Package org.orekit.estimation.iod
Class IodGibbs
- java.lang.Object
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- org.orekit.estimation.iod.IodGibbs
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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
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Constructor Summary
Constructors Constructor Description IodGibbs(double mu)
Creator.
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Method Summary
All Methods Instance Methods Concrete Methods 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.
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Method Detail
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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 framep1
- First position measurementp2
- Second position measurementp3
- Third position measurement- Returns:
- an initial orbit estimation at the central date (i.e., date of the second position measurement)
- Since:
- 11.0
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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 framepv1
- PV measure 1 taken in framepv2
- PV measure 2 taken in framepv3
- PV measure 3 taken in frame- Returns:
- an initial orbit estimation at the central date (i.e., date of the second PV measurement)
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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 framer1
- position 1 measured in framedate1
- date of measure 1r2
- position 2 measured in framedate2
- date of measure 2r3
- position 3 measured in framedate3
- date of measure 3- Returns:
- an initial orbit estimation at the central date (i.e., date of the second position measurement)
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