Fig. 1 - The Shooting Star Flight Experiment

The Shooting Star Experiment (SSE) incorporates a thin film deployable Fresnel primary concentrator, thin film support structures, a refractive secondary concentrator, a high temperature engine, nitrogen propellant, and associated instrumentation integrated onto a Spartan experiment carrier. NASA Marshall Space Flight Center managed the project which involved a government/university/industry team of NASA GRC, University of Alabama in Huntsville, and United Applied Technologies.

Fig. 2 - SSE Engine and Refractive Secondary Concentrator inside the Spartan

Fig. 3 - Schematic of the Refractive Secondary integrated with the engine

Figures 2 and 3 illustrate the refractive secondary integrated with the SSE engine. Concentrated solar flux from the Fresnel primary concentrator impinges on the domed inlet of the refractive secondary. Through refraction and total internal reflection, the solar flux travels through the secondary and exits at the extractor tip onto the engine cavity, heating the cavity to temperatures in excess of 2000 K. The propellant travels through the hot engine, heats up, expands through the nozzle providing thrust. Fig. 4 - is a photograph of a prototype refractive secondary concentrator.

Fig. 4 - Prototype Refractive Secondary Concentrator installed in Support Structure

Due to budget constraints the Shooting Star flight project was cancelled in the Fall of 1998. The development of the refractive secondary concentrator is continuing under Space Solar Power.

Last Revision: January 4, 2000

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