Class IodGibbs


  • public class IodGibbs
    extends Object
    Gibbs position-based Initial Orbit Determination (IOD) algorithm.

    An orbit is determined from three position vectors. This method requires the vectors to be coplanar. Orekit uses a default coplanar threshold of 5°. Reference: Vallado, D., Fundamentals of Astrodynamics and Applications

    Since:
    8.0
    Author:
    Joris Olympio
    • Constructor Detail

      • IodGibbs

        public IodGibbs​(double mu)
        Creator.
        Parameters:
        mu - gravitational constant
    • Method Detail

      • estimate

        public Orbit estimate​(Frame frame,
                              Position p1,
                              Position p2,
                              Position p3)
        Give an initial orbit estimation, assuming Keplerian motion. All observations should be from the same location.
        Parameters:
        frame - measurements frame
        p1 - First position measurement
        p2 - Second position measurement
        p3 - Third position measurement
        Returns:
        an initial orbit estimation at the central date (i.e., date of the second position measurement)
        Since:
        11.0
      • estimate

        public Orbit estimate​(Frame frame,
                              PV pv1,
                              PV pv2,
                              PV pv3)
        Give an initial orbit estimation, assuming Keplerian motion. All observations should be from the same location.
        Parameters:
        frame - measure frame
        pv1 - PV measure 1 taken in frame
        pv2 - PV measure 2 taken in frame
        pv3 - PV measure 3 taken in frame
        Returns:
        an initial orbit estimation at the central date (i.e., date of the second PV measurement)
      • estimate

        public Orbit estimate​(Frame frame,
                              Vector3D r1,
                              AbsoluteDate date1,
                              Vector3D r2,
                              AbsoluteDate date2,
                              Vector3D r3,
                              AbsoluteDate date3)
        Give an initial orbit estimation, assuming Keplerian motion. All observations should be from the same location.
        Parameters:
        frame - measure frame
        r1 - position 1 measured in frame
        date1 - date of measure 1
        r2 - position 2 measured in frame
        date2 - date of measure 2
        r3 - position 3 measured in frame
        date3 - date of measure 3
        Returns:
        an initial orbit estimation at the central date (i.e., date of the second position measurement)