LIQUID-PROPELLANT ROCKET REHEAT ENGINE Russian patent published in 2000 - IPC

FIELD: rocketry. SUBSTANCE: engine has chamber, fuel and oxidizer booster pumps, turbo-pump unit, gas generator, thrust regulator with programmed reversal actuator and propellant component ratio throttle valve. Provision is made for programmed starting and ignition system which includes fuel reservoir connected to low-flow loop of thrust regulator and fuel ampoule whose outlet is connected with fuel injectors of gas generator through start-and-shut-off valve. This reservoir is also connected to self- contained ignition injectors located in combustion chamber of engine through starting fuel ampoule. Used as oxidizer booster-pump is screw pump driven by gas turbine; its working medium is oxidizing gas which is exhausted to outlet manifold of booster pump. Feed pipe line of gas turbine of prepump is provided with heat exchanger where has intended for pressurization of rocket tanks is preheated. EFFECT: possibility of working of engine on low-toxic non-self-ignition components of propellant; reduced dynamic action of engine on rocket in the course of start; enhanced efficiency of pressurization system. 8 cl, 1 dwg