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Advanced Electric Propulsion for RLV Launched Geosynchronous SpacecraftSolar Electric Propulsion (SEP) when used for station keeping and final orbit insertion has been shown to increase a geostationary satellite's payload when launched by existing expendable launch vehicles. In the case of reusable launch vehicles or expendable launch vehicles where an upper stage is an expensive option, this methodology can be modified by using the existing on-board apogee chemical system to perform a perigee burn and then letting the electric propulsion system complete the transfer to geostationary orbit. The elimination of upper stages using on-board chemical and electric propulsion systems was thus examined for GEO spacecraft. Launch vehicle step-down from an Atlas IIAR to a Delta 7920 (no upper stage) was achieved using expanded on-board chemical tanks, 40 kW payload power for electric propulsion, and a 60 day elliptical to GEO SEP orbit insertion. Optimal combined chemical and electric trajectories were found using SEPSPOT. While Hall and ion thrusters provided launch vehicle step-down and even more payload for longer insertion times, NH3 arcjets had insufficient performance to allow launch vehicle step-down. Degradation levels were only 5% to 7% for launch step-down cases using advanced solar arrays. Results were parameterized to allow comparisons for future reusable launch vehicles. Results showed that for an 8 W/kg initial power/launch mass power density spacecraft, 50% to 100% more payload can be launched using this method.
Document ID
20000017931
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Oleson, Steven (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
December 1, 1999
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
IEPC-99-185
NAS 1.15:209646
NASA/TM-1999-209646
E-11994
Meeting Information
Meeting: 26th International Electric Propulsion Conference
Location: Kitakyushu
Country: Japan
Start Date: October 17, 1999
End Date: October 21, 1999
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
PROJECT: RTOP 632-1B-1C
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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