We propose a Phase I study to examine the potential for a lightweight carbon thermal management system, for hi-altitude aircraft and space vehicles. Thermal Hyperconducting carbons have demonstrated performance as high as 2000 W/mK. They are in use in some limited heat sink application at.this time, however this effort will look at a systems approach to conduct comprehensive thermal management of the flight vehicle, from heat source identification, thermal- transport, and radiation to the ether. We intend to study unidirectional carbon fibers in matrix, and in flexible rope forms, incorporated into a system to transport thermal energy in a rapid and efficient manner to carbon radiators. We have past experience in this technology in the IR decoy technology development area, and are well equipped to fabricate and test structures in Phase 1. The study will consist of three (3) segments. 1), an analytical study that includes mathematical modeling, a limited systems analysis and literature search. 2), a thermal management system design effort that will consider applications/configurations in space vehicles, and 3) fabrication of a prototype thermal transport device, and a test series to verify performance. Documentation will include study and test results, designs, and detailed plans for Phase II
