Package org.orekit.estimation.iod

Class IodLaplace

java.lang.Object
org.orekit.estimation.iod.IodLaplace
public class IodLaplace extends Object
Laplace angles-only Initial Orbit Determination (IOD) algorithm, assuming Keplerian motion.

Laplace algorithm is one of the first method to determine orbits. An orbit is determined from three lines of sight w.r.t. their respective observers inertial positions vectors. For Laplace method, the observer is identical for all observations. Reference: Bate, R., Mueller, D. D., & White, J. E. (1971). Fundamentals of astrodynamics. New York: Dover Publications.

Since:
10.1
Author:
Shiva Iyer

  • Constructor Details

    • IodLaplace

      public IodLaplace(double mu)
      Constructor.
      Parameters:
      mu - gravitational constant

  • Method Details

    • estimate

      public Orbit estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3)
      Estimate the orbit from three angular observations at the same location.
      Parameters:
      outputFrame - Observer coordinates at time of raDec2
      azEl1 - first angular observation
      azEl2 - second angular observation
      azEl3 - third angular observation
      Returns:
      estimate of the orbit at the central date or null if no estimate is possible with the given data
      Since:
      12.0

    • estimate

      public Orbit estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3)
      Estimate the orbit from three angular observations at the same location.
      Parameters:
      outputFrame - Observer coordinates at time of raDec2
      raDec1 - first angular observation
      raDec2 - second angular observation
      raDec3 - third angular observation
      Returns:
      estimate of the orbit at the central date or null if no estimate is possible with the given data
      Since:
      11.0

    • estimate

      public Orbit estimate(Frame outputFrame, PVCoordinates obsPva, AbsoluteDate obsDate1, Vector3D los1, AbsoluteDate obsDate2, Vector3D los2, AbsoluteDate obsDate3, Vector3D los3)
      Estimate orbit from three line of sight angles at the same location.
      Parameters:
      outputFrame - inertial frame for observer coordinates and orbit estimate
      obsPva - Observer coordinates at time obsDate2
      obsDate1 - date of observation 1
      los1 - line of sight unit vector 1
      obsDate2 - date of observation 2
      los2 - line of sight unit vector 2
      obsDate3 - date of observation 3
      los3 - line of sight unit vector 3
      Returns:
      estimate of the orbit at the central date obsDate2 or null if no estimate is possible with the given data