Package org.orekit.estimation.iod

Class IodGibbs

java.lang.Object

org.orekit.estimation.iod.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 Summary

Constructors

Constructor	Description
IodGibbs(double mu)	Creator.

Method Summary

Modifier and Type	Method	Description
Orbit	estimate(Frame frame, Vector3D r1, AbsoluteDate date1, Vector3D r2, AbsoluteDate date2, Vector3D r3, AbsoluteDate date3)	Give an initial orbit estimation, assuming Keplerian motion.
Orbit	estimate(Frame frame, Position p1, Position p2, Position p3)	Give an initial orbit estimation, assuming Keplerian motion.
Orbit	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 Details

IodGibbs

public IodGibbs(double mu)

Creator.

Parameters:

mu - gravitational constant

Method Details

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)