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

FIELD: engines and pumps.

SUBSTANCE: proposed rocket engine comprises at least two combustion chambers with jet nozzles furnished with regenerative cooling system. In compliance with this invention, nozzle extensions are arranged concentric with every jet nozzle are attached to lower plate to move along combustion chamber axes driven by at least one actuating mechanism. The latter is jointed to upper power plate fixed on combustion chamber and furnished with locking mechanism incorporating unlocking device. The latter comprises position pickup. Every aforesaid nozzle extension is made from carbon-carbon composite and comprises cooling jacket arranged concentric with aforesaid nozzle extension to form a clearance space communicated, via flexible pipelines, with fuel pump and manifold. Note here that actuating mechanism can represent at least one pneumatic cylinder, or one hydraulic cylinder, or screw gear.

EFFECT: simplified pneumohydraulic circuit, higher reliability and power.

10 cl, 5 dwg