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Design synthesis of the SEPSThis paper summarizes the most current configuration of the Solar Electric Propulsion Stage (SEPS) design resulting from the synthesis of key tradeoff analyses. The baseline SEPS is a 21-kW propulsion-power vehicle using the Shuttle/Interim Upper Stage (IUS) launch vehicle for planetary and geosynchronous missions. The trade analyses supporting the baseline configuration include ion thruster array pattern, solar array stowage concepts, and number of thrusters and power processors (PP). In addition, an integrated thermal control and structural system was optimized and designed to meet flight loads and dynamics requirements. Payload provisions, mercury propellant refueling, and design compatibility of the SEPS and Shuttle/IUS are presented.
Document ID
19750040897
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Horio, S. P.
Watkins, C. L.
Shollenberger, J. M.
(Rockwell International Corp. Space Div., Downey, Calif., United States)
Date Acquired
August 8, 2013
Publication Date
March 1, 1975
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 75-371
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Electric Propulsion Conference
Location: New Orleans, LA
Start Date: March 19, 1975
End Date: March 21, 1975
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
75A24969
Funding Number(s)
CONTRACT_GRANT: NAS8-30920
Distribution Limits
Public
Copyright
Other

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