Unique nuclear thermal rocket engine

Details Unique nuclear thermal rocket engine Unique nuclear thermal rocket engine

Jan 1993

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993aipc..271..669c&link_type=abstract

Proceedings of the tenth symposium on space nuclear power and propulsion. AIP Conference Proceedings, Volume 271, pp. 669-675 (

Physics

Propulsion Reactors, Flows In Ducts, Channels, Nozzles, And Conduits

Scientific paper

Earlier this year Aerojet Propulsion Division (APD) introduced a new, advanced nuclear thermal rocket engine (NTRE) concept intended for manned missions to the moon and to Mars. This NTRE promises to be both shorter and lighter in weight than conventionally designed engines, because its forward flowing reactor is located within an expansion-deflection (E-D) rocket nozzle. The concept has matured during the year, and this paper discusses a nearer term version that resolves four open issues identified in the initial concept: (1)Reactor design and cooling scheme simplification while retaining a high pressure power balance option; (2)Eliminate need for a new, uncooled nozzle throat material suitable for long life application; (3)Practical provision for reactor power control; and (4)Use near term, long life turbopumps.

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