Class IodGooding


  • public class IodGooding
    extends Object
    Gooding angles only initial orbit determination, assuming Keplerian motion. An orbit is determined from three angular observations. Reference: Gooding, R.H., A New Procedure for Orbit Determination Based on Three Lines of Sight (Angles only), Technical Report 93004, April 1993
    Since:
    8.0
    Author:
    Joris Olympio
    • Constructor Detail

      • IodGooding

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

      • getRange1

        public double getRange1()
        Get the range for observation (1).
        Returns:
        the range for observation (1).
      • getRange2

        public double getRange2()
        Get the range for observation (2).
        Returns:
        the range for observation (2).
      • getRange3

        public double getRange3()
        Get the range for observation (3).
        Returns:
        the range for observation (3).
      • estimate

        public KeplerianOrbit estimate​(Frame frame,
                                       AngularRaDec raDec1,
                                       AngularRaDec raDec2,
                                       AngularRaDec raDec3,
                                       double rho1init,
                                       double rho3init,
                                       int nRev,
                                       boolean direction)
        Orbit got from three angular observations.
        Parameters:
        frame - inertial frame for observer coordinates and orbit estimate
        raDec1 - first angular observation
        raDec2 - second angular observation
        raDec3 - third angular observation
        rho1init - initial guess of the range problem. range 1, in meters
        rho3init - initial guess of the range problem. range 3, in meters
        nRev - number of complete revolutions between observation 1 and 3
        direction - true if posigrade (short way)
        Returns:
        an estimate of the Keplerian orbit at the central date (i.e., date of the second angular observation)
        Since:
        11.0
      • estimate

        public KeplerianOrbit estimate​(Frame frame,
                                       AngularRaDec raDec1,
                                       AngularRaDec raDec2,
                                       AngularRaDec raDec3,
                                       double rho1init,
                                       double rho3init)
        Orbit got from three angular observations.
        Parameters:
        frame - inertial frame for observer coordinates and orbit estimate
        raDec1 - first angular observation
        raDec2 - second angular observation
        raDec3 - third angular observation
        rho1init - initial guess of the range problem. range 1, in meters
        rho3init - initial guess of the range problem. range 3, in meters
        Returns:
        an estimate of the Keplerian orbit at the central date (i.e., date of the second angular observation)
        Since:
        11.0
      • estimate

        public KeplerianOrbit estimate​(Frame frame,
                                       Vector3D O1,
                                       Vector3D O2,
                                       Vector3D O3,
                                       Vector3D lineOfSight1,
                                       AbsoluteDate dateObs1,
                                       Vector3D lineOfSight2,
                                       AbsoluteDate dateObs2,
                                       Vector3D lineOfSight3,
                                       AbsoluteDate dateObs3,
                                       double rho1init,
                                       double rho3init,
                                       int nRev,
                                       boolean direction)
        Orbit got from Observed Three Lines of Sight (angles only).
        Parameters:
        frame - inertial frame for observer coordinates and orbit estimate
        O1 - Observer position 1
        O2 - Observer position 2
        O3 - Observer position 3
        lineOfSight1 - line of sight 1
        dateObs1 - date of observation 1
        lineOfSight2 - line of sight 2
        dateObs2 - date of observation 2
        lineOfSight3 - line of sight 3
        dateObs3 - date of observation 3
        rho1init - initial guess of the range problem. range 1, in meters
        rho3init - initial guess of the range problem. range 3, in meters
        nRev - number of complete revolutions between observation1 and 3
        direction - true if posigrade (short way)
        Returns:
        an estimate of the Keplerian orbit at the central date (i.e., date of the second angular observation)
      • estimate

        public KeplerianOrbit estimate​(Frame frame,
                                       Vector3D O1,
                                       Vector3D O2,
                                       Vector3D O3,
                                       Vector3D lineOfSight1,
                                       AbsoluteDate dateObs1,
                                       Vector3D lineOfSight2,
                                       AbsoluteDate dateObs2,
                                       Vector3D lineOfSight3,
                                       AbsoluteDate dateObs3,
                                       double rho1init,
                                       double rho3init)
        Orbit got from Observed Three Lines of Sight (angles only). assuming there was less than an half revolution between start and final date
        Parameters:
        frame - inertial frame for observer coordinates and orbit estimate
        O1 - Observer position 1
        O2 - Observer position 2
        O3 - Observer position 3
        lineOfSight1 - line of sight 1
        dateObs1 - date of observation 1
        lineOfSight2 - line of sight 2
        dateObs2 - date of observation 1
        lineOfSight3 - line of sight 3
        dateObs3 - date of observation 1
        rho1init - initial guess of the range problem. range 1, in meters
        rho3init - initial guess of the range problem. range 3, in meters
        Returns:
        an estimate of the Keplerian orbit at the central date (i.e., date of the second angular observation)
      • lineOfSight

        public static Vector3D lineOfSight​(double alpha,
                                           double delta)
        Calculates the line of sight vector.
        Parameters:
        alpha - right ascension angle, in radians
        delta - declination angle, in radians
        Returns:
        the line of sight vector
        Since:
        11.0
      • lineOfSight

        public static Vector3D lineOfSight​(AngularRaDec raDec)
        Calculate the line of sight vector from an AngularRaDec measurement.
        Parameters:
        raDec - measurement
        Returns:
        the line of sight vector
        Since:
        11.0