Spacecraft radiator system

A heat pipe radiator comprising:

• a plurality of parallel positioned pipes, each having evaporator and condenser sections therealong;
• circumferential fine grooves formed along an interior wall of the pipes for creating high film coefficients therebetween for preventing low temperature drops along the evaporator and condenser sections;
• a planar baffle located within each pipe for creating separate liquid and vapor channels thus minimizing viscous pressure loss coupled with high capillary rise capability for high hydrodynamic transport capacity;
• each pipe having two opposing pairs of elongated spaced flanges extending laterally outward;
• and
• a plurality of carbon-carbon fin sections having their respective edges clamped between adjacent pairs of flanges, the material of the fin sections having a lower coefficient of thermal expansion than that of the pipes thereby causing release of clamping pressure therebetween and minimizing heat flow from the fin to the pipe in the event the fin is exposed to a high energy source;
• fibers in the carbon-carbon material being directed perpendicular to the pipes for optimizing heat flow from the pipes to the fin sections;
• and
• a curved fine mesh member located along the interior length of each pipe to serve as a barrier between the liquid and the heat pipe wall on the return path of liquid from the condenser to evaporator sections.