METHOD OF OPERATION OF LIQUID-PROPELLANT ROCKET ENGINE WITH TURBOPUMP DELIVERY OF CRYOGENIC PROPELLANT ON BASIS OF OXYGEN OXIDIZER AND HYDROCARBON FUEL AND LIQUID- PROPELLANT ROCKET ENGINE IMPLEMENTING SAID METHOD

摘要

FIELD: rocketry. SUBSTANCE: proposed method of operation of liquid-propellant rocket engine with turbopump delivery of cryogenic propellant at which mass of oxidizer consumed for obtaining oxidizing gas is used first for cooling waste vapor, and oxidizing gas consumed for generating vapor is used directly for afterburning of remaining part of fuel in thrust chamber. Liquid propellant rocket engine implementing proposed method comprises heat exchanger-condenser whose oxidizer line output is connected with chamber nozzle head by gas conduit with built-in heat exchanger-heater. EFFECT: increased efficiency of liquid-propellant rocket engine by increasing specific thrust pulse. 5 cl, 3 dwg