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Primary propulsion of electrothermal, ion, and chemical systems for space-based radar orbit transferAn orbit transfer mission concept has been studied for a Space-Based Radar (SBR) where 40 kW required for radar operation is assumed available for orbit transfer propulsion. Arcjet, pulsed electrothermal (PET), ion, and storable chemical systems are considered for the primary propulsion. Transferring two SBR per shuttle flight to 1112 km/60 deg using eiectrical propulsion systems offers an increased payload at the expense of increased trip time, up to 2000 kg each, which may be critical for survivability. Trade offs between payload mass, transfer time, launch site, inclination, and height of parking orbits are presented.
Document ID
19860029693
Document Type
Conference Paper
Authors
Wang, S.-Y. (NASA Lewis Research Center Cleveland, OH, United States)
Staiger, P. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
July 1, 1985
Subject Category
SPACECRAFT PROPULSION AND POWER
Report/Patent Number
AIAA PAPER 85-1477
Distribution Limits
Public
Copyright
Other