In-reactor tests of the nuclear light bulb rocket concept

Details In-reactor tests of the nuclear light bulb rocket concept In-reactor tests of the nuclear light bulb rocket concept

Jul 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992jpnt.confry...g&link_type=abstract

AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 28th, Nashville, TN, July 6-8, 1992. 16 p.

Computer Science

Performance

Engine Tests, Nuclear Lightbulb Engines, Performance Prediction, Product Development, Spacecraft Propulsion, Engine Design, Propulsion System Performance

Scientific paper

An overview is given of the closed-cycle Gas Core Nuclear Rocket outlining scenarios for its use in short-duration Mars missions and results of Nuclear Light Bulb (NLB) tests. Isothermal and nonnuclear tests are described which confirmed the fundamental concepts behind the NLB. NLB reference-engine performance characteristics are given for hypothetical engines that could be used for manned Mars missions. Vehicle/propulsion sizing is based on a Mars mission with three trans-Mars impulse burns, capture and escape burns, and a total mission duration of 600 days. The engine would have a specific impulse of 1870 seconds, a 412-kN thrust, and a thrust/weight ratio of 1.3. Reactor tests including small-scale in-reactor tests are shown to be prerequisites for studying: (1) fluid mechanical confinement of the gaseous nuclear fuel; (2) buffer gas separation and circulation; and (3) the minimization of transparent wall-heat loading. The reactor tests are shown to be critical for establishing the feasibility of the NLB concept.

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