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Reactor moderator, pressure vessel, and heat rejection system of an open-cycle gas core nuclear rocket conceptA preliminary design study of a conceptual 6000-megawatt open-cycle gas-core nuclear rocket engine system was made. The engine has a thrust of 196,600 newtons (44,200 lb) and a specific impulse of 4400 seconds. The nuclear fuel is uranium-235 and the propellant is hydrogen. Critical fuel mass was calculated for several reactor configurations. Major components of the reactor (reflector, pressure vessel, and waste heat rejection system) were considered conceptually and were sized.
Document ID
19730018848
Document Type
Technical Memorandum (TM)
Authors
Taylor, M. F. (NASA Lewis Research Center Cleveland, OH, United States)
Whitmarsh, C. L., Jr. (NASA Lewis Research Center Cleveland, OH, United States)
Sirocky, P. J., Jr. (NASA Lewis Research Center Cleveland, OH, United States)
Iwanczyke, L. C. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
July 1, 1973
Subject Category
NUCLEAR ENGINEERING
Report/Patent Number
E-6588
NASA-TM-X-2772
Funding Number(s)
PROJECT: RTOP 503-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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NameType 19730018848.pdf STI