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Otkrytoe Aktsionernoe Obschestvo Nauchno-proizvodstvennoe Obiedinenie

Boris Ivanovich Katorgin

Vladimir Konstantinovich Chvanov

Gennady Grigorievich Derkach

Jury Vasilievich Movchan

Viktor Nikonorovich Semenov

Vladimir Jurievich Bogushev

Felix Jurievich Chelkis

Alexandr Alexandrovich Vasin

Alexandr Nikolaevich Vycherov

Valentin Georgievich Polushin

Jury Alexandrovich Pestov

Nikolai Kondratievich Dudkin

Nikolai Fedorovich Molev

Nikolai Mikhailovich Grigorkin

Stanislav Dmitrievich Kamensky

Vladimir Vladimirovich Fedorov

Leonid Alexeevich Tumanov

Anatoly Ivanovich Grigoriev

Anatoly Lukich Loginov

Galina Andreevna Babaeva

Alexandr Grigorievich Liakumovich

Alexandr Mikhailovich Samsonov

Alexei Pogosovich Adzhian

Oleg Andreevich Masljukov

Mikhail Ivanovich Zykov

Jury Anatolievich Tjurin

Valery Petrovich Mordashov

Vadim Iliich Semenov

Leonid Alexeevich Tolstikov

Sergei Prokopievich Chernykh

Larisa Mikhailovna Panaskina

Jury Aleksandrovich Pestov

Oleg Efimovich Batalin

Vladimir Ilich Bobkov

Vladimir Serapionovich Anufriev

Pavel Ivanovich Ogibalin

Tatiana Mikhailovna Avsenjuk

Igor Grigorievich Storozhenko

Vadim Lliich Semenov

Nina Ivanovna Murlykina

Vladimir Veniaminovich Sagalovich

Benyamin Sinaevich Strelchik

Evgeny Ivanovich Baranov

Raisa Vasilievna Chernikova

Galina Vasilievna Shashelova

Ljudmila Alexandrovna Anosova

Jury Alexandrovich Bedov

Oleg Ivanovich Studenikin

Alexei Ivanovich Kolesnikov

Viktor Petrovich Nosov

Anatoly Ivanovich Stavrulov

Evgeny Shmerovich Finkelshtein

Valentina Dmitrievna Kolesnikova

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 (C H ). 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 (C H ), 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.

Method for increasing the specific impulse in a liquid-propellant rocket engine and rocket powder unit for realising the same

A gas generator is produced of separate units, including a mixing head, a casing and an outlet branch pipe, which are interjoined by welding. The mixing head is welded to the outlet branch pipe through a spacer and a structural spherical casing. The spacer and the outlet branch pipe are made of two inter-brazed envelopes, the inner envelopes of the spacer and the branch pipe are welded at their end faces by electron-beam welding, and the outer structural envelopes are welded by electron-arc welding using a split ring. The spacer is joined to the mixing head by automatic gas-shielded welding. The spherical casing of the gas generator is welded to the outlet branch pipe and the mixing head after the spacer is welded to the mixing head and the outlet branch pipe.

Method for producing a gas generator of welded-brazed construction

A gas generator in particular for driving liquid-propellant rockets, having, a structural envelope, an outlet pipe, a cover connected to the structural envelope from the side opposite to the outlet pipe. A bush is made on the inner side of the cover. An injector face is mounted on the bush end to form a space between the injector face and the cover. Chambers are made in the injector face and the cover. A spacer, mounted inside the structural envelope, is fastened on the outlet pipe and the bush to form an annular space there between. Mixing modules are fastened in the cover and in the injector face chambers. A propellent feed inlet pipe is fastened to the outer surface of the cover inside which a propellant space is made. An oxidizer feed inlet pipe is fastened inside the structural envelope and communicates with the annular space. The annular space communicates with the space between the cover and the injector face via ports made in the bush. The propellant space communicates with propellant passages of the mixing modules through calibrated openings made in the cover. The space between the cover and the injector face communicates with annular oxidizer passages of the mixing modules via openings. Slots are made in the injector face between housing of the mixing modules and walls of the chambers.

Gas generator for liquid propellant rockets

The invention relates to rocket engine manufacturing, and may also be used in aircraft engine manufacturing. A chamber comprises a casing, ignition means and a mixing head. The mixing head consists of an internal injector face, a middle bottom, an external bottom. Bipropellant injectors are fixed in the internal injector face and the middle bottom. A portion of the bipropellant injectors are mounted projecting from the internal injector face, while another portion are recessed in the internal injector face. The ignition means are made from jet injectors mounted in a structural casing behind the internal injector face. Axes of diverging ports of jet injectors are positioned at an acute angle to an outlet from the structural casing and deflected in a circle in a lateral plane from the longitudinal axis of the structural casing in an identical direction. The chamber casing comprises a combustion chamber and a nozzle, made from an external structural envelope and an internal fire wall. A regenerative cooling passage is positioned between the external structural envelope and the internal fire wall. A ring-like slot of a gas-screen belt is made in the internal fire wall before the nozzle throat. The regenerative cooling passage of the chamber is made with a branched inlet. One of its branches communicates with the space of the chamber regenerative cooling passage between the nozzle throat and its scarf, a second branch&mdash;with the space of the chamber regenerative cooling passage before the nozzle throat, and a third&mdash;with the space of the chamber regenerative cooling passage before the ring-like slot of the gas-screen belt.

Liquid-propellant rocket engine chamber and its casing

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. A heat exchanger, in which the gas used for rocket tank pressurization is heated, is mounted on a pipeline feeding the gas to the aforesaid gas turbine of the booster pump actuator.

Liquid-propellant rocket engine with turbine gas afterburning

The method for prodicing a multilayer thin-walled bellows of stainless steel consists of manufacturing round billets by welding the sheets, packing the round billets into a multilayer bank, corrugating the bank for forming the multilayer bellows and the bellows tightness testing. The round billets are manufactured of the preliminary cut sheets of given dimensions by their electric arc pulsed gas-shielded welding. The packed multilayer bank is welded from two sides over the end faces and subjected to heat treatment by its heating up to the temperature of 1000-1130&deg; C. in the shielding medium and holding at this temperature during 20-45 minutes with subsequent cooling.

Method for producing a multilayer thin-walled bellows of stainless steel

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. At its end on the outlet side, the pipe is provided with a balance for compensating angular displacements, for instance, a bellows balance with a cardan mechanism. The curved pipe is connected to the frame by a hinge, and its outlet end is gas-tightly connected to the bellows of the balance.

Liquid-propellant rocket engine

A combustion chamber for a liquid-propellant rocket engine includes an injector head jointed to a combustion chamber casing having an exhaust head on a nozzle output. The casing is made of a steel jacket and a bronze-steel internal fire wall, which are joined with each other and contain shells connected in series. The exhaust head with shells of the casing, jointed to the exhaust head, are brazed using a solder on the basis of nickel, chromium and manganese. Parts of the injector head and other members of the combustion chamber casing are brazed using a copper-silver solder. Shells of the fire wall are connected by an electron-beam welding, directing an electron beam into axial gaps left while brazing between shells of the jacket. The shells of the jacket are then sequentially connected by an automatic gas-shielded arc welding through corresponding ring spacers.

Method for producing a welded-brazed combustion chamber

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Khimki, Russia

Boris Ivanovich Katorgin