Abstract: The present invention pertains to the field of rocketry and more precisely to liquid-propellant rocket engines and to rocket power units. This invention essentially relates to a method for increasing the specific impulse in a liquid-propellant rocket engine by using oxygen as well as a hydrocarbon fuel consisting of dicyclobutyl (C8H14). The dicyclobutyl provides for a substantial increase in the specific impulse of the liquid-propellant rocket engine when compared with kerosene. This invention also relates to a power unit for a rocket that has tanks for liquid oxygen and for the hydrocarbon fuel. Since the fuel tank is filled with dicyclobutyl (C8H14), it is thus possible to increase the thrust, the specific impulse, as well as the in-flight operation duration of the engine, and to reduce the weight of the tanks without any substantial change in the circuits of the liquid-propellant rocket engine and of the rocket power unit.

Abstract: The invention relates to the field of automatic equipment and, in particular, to devices for chemical ignition of liquid rocket engine propellant components. The ampoule comprises a body, diaphragm units mounted at the body inlet and outlet, each of which is made as a piston made as a single part with a diaphragm. The peripheral part of the diaphragm is fixed in an air-tight manner to the body under a guide element in which the body is mounted. The piston has a stem extending into a guide bush. Furthermore, a device for filling the ampoule with fuel is located in a partition of the body inside the ampoule. A guaranteed cutting of the diaphragm along the entire perimeter and reproduction of hydraulic characteristics for the flow part of the ampoule are achieved in this ampoule design.

Abstract: The engine comprises a chamber, fuel and oxidizer booster pumps, a turbopump unit, a gas generator, an electrically driven thrust regulator, and a fuel throttle. A programmable starting and ignition system is introduced, which includes a fuel tank, connected to the thrust regulator, and a first ampoule with starting fuel, an output of which through a starting/cut-off valve is connected to fuel injectors of the gas generator. The aforesaid tank is also connected through a second ampoule to the starting fuel and by a jet to autonomous ignition injectors located in the space of the combustion chamber of the engine. An inclined Archimedian screw pump with a gas turbine as an actuator and an oxidizing gas as a working medium is used as an oxidizer booster pump. The gas is discharged after its use in a turbine into an outlet manifold of the booster pump.

Abstract: The liquid-propellant rocket engine comprises two combustion chambers, a gas generator, a turbopump assembly, pipelines as well as a frame having footpads and supports located in different planes that are perpendicular to the engine axis, said frame being made up of at least two welded rod sections. Said sections are fastened to each other by a plane rod joint. The engine pipelines are connected to the combustion chambers and comprise bellows balances or flexible hoses which have their movable ends connected directly to the combustion chambers or to pipes joined thereto. The frame is made demountable due to the use of threaded connections that joint together the frame sections and the plane rod joint. The frame is made as a compensation frame by placing the footpad plane over the support plane. A curved pipe joint comprises a curved pipe, a hinge and a frame.

Abstract: The invention relates to the field of producing the means for protecting the alloys on the nickel base against the influence of corrosive media, and more particularly concerns the metal-ceramic coatings used for protecting the flow parts of the turbines of turbopump liquid-propellant rocket engines (LRE). The composition for producing the metal-ceramic coating consists of nickel and of oxides of barium, boron, aluminum, cerium and zirconium at the following percentage of components by mass: nickel--36-58, barium oxide--16-19, boron oxide--7-13, aluminum oxide--6-9, cerium oxide--14-19, zirconium oxide--1-2. The coating is produced of a slip, that is applied to the pieces by dipping, spraying or flooding. The slip layers are dried in the flow of hot air. The coating is fired in a furnace in the inert gas medium, argon for example, at a temperature of 1000-1100.degree. C. during 0.5-1 hour.