Class ExtendedSemianalyticalKalmanFilter


  • public class ExtendedSemianalyticalKalmanFilter
    extends Object
    Tutorial to present the Extended Semi-analytical Kalman Filter.

    Because the DSST orbit propagator uses large step size to perform the numerical integration of the equations of motion for the mean equinoctial elements (e.g., half-day for GEO satellites), itvssical Extended Kalman Filter orbit determination. The classical Extended Kalman Filter algorithm needs to re-initialize the orbital state at each observation epoch. However, the time difference between two observations is usually much smaller than the DSST step size. In order to take advantage of the DSST theory within a recursive filter orbit determination, Orekit implements the Extended Semi-analytical Kalman Filter.

    This tutorial presents the functional validation test performed in the second reference below. It corresponds to a 5-days orbit determination of Lageos 2 satellites. Lageos' positions are used as observations during the estimation process.

    Author:
    Bryan Cazabonne
    See Also:
    "Folcik Z., Orbit Determination Using Modern Filters/Smoothers and Continuous Thrust Modeling, Master of Science Thesis, Department of Aeronautics and Astronautics, MIT, June, 2008.", "Cazabonne B., Bayard J., Journot M., and Cefola P. J., A Semi-analytical Approach for Orbit Determination based on Extended Kalman Filter, AAS Paper 21-614, AAS/AIAA Astrodynamics Specialist Conference, Big Sky, August 2021."
    • Constructor Detail

      • ExtendedSemianalyticalKalmanFilter

        public ExtendedSemianalyticalKalmanFilter()