POWERSAT CONFIGURATION This configuration is the result of concept studies begun on Boeing IR&D and presently being continued under a contracted study with the NASA Marshall Space Flight Center in Huntsville. The solar concentrator, cavity absorber, and heat engines are analogous to the heliostat/towertop ground solar power system being researched by Boeing Engineering and Construction. Because of their space environment, the satellite's concentrator heliostats can be much larger, do not require protection by bubbles, can be nested close together and require a tracking angle of only a few degrees. Lack of oxidation allows the cavity and turbines to be operated at a higher temperature through use of refractory alloys. Without gravity, turbogenerators can be entirely supported on gas bearings. Heat rejection is accomplished by the large thermal radiators employing a liquid metal loop and a helium/liquid metal heat exchanger. Most of the problems associated with liquid alkali metals result from contamination of the metals by air or reaction with air or water. These problems are not present in space. The power generated by the machinery is routed along the satellite structural main frame members to the antenna, where it is rectified to D.C. to drive the RF generation system. The configuration illustrated would produce 10,000 megawatts of net useful output from the ground receiver. Its mass is estimated at slightly over 100,000 tons; it is about nine miles long. Also shown in the illustration are some of the electric tug orbit transfer units.
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