RU2008124930A - Complex for jet helicopter and aircraft flight - Google Patents

Complex for jet helicopter and aircraft flight Download PDF

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Publication number
RU2008124930A
RU2008124930A RU2008124930/11A RU2008124930A RU2008124930A RU 2008124930 A RU2008124930 A RU 2008124930A RU 2008124930/11 A RU2008124930/11 A RU 2008124930/11A RU 2008124930 A RU2008124930 A RU 2008124930A RU 2008124930 A RU2008124930 A RU 2008124930A
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RU
Russia
Prior art keywords
nozzles
nozzle
complex
engine
jet
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Application number
RU2008124930/11A
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Russian (ru)
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RU2387582C2 (en
Inventor
Александр Сергеевич Артамонов (RU)
Александр Сергеевич Артамонов
Евгений Александрович Артамонов (RU)
Евгений Александрович Артамонов
Original Assignee
Александр Сергеевич Артамонов (RU)
Александр Сергеевич Артамонов
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Application filed by Александр Сергеевич Артамонов (RU), Александр Сергеевич Артамонов filed Critical Александр Сергеевич Артамонов (RU)
Priority to RU2008124930/11A priority Critical patent/RU2387582C2/en
Publication of RU2008124930A publication Critical patent/RU2008124930A/en
Application granted granted Critical
Publication of RU2387582C2 publication Critical patent/RU2387582C2/en

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Abstract

1. A complex for a jet flight of a helicopter and an aircraft, comprising blocks of jet lifting and traction detonation engines rigidly fastened to each other and the fuselage, placed sequentially one after another in a bearing plane containing an air intake with deflecting plates, a marching jet detonation engine and control wheels, a system transportation and injection of hydrocarbon fuel and conductive fluid, the system of excitation of electric discharges, characterized in that each lifting and traction the engine is equipped with a receiving chamber for atmospheric air, containing a lattice with self-acting plate valves, communicating with a carrier plane diffuser connected to a damping device containing a reflector made in the form of a body pointed on one side and concave on the other to reflect shock waves, connected to the combustion chamber with an expanding nozzle connected to the working channel containing a hinged nozzle for changing the thrust vector, with the exhaust valve block located in it new to compressed air, made in the form of gratings with nozzles and plate self-acting valves, afterburning jet detonation engine and resonator nozzles placed on both sides of the working channels, the combustion chambers are equipped with combined nozzles with explosive chambers sequentially placed one after another, for injection of the mixture products of thermochemical decomposition of hydrocarbon fuels and products of electrothermal decomposition of an electrically conductive liquid, and force adjacent to them

Claims (15)

