Class OsculatingToMeanElementsConverter


  • public class OsculatingToMeanElementsConverter
    extends Object
    This class converts osculating orbital elements into mean elements.

    As this process depends on the force models used to average the orbit, a Propagator is given as input. The force models used will be those contained into the propagator. This propagator must support its initial state to be reset, and this initial state must represent some mean value. This implies that this method will not work with TLE propagators because their initial state cannot be reset, and it won't work either with Eckstein-Hechler propagator as their initial state is osculating and not mean. As of 6.0, this works mainly for DSST propagator.

    Author:
    rdicosta, Pascal Parraud
    • Constructor Detail

      • OsculatingToMeanElementsConverter

        public OsculatingToMeanElementsConverter​(SpacecraftState state,
                                                 int satelliteRevolution,
                                                 Propagator propagator,
                                                 double positionScale)
        Constructor.
        Parameters:
        state - initial orbit to convert
        satelliteRevolution - number of satellite revolutions in the averaging interval
        propagator - propagator used to compute mean orbit
        positionScale - scaling factor used for orbital parameters normalization (typically set to the expected standard deviation of the position)
    • Method Detail

      • convert

        public final SpacecraftState convert()
        Convert an osculating orbit into a mean orbit, in DSST sense.
        Returns:
        mean orbit state, in DSST sense