FIELD: transport.
SUBSTANCE: set of invention relates to multi-stage carrier rocket, three-component rocket engine, method of its starting, turbo pump unit and three-component gas generator. Multi-stage carrier rocket comprises first- and second-stage rocket assemblies connected in parallel wit oxidiser and fuel tanks. Second-stage assembly accommodates second fuel tank. Second-stage engine comprises combustion chamber and turbo pump unit. Turbo pump unit comprises turbine, two-zone has generator, oxidiser pump, additional oxidiser pump, second fuel pump and first fuel pump. Drain pipeline with drain valve is arranged between second fuel additional pump and starting shut-off valve of second fuel. Engine comprises combustion chamber with nozzle and regenerative cooling system, turbo pump unit incorporating gas generator, turbine, oxidiser and fuel pumps. Outlets of all pumps are communicated with three-component two-zone gas generator inlet. Gas generator outlet is communicated via gas line with every combustion chamber. All valves are electrically connected with control unit. Method of engine operation comprises feeding oxidiser and fuel into gas generator and combustion chamber, their ignition and exhaust of combustion products via foresaid nozzle. First fuel run out, a portion of second fuel is fed into gas generator, then remaining second fuel is fed thereto. Second fuel pump and second fuel additional pump are cooled down by forcing second fuel via drain valve to produced liquid phase.
EFFECT: improved operating performances of rocket second-stage engines.
5 cl, 7 dwg
