SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2000 - IPC

FIELD: rocketry. SUBSTANCE: engine has charge in form of solid-propellant grain, supersonic nozzle with central body secured on thin-walled tube connected with movable end face of grain and guide secured on bottom of housing on side opposite to nozzle. Engine is also provided with rod which is spring-loaded relative to housing; this rod is mounted in tubular guide; thin-walled tube is flexibly suspended from rod embracing it for fixing on this rod. Rod is provided with damper whose housing is secured on guide; thin-walled tube is connected with movable end face of propellant grain by means of levers whose fixed stop is mounted on housing; shorter arm of lever rests against solid-propellant grain and longer arm is articulated with thin-walled tube. Damper may be hydraulic or gaseous. Construction provides for automatic adjustment of nozzle in accordance with initial combustion temperature of solid propellant, thus ensuring stable operation of thrust stabilizer with closed control of pressure in combustion chamber. EFFECT: reduced spread of thrust during operation of engine. 7 cl, 4 dwg