INVESTIGATION OF A 15-KW SOLAR DYNAMIC POWER SYSTEM FOR SPACE APPLICATION.
Interim summary rept., 1 Jun 60-1 Jun 62,
SUNDSTRAND AVIATION-DENVER COLO
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The general design studies, detailed design efforts, conceptual experimental component fabrication, and development testing completed through the report period is summarized. During the report period the evaluation and generation of design technology predominated. Through system studies a full scale design was created consisting of an inflatable concentrator, a solar energy divider, a double cavity heat receiver-storage unit, a multi-stage turbo-alternator assembly running on rubidium lubricated hydrodynamic bearings, and a radial flow radiator-condenser. Feasibility studies and designs were completed for an orientation system which minimizes reaction forces fed back to an assumed vehicle. Studies were completed for the integration and erection of the space power system SPS with an assumed vehicle. First priority was given to proving feasible a large size solar concentrator. A design competition was staged between a folding rigid mirror and an inflatable type. During this competition, 10 foot diameter scale methods of each were built and tested. Several flux traps were designed and tested. The heat receiver-storage assembly remains the most critical element of the system. A small scale unit is being fabricated for future evaluation. Author