Computer Science – Performance
Scientific paper
Jan 1992
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992aipc..246..714c&link_type=abstract
Proceedings of the ninth symposium on space nuclear power systems. AIP Conference Proceedings, Volume 246, pp. 714-720 (1992).
Computer Science
Performance
Propulsion Reactors, Theory, Design, And Computerized Simulation
Scientific paper
Aerojet Propulsion Division (APD) studied 75-klb thrust Nuclear Thermal Rocket Engines (NTRE) with particle bed reactors (PBR) for application to NASA's manned Mars mission and prepared a conceptual design description of a unique engine that best satisfied mission-defined propulsion requirements and customer criteria. This paper describes the selection of a sprint-type Mars transfer mission and its impact on propulsion system design and operation. It shows how our NTRE concept was developed from this information. The resulting, unusual engine design is short, lightweight, and capable of high specific impulse operation, all factors that decrease Earth to orbit launch costs. Many unusual features of the NTRE are discussed, including nozzle area ratio variation and nozzle closure for closed loop after cooling. Mission performance calculations reveal that other well known engine options do not support this mission.
Culver Donald W.
Dahl Wayne B.
McIlwain Melvin C.
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