CONTROLLED LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2003 - IPC

FIELD: rocketry. SUBSTANCE: controlled liquid-propellant rocket engine contains chamber, gas generator and turbopump set with centrifugal pumps and turbine. Automatic control system contains valves, liquid flow controllers and liquid flow stabilizer. High-and low-pressure propellant main lines include at least two high- pressure liquid propellant main lines with liquid flow controllers operated by drives when electric commands are sent. Engine is furnished with control electric valves and command shaping unit to form commands for operation of control electric valves. At least two high-pressure liquid propellant main lines are branched into two parallel lines provided with common inlet and common outlet for each main line. Each liquid flow controller is made in form of hydraulic valves installed in corresponding lines of main lines and operated by control electric valves. Said hydraulic valves have two fixed positions, namely open and closed. EFFECT: improved response of liquid propellant engine control system with provision of quickly changing thrust value. 4 cl, 6 dwg