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

FIELD: aircraft industry. SUBSTANCE: proposed solid-propellant rocket engine has housing accommodating igniter and change in form of solid-propellant grain. Central body of supersonic nozzle is secured on thin-walled reduction tube coupled with movable end face of solid-propellant grain. Guide rod is secured on bottom of housing from side opposite to supersonic nozzle. Supersonic nozzle, spring-loaded relative to housing, is installed in telescopic guide and is rigidly connected with piston arranged in cylinder. Cylinder is secured on housing. Working spaces of cylinder, divided by piston, are connected with engine combustion chamber by channels made in neck of supersonic nozzle with throttling holes and form gas damper with throttling channel made in piston. Thin-walled tube is coupled with movable end face of solid-propellant grain by means of levers whose fixed stop is placed on housing. Short arm of levers rests on solid- propellant grain, and long arm is hinge-connected with thin-walled tube. Damper spaces communicate with supercritical section of supersonic nozzle through outlet throttling holes connected by channel passing in neck of supersonic nozzle. Passage areas of throttling holes of damper rear space exceed those of front space. EFFECT: provision of stable operation of thrust stabilizer with solid-propellant initial temperature open-loop control and combustion chamber, pressure closed-loop control, and rocket acceleration. 3 cl, 3 dwg