Constant sun angle transfer orbit sequence and method using elec

Details Constant sun angle transfer orbit sequence and method using elec Constant sun angle transfer orbit sequence and method using elec

1995-10-31

1998-02-10

Barefoot, Galen L.

Aeronautics and astronautics

Spacecraft

Spacecraft formation, orbit, or interplanetary path

B64G 110

Patent

active

057160295

ABSTRACT:
An apparatus and method for translating a spacecraft (102, 108) from an injection orbit (114) about a central body (100) to synchronous orbit (122) in a time efficient manner. The spacecraft (102, 108) includes propulsion thrusters (50) which are fired in predetermined timing sequences controlled by a controller (64) in relation to the apogee (118) and perigee (120) of the injection orbit (114) and successive transfer orbits (114). During transfer orbit, the spacecraft's inertial attitude is adjusted to track sun movement. The spacecraft is injected into a particular injection orbit that offsets moments created by tracking sun movement to maintain stable transfer orbits.

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.

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