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Self-powered electric propulsion of satellite power systemsElectric propulsion using argon ion bombardment thrusters is described as a means of transferring solar power satellites from low earth orbit (LEO) to geosynchronous equatorial orbit (GEO). A portion of the satellite GaAs solar array is constructed in LEO and provides power for ascent propulsion; the remainder of the array is constructed in GEO. The electric propulsion system is returned to LEO by detaching a section of the solar array. Alternatively, an autonomous electric propulsion vehicle is assembled in LEO and transports power satellite materials to a GEO construction site. Maximum thrust per thruster and minimum argon consumption are achieved at specific impulse (Isp) 13,000 s. The thrust/power relationship leads to minimum transportation vehicle mass, including the solar array, at Isp 9,000 s. Thruster screen, accel, and discharge supplies are obtained directly from the solar array.
Document ID
19780048856
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Weddell, J. B.
(Rockwell International Corp. Downey, CA, United States)
Mcrae, W. V.
(Rockwell International Corp. Downey, CA, United States)
Cerri, S. T.
(Rockwell International Corp. Space Div., Downey, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
April 1, 1978
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 78-694
Meeting Information
Meeting: International Electric Propulsion Conference
Location: San Diego, CA
Country: US
Start Date: April 25, 1978
End Date: April 27, 1978
Sponsors: Deutsche Gesellschaft fuer Luft- und Raumfahrt, American Institute of Aeronautics and Astronautics
Accession Number
78A32765
Funding Number(s)
CONTRACT_GRANT: NAS8-42375
Distribution Limits
Public
Copyright
Other

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