MULTI-STAGE CARRIER ROCKET, METHOD TO LAUNCH IT AND THREE-COMPONENT ROCKET ENGINE Russian patent published in 2010 - IPC B64G1/40 F02K9/46 

FIELD: transport.

SUBSTANCE: invention relates to rocketry. Proposed carrier rocket comprises 1^st- and 2^nd-stages connected in parallel and having oxidizer and fuel tanks. Second-stage unit accommodates 2^nd-fuel tank. Second-stage engines comprise combustion chamber and turbo pump unit arranged in parallel with combustion chamber or at an angle to it. Turbo pump unit comprises turbine, three-component gas generator, oxidizer pump, 2^nd-fuel pump, extra 2^nd-fuel pump, 1^st-fuel pump and extra 1^st-fuel pump. 2^nd-fuel pump is mounted directly under oxidizer pump. Three-component gas generator outlet is communicated, via gas duct, with combustion chamber. Rocket engine comprises combustion chamber with jet nozzle incorporating regenerative cooling system, has generator, turbo pump unit consisting of turbine gas generator, oxidizer pump and fuel pumps. Turbo pump unit comprises two fuel pumps and two extra fuel pumps intended for consecutive operation on 1^st and 2^nd fuels without changing oxidizer. 2^nd-fuel pump and extra pump are arranged directly under oxidizer pump and are connected, via cut-off valves, with gas generator. Launching method comprises simultaneous starting the engines of 1sr and 2^nd stages operating on oxidizers and 1^st-fuel, cutting off 1^st-stage engines and detachment of1st-stage units. Thereafter, every engine of 2^nd-stage is switched over to feeding by second fuel.

EFFECT: higher reliability.

10 cl, 4 dwg