Package org.orekit.estimation.iod

Class IodGibbs

java.lang.Object

org.orekit.estimation.iod.IodGibbs

public class IodGibbs
extends Object

Gibbs initial orbit determination. An orbit is determined from three position vectors. Reference: Vallado, D., Fundamentals of Astrodynamics and Applications

Since:

8.0

Author:

Joris Olympio

Constructor Summary

Constructors

Constructor	Description
IodGibbs(double mu)	Creator.

Method Summary

Modifier and Type	Method	Description
KeplerianOrbit	estimate(Frame frame, Vector3D r1, AbsoluteDate date1, Vector3D r2, AbsoluteDate date2, Vector3D r3, AbsoluteDate date3)	Give an initial orbit estimation, assuming Keplerian motion.
KeplerianOrbit	estimate(Frame frame, PV pv1, PV pv2, PV pv3)	Give an initial orbit estimation, assuming Keplerian motion.

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Constructor Detail

IodGibbs

public IodGibbs(double mu)

Creator.

Parameters:

mu - gravitational constant

Method Detail

estimate

public KeplerianOrbit 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

estimate

public KeplerianOrbit 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