Performance potential of advanced solar thermal propulsion
Design features, component test results, and performance levels of a solar thermal propulsion system for transferring payloads from LEO to GEO are detailed. Solar radiation is collected by two inflated paraboloidal reflectors which funnel the light into a radiant cavity through which propellant is flowing. The propellant, preferably H2 due to its high specific impulse at low temperatures, is then directed through a nozzle to provide 200 lb of thrust. Attention has been given to turbine, rotating bed, and seeded absorber configurations. Testing concentrated on directly heated concepts because of a potential 20 pct increase in thrust using 24.7 kWt concentrated on a 6 cm diameter spot. An open-ended-absorber reached a 76.9 pct thermal efficiency and delivered a specific impulse of 808 lbft-sec/lbm. Rhenium tubes were used in the final test design, which included a quartz window with an IR protective coating. Further component testing is recommended, together with investigations of advanced concepts, in order to assay the ultimate performance capabilities of the propulsion system.
- OSTI ID:
- 6485141
- Report Number(s):
- CONF-830635-
- Resource Relation:
- Conference: 19. AIAA-SAE-ASME joint propulsion conference, Seattle, WA, USA, 27 Jun 1983
- Country of Publication:
- United States
- Language:
- English
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