Method for designing an orbit of a spacecraft

Details Method for designing an orbit of a spacecraft Method for designing an orbit of a spacecraft

2006-07-19

2010-06-29

Collins, Timothy D (Department: 3644)

Aeronautics and astronautics

Spacecraft

Spacecraft formation, orbit, or interplanetary path

Reexamination Certificate

active

07744036

ABSTRACT:
A method is disclosed for designing an orbit of a spacecraft which allows the spacecraft to take a small-radius halo orbit near a Lagrange point while avoiding the prohibited zone where the spacecraft may be shadowed or might be prevented from making communication. The method makes it possible to have a closed orbit although being similar to a Lissajous orbit, under a restricted condition where a propulsion force magnitude applied to a spacecraft is fixed, and where it rotates at a constant angular velocity, based on the equation of motion close to a Lagrange point. The method also provide a theory for guiding/controlling the orbit of a spacecraft, that is, the embodiment of the above orbit design method.

REFERENCES:
patent: 4795113 (1989-01-01), Minovitch
patent: 5183225 (1993-02-01), Forward
patent: 6385512 (2002-05-01), Belbruno
patent: 6809818 (2004-10-01), Hillis et al.
Roberts, Craig, Sun-Earth L1 Region Halo-to-Halo and Halo-to-Lissajous Orbit Transfers, 2004, AI Solutions, pp. 1-6.
AI Solutions, Technical Paper Library, p. 4.
ESA/NASA, Schematic Diagram of SOHO's Orbit, Jan. 9, 2004, ESA, p. 1.
NASA, SOHO Orbit Schematic, p. 1.
NASA, RLP Coordinate System, p. 1.
Min Xin, et al., “Stationkeeping of an L2Libration Point Satellite with θ-D Technique”, Proceeding of the 2004 American Control Conference, Jun. 30, 2004-Jul. 2, 2004, pp. 1037-1042, XP002407945, Boston, Massachusettes, USA.
Kulkarni J. Campbell M., “Asymptomatic Stabilization of Motion about an Unstable Orbit: Application to Spacecraft Flight in Halo Orbit”, Proceeding of the 2004 American Control Conference, Jun. 30, 2004-Jul. 2, 2004, pp. 1025-1030, XP002407946, Boston, Massachusettes, USA.
Gomez G, et al., “Libration Point Orbits: A Survey from the Dynamical Point of View”, Proceedings of the International Conference on Libration Point Orbits and Applications, Jun. 10, 2002-Jun. 14, 2002, pp. 1-9 and pp. 30-37, XP002407947, Begur, Girona, Spain.
Dunham D. W., Farquhar R. W.: Libration Point Missions, 1978-2002, Proceedings of the International Conference on Libration Point Orbits and Applications, Jun. 10, 2002-Jun. 14, 2002, XP002407948, Begur, Girona, Spain.
Farquhar, R. W. et al., “Mission Design for a Halo Orbiter of the Earth”, AIAA/AAS Astrodynamics Conference, San Diego, CA, Aug. 18-20, 1976, pp. 170-177.
Farquhar, R. W., The Flight of ISEE-3/ICE: Origins, Mission History, and a Legacy, , AIAA/AAS Astrodynamics Specialists Conference, Boston, MA, Aug. 10-12, 1998, pp. 1-59.
European Search Report, EP Application No. 06117482.7, Dec. 13, 2006, 3 pages.

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