ADJUSTABLE FLUID PROPELLANT ROCKET ENGINE Russian patent published in 2010 - IPC F02K9/97 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises at least two combustion chambers with jet nozzles incorporating regenerative cooling system. In compliance with this invention, nozzle tops are arranged concentrically about every jet nozzle on lower load-bearing plate that represent a nozzle extension and can move along axes of combustion chambers, furnished with a drive. The latter comprises at least one actuating mechanism representing a motor with worm or auger gear. Said drive is coupled with top load-bearing plate attached onto combustion chambers, while power screw passes through the nut arranged at the lower load-bearing plate center.

EFFECT: optimum engine operation at various altitudes, simplified design of pneumohydraulic circuitry, higher output and reliability.

3 dwg