeris segment.
        Since:
        12.0