Carbon-Carbon Composite for Space Radiators

The program objective is to fabricate and test carbon-carbon panels for spacecraft radiators with a thermal conductivity above 700 W/mK. Innovations required to meet this objective are: (1) 1100 W/mK K1100X graphite fiber, (2) unique weaving techniques that will provide a nearly unidirectinal preform with adequate mechnical strength for handling and launch loads, and (3)careful impregnation of pitch A240 into the preform, possibly supplemented with CVD. The matrix should orient itself to the graphite fibers with an apparent growth of the fiber diameter. Maximum density is vital with a goal of 1.85 g/cc. Through flattening of the fiber tow, it is expected that thickness in the range of 10 mils can be obtained. Evaluation consist of non-destructive thermal conductivity measurements and mechanical property measurements. Phase II activities will include composite scale-up, proof of thermal and mechanical property reproducibility, and a design data base will be developed.