NOZZLE UNIT OF SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2002 - IPC

FIELD: solid-propellant rocket engines. SUBSTANCE: nozzle unit of solid-propellant rocket engine includes central body and supersonic nozzle which is mounted in telescopic guide and is rigidly connected with piston. Piston is located in cylinder secured on body; working chambers of cylinder which are divided by piston are connected with engine combustion chamber by means of passages which are made in nozzle throat with throttle orifices; cylinder cavities are connected with supercritical part of nozzle through outlet throttle orifices connected by exhaust passage running in throat of movable nozzle into its supercritical part. Cavities of cylinder are interconnected by throttle passage made in piston. Nozzle unit is provided with spring-loaded relief valve and working chamber is connected with supercritical part of nozzle through liquid-flow throttling valve of varying throat section whose magnitude depends on axial displacement of piston. EFFECT: reduced mass and overall dimensions of nozzle unit due to avoidance of mechanical spring used for securing the supersonic nozzle. 2 cl, 1 dwg