FIELD: aircraft industry; rocketry.
SUBSTANCE: proposed solid-propellant rocket engine has combustion chamber with nozzle unit, multigrain powder charge, igniter and electroigniter. Cylindrical post is secured on front bottom of combustion chamber of end of which support with central threaded hole is installed coaxially to chamber. Said support is made in form of multiarm star. Cavities of multiarm star are mated with cylindrical surfaces of charge grains. Conical recess is made on other end of support from which cylindrical gas outlet channels are laid getting into cavities of multiarm star. Spherical space with symmetrical projections is formed on inner surface of nozzle unit. Inner surface of projections is mated with outer surface of one of grains of powder charge. Area of one through section between projections with powder charge fitted in exceeds area of charge grain channel. Support in form of multiarm star is made mainly of nonmetal material.
EFFECT: prevention of nondesigned increased of pressure at beginning and end of engine operation, and also vibratory combustion of charge, reduced spread of output characteristics in temperature range of operation, improved reliability if engine.
3 cl, 2 dwg
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