1. A complex for a jet flight of a helicopter and an aircraft, comprising blocks of jet lifting and traction detonation engines rigidly fastened to each other and the fuselage, placed sequentially one after another in a bearing plane containing an air intake with deflecting plates, a marching jet detonation engine and control wheels, a system transportation and injection of hydrocarbon fuel and conductive fluid, the system of excitation of electric discharges, characterized in that each lifting and traction the engine is equipped with a receiving chamber for atmospheric air, containing a lattice with self-acting plate valves, communicating with a carrier plane diffuser connected to a damping device containing a reflector made in the form of a body pointed on one side and concave on the other to reflect shock waves, connected to the combustion chamber with an expanding nozzle connected to the working channel containing a hinged nozzle for changing the thrust vector, with the exhaust valve block located in it new to compressed air, made in the form of gratings with nozzles and plate self-acting valves, afterburning jet detonation engine and resonator nozzles placed on both sides of the working channels, the combustion chambers are equipped with combined nozzles with explosive chambers sequentially placed one after another, for injection of the mixture products of thermochemical decomposition of hydrocarbon fuels and products of electrothermal decomposition of an electrically conductive liquid, and force adjacent to them detonators for igniting the working combustible mixture in the chambers by injecting gaseous jets of electrothermal decomposition of the electrically conductive liquid, the combined nozzles containing an outer casing with nozzles and channels for cooling with liquid, inside which cylindrical channels are placed in the layer of insulating material that communicate with the nozzles for supplying electrically conductive liquids, inside which there are screws for reflection of shock waves, nozzles are made in the channels on one side, in the direction nye at an angle to each other and communicating with the explosion chamber injector comprising a bottom with openings for exit of gas jets, and the other has electrodes connected to a generator of electric impulses.
2. The complex according to claim 1, characterized in that the detonator nozzle and the resonator nozzle contain an outer casing with an explosive chamber and channels for cooling with liquid, inside of which in the electrical insulation layer there are cylindrical channels communicating with nozzles containing screws in the channels with on the one hand nozzles are made, directed at an angle to each other and communicating with the explosive chamber of the nozzle, and on the other, electrodes are placed.
3. The complex according to claim 1, characterized in that the afterburner engine is equipped with an air intake connected to a damping device for reflecting shock waves, containing concave reflectors located at a predetermined distance from each other, communicating with a combustion chamber containing an expanding nozzle, the combustion chamber is provided combined nozzles with explosive chambers, sequentially placed one after another, for injection of a mixture of gaseous fuel and electrically conductive liquid, and adjacent forums located to them detonators for injecting gaseous jets of conductive fluid.
4. The complex according to claims 1 to 3, characterized in that the working channels are equipped with an air intake containing a grill with nozzles and plate self-acting valves, the working channel contains a nozzle with a guide vane.
5. The complex according to claims 1 to 4, characterized in that the lifting and traction motors arranged sequentially one after another in the bearing plane perpendicular to the fuselage contain an air inlet and intake chambers for atmospheric air with grilles installed in them with self-acting plate valves, the receiving chamber is lifted the traction motor is connected to a shock absorber for reflecting shock waves connected to a cylindrical transition part connected to a combustion chamber containing an expanding nozzle connected left with the working channel, combined nozzles successively mounted one after another, and detonator nozzles adjacent to them, the working channel contains a hinged nozzle for changing the thrust vector with the exhaust valve blocks for compressed air located in it, made in the form of gratings with nozzles and self-acting plate valves placed at a predetermined distance from each other, and an intake valve block for atmospheric air inlet and an afterburning jet engine.
6. The complex according to claims 1 and 5, characterized in that the receiving chamber contains rotary damper valves with sealing plates at the ends, while the valve shafts are connected to an electromechanical actuator for periodically turning them around the axes.
7. The complex according to PP.5 and 6, characterized in that the lifting and traction motors placed sequentially one after another in the carrier plane perpendicular to the fuselage, contain receiving chambers with rotary damper valves, connected to the exhaust nozzle of the turbojet engine on one side and to the expanding a nozzle connected to the working channels, on the other hand, provided with hinged nozzles for changing the thrust vector, with exhaust valve blocks for compressed air located therein at a predetermined distance from each other ha, made in the form of gratings with nozzles and plate self-acting valves, and an intake valve block for atmospheric air inlet and an afterburning jet engine.
8. The complex according to 5, characterized in that the jet engines, placed sequentially one after another in the bearing plane perpendicular to the fuselage, contain an air intake and receiving chambers with grilles installed with self-acting plate valves for air inlet, the engine receiving chamber is connected to the combustion chamber equipped with a combined nozzle and a conical transitional part connected to a long pipe containing an articulated nozzle for changing the thrust vector and a combined nozzle.
9. The complex according to claim 8, characterized in that an additional pair of cylindrical channels with nozzles and electrodes connected to an electric pulse generator of a combined nozzle is placed in the layer of insulating material.
