FIELD: rocket engine.
SUBSTANCE: proposed nozzle cover of rocket engine contains spherical diaphragm secured on wall of supersonic part of nozzle and pointed by convex side of sphere to engine chamber. Thickness of spherical diaphragm is defined by 
where k=1.6-1.8 is empirically determined coefficient; 
is radius of sphere; p is cover operating pressure; E is modulus of elasticity of material of diaphragm. Invention provides integral and tightness of cover exposed to action of pressure of gases from powder pressure accumulator and after starting of rocket engine and designed level of cover opening pressure and considerably lower level of gas pressure of powder pressure accumulator at minimum mass of ejected parts.
EFFECT: provision of integrity and tightness of nozzle cover.
1 dwg
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