Previous spacecraft heat rejection systems have been tailored to a specific spacecraft and a specific mission. Many different panel designs, fluids, and control methods have been used with no significant degree of commonality. For future spacecraft, it is desirable to have heat rejection systems which can accommodate widely varying loads and have a high degree of commonality to minimize development requirements. A modular radiator system which satisfies this requirement and is adaptable to a variety of future vehicles and missions is described. A test program with two modular panels connected in several flow arrangements, which are representative of candidate shuttle orbiter and other future spacecraft applications, is described.
ASME PAPER 72-ENAV-34
American Society of Mechanical Engineers, Environmental Control and Life Support Systems Conference; Aug. 14-16, 1972; San Francisco, CA