FIELD: astronautics.
SUBSTANCE: invention relates to space engineering and can be used in designs of spacecrafts (SC) and power plants refrigerators-radiators. Spacecraft low-potential energy release device radiator includes metal tube with outer protective heat-conducting layer. External protective heat conducting layer is made of at least two identical longitudinal tubular elements arranged around tube. Walls of adjacent tubular elements are in contact and are made from carbon-carbon composite material based on highly thermally-conductive carbon fibre. Ends of tubular elements are closed. Tubular elements are filled with light filler.
EFFECT: increasing radiator heat removal capacity and protection.
4 cl, 2 dwg
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