Optimal transfer orbit trajectory using electric propulsion

Details Optimal transfer orbit trajectory using electric propulsion Optimal transfer orbit trajectory using electric propulsion

1994-03-25

1997-01-21

Barefoot, Galen L.

Aeronautics and astronautics

Spacecraft

Spacecraft formation, orbit, or interplanetary path

B64G 110

Patent

active

055953603

ABSTRACT:
An apparatus and method for translating a spacecraft (10) from an injection orbit (16) about a central body (10) to geosynchronous orbit (18) in a time efficient manner. The spacecraft (10) includes propulsion thrusters (50) which are fired in predetermined timing sequences controlled by a controller (64) in relation to the apogee (66) and perigee (72) of the injection orbit (16) and successive transfer orbits (74, 76).

REFERENCES:
patent: 4943014 (1990-07-01), Harwood et al.
Porte et al. "Benefits of Electric Propulsion For Orbit Injection Of Communication Spacecraft", 14th AIAA International Communication Satellite Systems Conference and Exhibit, 26 Mar. 1992, pp. 1-9.
Meserole, J., "Launch Costs To GEO Using Solar Powered Orbit Transfer Vehicles", American Institute of Aeronautics and Astronautic (AIAA) Paper 93-2219, AIAA/SAE/ASME/ASEE 29th Joint Propulsion Conference and Exhibit, Jun. 28-30, 1993.
Free, B. "High Altitude Orbit Raising With On-Board Electric Power", International Electric Propulsion Conference Paper 93-205, American Institute Of Aeronautics and Astronautics AIAA/AIDA/DGLA/JSASS 23rd International Electric Propulsion Conference, Sep. 13-16, 1993.
Parkhash, "Electric Propulsion for Space Missions" Electrical India vol. 19, No. 7, pp. 5-18., Apr. 1979.
Davison, "orbit Expansion by Microthrust" Royal Aircraft Est. Tech Report 67249 Sep. 1967.

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