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.
Unique nuclear thermal rocket engine
10th SymposiumùSpace Nuclear Power and Propulsion ; 1993 ; Albuquerque, NM, USA
AIP Conference Proceedings ; 271 , 2 ; 669-675
15.01.1993
7 pages
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Unique nuclear thermal rocket engine
AIAA | 1993
|Unique Nuclear Thermal Rocket Engine
British Library Conference Proceedings | 1993
|