FIELD: spacecraft. SUBSTANCE: one end of rocket engine chamber housing is secured on nozzle head. Said housing consists of combustion chamber housing and divergent nozzle housing, both made of high heat temperature steel. Nozzle part located between combustion chamber housing and divergent nozzle housing is made of platinum and iridium alloy. Invention makes it possible to design expedient and easy to make combustion chamber of rocket engine in which regenerative cooling of nozzle part is not required and whose walls feature high strength at high temperatures. EFFECT: improved operation reliability. 4 cl, 1 dwg
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