FIELD: machine building; cosmonautics.
SUBSTANCE: invention relates to solid-propellant rocket engines (SPRE). In a solid-propellant rocket engine comprising a housing from a composite material, comprising a bottom with a metal flange disposed in the central opening of the bottom, and connected to metal flange nozzle with gas duct, support flange is installed on flange with support on flange annular ledge surface, in the annular groove of which on the inner surface on the side of the outer surface of the housing bottom a clamping ring is installed in an axially movable manner, which is borne against the external surface of the housing by the rubber gasket, wherein that in the support ring there are a number of through threaded holes arranged along coaxial support ring of ring, in which there are bolts, wherein bolts are screwed against the stop in the clamping ring.
EFFECT: proposed technical solution makes it possible to improve the SPRE structure operational reliability with the nozzle having the gas duct.
6 cl, 3 dwg
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