SOLID PROPELLANT ROCKET ENGINE Russian patent published in 2010 - IPC F02K9/92 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises housing made from composite material, nozzle and shut-off assemblies made on housing front bottom. Each thrust shut-off assembly comprises inserted flange arranged below load bearing envelopment with its wing covered by inner heatproof coat of the case, reverse thrust nozzle socket secured to the latter and plug with sealing assembly locked by locking device that comprises pyrotechnical appliance and cams or balls arranged in trapezoidal groove of aforesaid socket. Cams or balls are radially locked by locking device, ID of inserted flange equals that of through hole made in the case bottom and plug OD. Reverser thrust nozzle socket is attached to inserted flange by studs, bolts or screws passed through case load bearing envelopment. Inserted flange wing apex radius exceeds radius of circle circumscribed around studs by at least 1.225 times. Sealing assembly is arranged in the area of joint between plug and inserted flange, while the latter represents a ring jointed with the wing by a thin web.

EFFECT: reduced weight, higher stability of operation, longer life.

3 cl, 3 dwg