INTEGRAL RADIATORS FOR NEXT GENERATION THERMAL CONTROL SYSTEMS, Phase I

The main goal of spacecraft thermal control systems is to maintain internal and external temperature within acceptable boundaries while minimizing impact on vehicle mass, complexity and operability. Paragon is proposing to develop an integrated radiator/structure design approach that will permit efficient thermal performance of the integral radiator while simultaneously serving as a load bearing structure member. The innovation in the proposed design is to integrate the radiator within the stressed skin of the vehicle thereby achieving a superior lb/sq ft penalty over conventional designs while establishing a baseline coating system that will survive the ground, launch pad and ascent environments. An additional possibility will be to achieve survival of coatings in a leeward reentry environment for added benefit to reusable OSP concepts. Our proposal would advance the state-of-the-art in integral radiator designs for conformal structure applications by reducing the key technology development risks so they can be considered for the next generation manned space systems, such as the OSP, as well as other applications. The central objective of the combined Phase I and Phase II work plan is to take load bearing, environmentally compatible radiator designs from the present position of TRL 3, to TRL 5 or 6.

This is a mature technology (TRL 7+) — the realistic path in is usually NASA's Technology Transfer Program: licensing an existing NASA patent, or a Space Act Agreement to use NASA facilities/expertise directly. NASA also runs a startup licensing program with no upfront fee for companies formed to commercialize a specific NASA technology.

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