10. The complex according to claim 9, characterized in that the mid-flight jet engine comprises a housing equipped with a nozzle and a diffuser, with a pointed body located therein adjacent to a compressor connected to combustion chambers with combined nozzles for injecting a gaseous mixture of products thermochemical decomposition of hydrocarbon fuel and electrochemical decomposition of conductive fluid and adjacent nozzles for igniting the working mixture, equipped with expanding nozzles, Combined with long cylinders of wave compressors connected to a guide device of a gas turbine containing a bandage with high-pressure fan blades located on it, the turbine communicates with an elongated nozzle containing an afterburner with a guide cone in it, combined nozzles arranged uniformly around the circumference for injection mixtures of gaseous jets of hydrocarbon fuel with an electrically conductive liquid and ignition of this mixture with air and nozzles-resonator In order to reduce engine noise, direct-flow jet detonation engines are located on the engine casing, comprising a casing with a combustion chamber equipped with combined nozzles sequentially mounted one after the other, and opposite them with detonator nozzles and a Laval nozzle on one side and a diffuser with a reflector placed in it made with a pointed body, on the other hand.
11. The complex according to claim 10, characterized in that the ramjet engine is equipped with a damping device containing a reflective body with a reflective concave surface, on the one hand connected to the combustion chamber, and on the other with a cylindrical transition part connected to a damping device containing multi-hop diffuser with a reflector equipped with a pointed body.
12. The complex according to claims 2 and 10, characterized in that the explosive chamber of the nozzle contains a bottom with openings for the exit of jets of gaseous products of electrothermal decomposition of the electrically conductive liquid and ignition of the workforce.
13. The complex according to claims 1 and 2, characterized in that the marching jet detonation engine comprises a housing provided with a nozzle and a diffuser, with a pointed body placed therein adjacent to a compressor connected to damping devices containing a reflector made in the form of a body, sharpened on one side and concave on the other, to reflect shock waves, connected to cylindrical transitional parts and combustion chambers containing combined nozzles sequentially mounted one after another and opposite but their placed detonator nozzles, combustion chambers are connected to conical or expanding nozzles connected to long cylinders of wave compressors containing deaf reflective surfaces at the ends and connected to a gas manifold of combustion products and a gas turbine containing a bandage with high-pressure fan blades located on it, the turbine communicates with the afterburner with the combined nozzles located in it, arranged uniformly around the circumference, nozzles for igniting the mixture and nozzles-resonators.
14. The complex according to claims 1, 2, 10 and 13, characterized in that the marching jet detonation engine comprises a housing provided with a nozzle and a diffuser, with a pointed body located therein, adjacent to a fan located on one shaft with a compressor connected to the damping devices connected to cylindrical transitional parts and combustion chambers containing combined nozzles sequentially installed one after another and oppositely placed detonator nozzles and conical or expanding nozzles, connected to long cylinders of wave compressors, containing deaf reflecting surfaces at the ends, and connected to a gas manifold of combustion products and a gas turbine in communication with a nozzle with a cone and resonator nozzles arranged uniformly around the circumference, a ramjet detonation engine is placed in the housing, containing combustion chambers with combined nozzles mounted on them, sequentially installed one after another, and the nozzle opposite them mi detonators and Laval nozzles, combustion chambers are connected to cylindrical transitional parts and damping devices that communicate with diffusers placed on the engine casing uniformly around the circumference.
15. The complex according to any one of paragraphs, characterized in that the main jet engine comprises an electric motor located in a fairing, connected to a fan and a compressor connected to damping devices connected in series, connected to cylindrical transition parts and combustion chambers equipped with combined nozzles sequentially installed one after another, and opposite to them detonator nozzles and expanding nozzles with external magnets located on them by means and electrodes of the magnetohydrodynamic generator, the expanding nozzles communicate with the traction nozzle with resonator nozzles placed therein, coaxially located with the nozzle of the housing, while the electric motor is connected to the magnetohydrodynamic generator.
RU2008124930/11A 2008-06-18 2008-06-18 Complex for reactive flight RU2387582C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2008124930/11A RU2387582C2 (en) 2008-06-18 2008-06-18 Complex for reactive flight

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2008124930/11A RU2387582C2 (en) 2008-06-18 2008-06-18 Complex for reactive flight

Publications (2)

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RU2008124930A true RU2008124930A (en) 2009-12-27
RU2387582C2 RU2387582C2 (en) 2010-04-27

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RU2008124930/11A RU2387582C2 (en) 2008-06-18 2008-06-18 Complex for reactive flight

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Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2383515B1 (en) * 2010-04-28 2013-06-19 Siemens Aktiengesellschaft Combustion system for dampening such a combustion system
RU2443608C2 (en) * 2010-11-26 2012-02-27 Александр Михайлович Гультяев Rocket
RU2572366C2 (en) * 2014-03-18 2016-01-10 Публичное акционерное Общество "Таганрогский авиационный научно-технический комплекс им. Г.М. Бериева" (ПАО "ТАНТК им. Г.М. Бериева") Shipborne and ground-based lower radar signature aircraft with all around antenna system
RU2546385C1 (en) * 2014-05-19 2015-04-10 Александр Сергеевич Артамонов Vtol aircraft

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