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This paper describes a solar-powered, closed-Brayton-cycle power system and its application to manned space stations. The power system has been designed to meet the following objectives: 1. Utilization of presently available design techniques and standard materials. 2. High reliability. 3. Short development period. 4. Low costs. 5. Adaptability for launch by the Atlas, Titan, and Saturn class vehicles. The system described meets all of these objectives. In addition, it is flexible enough in design that a single set of dynamic rotating components can be used over a 10:1 power range. The heat-transfer components, which are modular in design, can be sized to meet the required power level.