The open-cycle gas-core nuclear rocket engine - Some engineering considerations.A preliminary design study of a conceptual 6000-MW open-cycle gas-core nuclear rocket engine system was made. The engine has a thrust of 44,200 lb and a specific impulse of 4400 sec. 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 the waste heat rejection system were considered conceptually and were sized.
Document ID
19720027681
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Taylor, M. F.
Whitmarsh, C. L., Jr.
Sirocky, P. J., Jr.
Iwanczyk, L. C. (NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 6, 2013
Publication Date
January 1, 1971
Subject Category
Nuclear Engineering
Meeting Information
Meeting: Symposium on Uranium Plasmas: Research and Applications