Abstract
The article considers a variant of using carbon heating elements for increasing the thermal stability of space-based radar satellite antenna. The effectiveness of such a variant is justified. The radiative-conductive heat transfer of the reflector structure was simulated as part of a flight in a low Earth orbit using carbon heating elements, which showed a decrease in the level of thermal displacements of the reflector mirror from 1.8 to 0.4 mm. The effect of the power and the layout of carbon heating elements on the temperature state of the reflector has been studied. The dimensional stability of its structural elements was assessed.
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