SOLID PROPELLANT ROCKET ENGINE Russian patent published in 2013 - IPC F02K9/32 

FIELD: engines and pumps.

SUBSTANCE: rocket engine comprises a body with a nozzle block, front and rear bottoms, an insert charge burning on the outer surface and a sleeve. The cylindrical part of the sleeve is arranged with a gap relative to the body and the outer surface of the charge, and the bottom contacts with the end of the charge and the rear bottom of the engine. The circular cavity between the sleeve and the bottom is sealed at the side of the rear bottom. The sleeve is made of combustible material on the basis of polyacryamide filled by nitrocellulose at the ratio of nitrocellulose:polyacrylamide - 2…3:1. In the bottom of the sleeve there are holes to gas passage from the slot gap "charge - sleeve" to the nozzle.

EFFECT: invention makes it possible to reduce effect of a thermal flow of combustion products at a rocket engine body and to increase total thrust impulse.

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