FIELD: aircraft manufacturing, rocketry, defense industry. SUBSTANCE: in proposed rocket engine whose rear part consists on housing with primary nozzle and six secondary nozzles arranged over perimeter and forming in assembly an ejector with outlet diffuser. Secondary nozzles made in form of spaces forming de Laval nozzles are rigidly second on engine housing and head whose front part in made conical with apex angle of 80-9 degrees. EFFECT: increased thrust of rocket engine.
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