temperature of 1075 K. A subsystem mass breakdown of both systems is shown in Fig. 14. Optimized values of the design variables are shown in Tables II and III. Conclusions We determined that a 1 MWe nuclear power plant could be designed for launch in a single shuttle flight using either Rankine cycle or thermionic conversion. We also determined that thermionic conversion is more suitable for space use than Rankine cycle conversion in this power range. The thermionic conversion cycle efficiency was 16.2% and the system specific mass was 5.6 kg/kW. This design study elucidated a design procedure for space nuclear power systems in the megawatt range. The most crucial design parameters for megawatt scale Rankine and thermionic powerplants were determined. Subjects requiring further research were identified. REFERENCES [1] Caveny, L.H. (1983) Orbit raising and maneuvering propulsion: research and needs, Progress in Astronautics and Aeronautics, 89 (AIAA, New York). [2] Buden, D. (1980) The Acceptability of Reactors in Space (LA-8724-MS). [3] Angelo, J.A. & Buden, D. (1985) Space Nuclear Power (Orbit Books, Malabar, Florida). [4] Kirpich, A., Biddiscombe, R., Chan, J. & McNamara, E. (1986) Comparison of concepts for a 300KWe nuclear power system, Proceedings of the 21st IECEC Conference, San Diego, CA, 25-29 August, 1986. [5] Josloff, A.T. & Chiu, W.S. (1986) Operational aspects of spacecraft using space reactor power systems, Proceedings of the 21st IECEC Conference, San Diego, CA, 25-29 August, 1986. [6] Dean, V.F. & El-Genk, M.S. (1984) Design Status of the SP-100 Heat Pipe Space Nuclear Reactor System (AFWL-144-1). [7] El-Genk, M.S. & Seo, J.T. (1985) Feasibility Study of Upgrading the SP-100 Heat Pipe Space Nuclear Power System (AFWL-TR-84-126, Vol. II, August). [8] Kikuti, T. et al, (1981) Experimental Measurement of Thermal Conductivity of Fuel Compact for HTGR and Gap Conductance between Fuel Compact and Carbon Sleeve (JAERI memo 9287). [9] Ranken, W.A. (1983) Space Reactors (LA-9598-PR). [10] Merrigan, M.A. (1985) Heat pipe technology issues, Space Nuclear Power Systems 1984 (Orbit Book Company, Malabo, FL) Chapter 48, pp. 419-426. [11] Reay, (1981) Advances in Heat Pipe Technology (Pergamon Press, Oxford). [12] Dunn & Reay (1987) Heat Pipes (2nd ed., Pergamon Press, Oxford). [13] English, E.R. et al, (1960) A 20,000KW Nuclear Turboelectric Power Supply for Manned Space Vehicles (NASA-TM 2-20-59E). [14] Shimizu, S. & Fukuda, R. (1986) Analysis of output-current characteristics of thermionic converters, Bui. Electrotech. Lab., 50, 11. [15] Wilkins, D.R. (1968) SIMCON-Digital Computer Program for Computing Thermionic Converter Performance Characteristic (GESR-2109). [16] Buden, D. et al, (1978) Selection of Power Plant Elements for Future Reactor Space Electric Power Systems (LA-7858). [17] The HPAD heat pipe code was developed by J. P. Wright of North American Rockwell.
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