METHOD OF OPERATION OF LIQUID-PROPELLANT ROCKET ENGINE AND LIQUID-PROPELLANT ROCKET ENGINE USED FOR REALIZATION OF THIS METHOD Russian patent published in 1998 - IPC

FIELD: rocketry; single- stage facilities for injection of payloads into near-earth orbits. SUBSTANCE: engine includes gas generator, fuel and oxidizer turbo-pump units, chamber with regenerative cooling line and units of engine automatic control equipment. Fuel main units work continuously on methane and hydrogen. All fuel is converted into reducing generator gas whose small amount is fed to turbine and then is discharged into chamber nozzle; the remaining part is subjected to after-burning with liquid oxygen. Engine is provided with unit for successive supply of methane and hydrogen fitted before fuel pump; gas generator is located coaxially relative to chamber. Its outlet is simultaneously used as chamber inlet. EFFECT: enhanced reliability and efficiency of devices used for injection of payloads into near-earth orbit due to replacement of double-stage launch vehicle by single-stage with proposed methane-hydrogen-oxygen engine. 3 cl, 1 dwg