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

FIELD: engines and pumps.

SUBSTANCE: invention is related to rocket engineering. Controlled liquid-propellant rocket engine comprises combustion chamber installed on frame with jet nozzle, having system of regenerative cooling, turbopump set arranged as a single unit, which comprises turbine, oxidant and fuel pumps, gas generator installed upstream turbine, at the same time nozzle extension is installed concentrically to jet nozzle, and is arranged in its profile as nozzle continuation and has the possibility to move along axis of combustion chamber with the help of four independent drives, which comprises actuating mechanisms, and four two-element mechanisms and ball hinge for extension rotation. Nozzle extension is arranged of carbon-carbon composite material. Nozzle extension is arranged as cooled and comprises cooling jacket, which is installed concentrically to nozzle extension with production of clearance, cavity of which is connected to fuel pump and fuel header by means of flexible pipelines. At least one electric motor is used as actuating mechanisms. At least one pneumatic cylinder is used as actuating mechanisms.

EFFECT: invention provides for optimal operation of rocket engine in wide range of modes at various height, simplification of pneumatic hydraulic layout, increased reliability and improved efficiency.

6 cl, 4 dwg