FIELD: engines and pumps.
SUBSTANCE: rocket engine nozzle plug consists of spherical membrane with a mating flange, which is fixed on the wall of supersonic nozzle part so that it faces with convex sphere side the engine chamber. Spherical membrane is made of two shells with braced tips, which are attached to each other. Mating flange is made of two annular parts. Tip of the shell located on engine chamber side is fixed between two parts of the mating flange. Tip of the shell located on the nozzle cut side is fixed on the edge of the mating flange.
EFFECT: invention allows keeping the plug continuity at acting thereon of gas pressure of cartridge pressure accumulator from the side of the nozzle cut and providing, after rocket engine has been started, design level of opening pressure from fuel combustion products, which is less than gas pressure of cartridge pressure accumulator at minimum weight of outgoing parts.
2 cl, 3 dwg
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