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An Integral Nuclear Power and Propulsion System Concept
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English
Abstract
An integral space power concept provides both the electrical power and propulsion from a common heat source and offers superior performance capabilities over conventional orbital insertion using chemical propulsion systems. This paper describes a hybrid (bimodal) system concept based on a proven, inherently safe solid fuel form for the high temperature reactor core operation and rugged planar thermionic energy converter for long-life steady state electric power production combined with NERVA-based rocket technology for propulsion. The integral system is capable of long-life power operation and multiple propulsion operations. At an optimal thrust level, the integral system can maintain the minimal delta-V requirement while minimizing the orbital transfer time. A trade study comparing the overall benefits in placing large payloads to GEO with the nuclear electric propulsion option shows superiority of nuclear thermal propulsion. The resulting savings in orbital transfer time and the substantial reduction of overall lift requirement enables the use of low-cost launchers for several near-term military satellite missions.
Authors
Citation
Choong, P., Teofilo, V., Begg, L., Dunn, C. et al., "An Integral Nuclear Power and Propulsion System Concept," SAE Technical Paper 929345, 1992, https://doi.org/10.4271/929345.Also In
References
- “A Comparison of Nuclear and Chemical Propulsion Upper-Stages and Launch Systems for LEO to GEO Orbital Transfer,” Bailey P. G. Choong P.T. 27th IECEC August 1992
- “Nuclear Rocket Program, Terminal Report” Argonne National Laboratory, Report # ANL-7236 June 30 1966
- “Advanced Nuclear Space Power Research Program: Advanced Thermionic Reactor Project” McVey J. Desplat J-L Hatch G.L. Choong P.T. Rasor N. S. October 1989
- “Hybrid Space Nuclear Reactor Concept” Begg L. Choong P.T. Teofilo V.L. Dunn C. Bhattacharyya S. 27th IECEC August 1992