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

FIELD: engines and pumps.

SUBSTANCE: invention relates to multi-chamber liquid propellant rocket engines. Proposed engine comprises at least two swinging combustion chambers with jet nozzles furnished with regenerative cooling system. In compliance with this invention, nozzle extensions are arranged coaxially with every said jet nozzle on lower bearing plate representing a nozzle extension that can move along combustion chamber lengthwise axis, driven by two drives (per every combustion chamber). Said drives comprise actuating mechanism, a motor, coupled via worm reduction gear and screw gear, with aforesaid lower bearing plate. Note that that said drives are coupled with upper bearing plate fixed on combustion chambers, and that screw gear screws pass through nuts arranged in lower bearing plate.

EFFECT: improved operating performances of liquid propellant engine in wide range of flight conditions at various altitudes, simplified pneumohydraulic circuit and increased chamber pressure at minimum overall dimensions.

4 dwg