WO2014088443A1 - Hélicoptère coaxial à grande vitesse - Google Patents

Hélicoptère coaxial à grande vitesse Download PDF

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Publication number
WO2014088443A1
WO2014088443A1 PCT/RU2012/001015 RU2012001015W WO2014088443A1 WO 2014088443 A1 WO2014088443 A1 WO 2014088443A1 RU 2012001015 W RU2012001015 W RU 2012001015W WO 2014088443 A1 WO2014088443 A1 WO 2014088443A1
Authority
WO
WIPO (PCT)
Prior art keywords
speed
helicopter
column
coaxial
coaxial high
Prior art date
Application number
PCT/RU2012/001015
Other languages
English (en)
Russian (ru)
Inventor
Михаил Андреевич МАМЫКИН
Original Assignee
КОЛЕСНИК, Яков Александрович
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by КОЛЕСНИК, Яков Александрович filed Critical КОЛЕСНИК, Яков Александрович
Priority to PCT/RU2012/001015 priority Critical patent/WO2014088443A1/fr
Publication of WO2014088443A1 publication Critical patent/WO2014088443A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B64C27/10—Helicopters with two or more rotors arranged coaxially
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/52—Tilting of rotor bodily relative to fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8236—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft including pusher propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
    • B64C2027/8272—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising fins, or movable rudders
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
    • B64C2027/8281—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising horizontal tail planes

Definitions

  • the invention relates to aeronautical engineering, in particular to the device of coaxial helicopters.
  • the speed characteristics of such a helicopter are achieved by distributing the lifting force between the main rotor and the aerodynamic surface (wing), and the higher the speed, the larger the share under the main rotor is the wing, thereby reducing the harmful effect of the asymmetry of the flow around the rotor.
  • the rotor speed decreases in proportion to the increase in speed and singing.
  • a drawback of the described construction is that in the high-speed flight mode, the main rotor 1 will create a part of the lifting force and, when ⁇ , will not create thrust, i.e. in fact, it acts as the main rotor of a gyroplane, creating harmful resistance greater than an ordinary wing of the same area.
  • flow asymmetry still requires compensation and steering surfaces (at least), which complicates the control system and requires special pilot training or mandatory autopilot.
  • the closest analogue to the proposed technical solution is a high-speed pine helicopter using the rotor aerodynamics according to the ABC (Advancing Blade Concept) Sikorsky Demonstrator X2
  • particle / 3274 comprising a fuselage, an engine, a coaxial synchronized rotor with a common pitch control and a cyclic pitch of the blades, a pushing screw with a common pitch control, surfaces for stabilization and maneuvering.
  • the problem of asymmetry of enveloping is almost completely solved by the use of a coaxial synchronized screw with a rigid fastening of the blades to the hub.
  • the design of such a helicopter is simpler than that of a hybrid helicopter, and the speed characteristics are higher - Sikorsky Demonstrator X2 is the officially registered record holder for speed and flight among helicopters.
  • the disadvantage of the design of the Sikorsky helicopter is 1 paoo ia of the main rotor at high speed in the emergency mode, i.e. the main rotor will create lifting force, and the horizontal thrust will be created by the pushing screw located in the tail of the top of the center.
  • General efficiency ver goal ⁇ a remains not high, for a flight with the same speed, a plane with classical aerodynamics will require much less energy.
  • the problem is to create izobrs 1eiiya For the construction soospogo fast) Nogo Ver toleta capable of vertical takeoff and vissshpo, skorosshom ⁇ y horizontal flight and thus with low energy tightened on rat s flight.
  • an coaxial high-speed helicopter containing the fuselage, an engine, a system of coaxial synchronized rotors with the ability to control the common and cyclic pitch, pushing the propeller with an axis located horizontally and with the ability to control the pitch of the screw a, and aerodynamic surfaces for stabilization and control are characterized in that they have a tilt mechanism for the rotor system and a helicopter stabilization system.
  • the tilt mechanism of the rotor system consists of a column with a gearbox and is controlled by the tilt drive of the column.
  • the column of the rotor system is hinged to the fuselage.
  • the tilt range of the rotor system column is 90 ° -70 ° relative to the horizontal axis of the verte.
  • the column tilt drive is electromechanical or pneumatic or hydraulic.
  • the helicopter stabilization system contains mechanical and electronic (autopilot) parts.
  • the control mechanism for the installation angle of the horizontal tail (GO) is made electromechanical or pneumatic or hydraulic.
  • the engine can be a piston or turbojet (turboshaft) internal combustion engine, or electric.
  • Figure 1 shows a helicopter indicating the main nodes; figure 2 system of rotors with a column tilt mechanism; figure 3 vector diagrams of the speeds and forces that occur when flowing around the profile of the rotor blade.
  • Coaxial high-speed helicopter contains (Fig. 1) the fuselage 1, on which the rotor system 2 is hinged, consisting of a column 3 (Fig. 2), synchronized coaxial rotors 4 with rigid fastening of the blades and with the ability to control the common and cyclic pitch of the blades, however, column 3 contains a gearbox 5 and coaxial shafts 6.
  • column 3 contains a gearbox 5 and coaxial shafts 6.
  • a horizontal tail 7 and a vertical tail 8 movably connected to the fuselage 1 and equipped with rudders of height 9 and direction 10, as well as a mechanism for controlling the angle of installation of GO 1 1.
  • the device operates as follows.
  • the engine 12 which is fixedly mounted in the fuselage 1, transmits power through an intermediate gearbox 13 and a transmission 14 pa to the rotor system 2, and through a transmission 15 to the tail propeller 16.
  • the intermediate gearbox 13 is configured to proportionally redistribute the power of the engine 12 between the rotor system 2 and tail propeller 16.
  • the rotation of the rotors 4 is synchronized in the gearbox 5 and is carried out using coaxial shafts 6.
  • the transmission to the main gearbox 14 contains a joint Nirni shafts connected with the possibility neredachi powerful in any angular position under the column 3.
  • the column tilt actuator 17 serves to change the angle of inclination of the column 3 and the mechanical linkage 19 connected to the horizontal tail 7.
  • the control mechanism for the installation angle GO 11 is connected with the horizontal tail 7, on the one hand, and the tilt drive of the column 17, on the other hand, and serves for additional balancing correction (trimming).
  • the column 3 of the rotors In take-off and viscepia mode, the column 3 of the rotors is located vertically or has a minimum forward inclination angle of ⁇ 86-90 °.
  • the rotor system 2 works like a regular system of co-operating helicopters, to ensure stability and controllability, the common and cyclic pitch of the rotor is used, the steering surfaces of 7.8 are ineffective in this mode.
  • the energy of the engine spent on unwinding the screws can be conditionally divided into two flows: the creation of lifting force (useful use) and the swirling of the air flow below the screw (energy loss), while the OJ effective efficiency will be in the region of 0.5-0.7 units.
  • the engine power required for the flight is reduced compared to the power required for the Wissner, and excess power is used to rotate the pushing screw 16 located at the rear of the fuselage to increase flight speed.
  • Pa figure 3 shows a vector diagram of the velocities and forces arising from the flow around the profile of the rotor blade when moving along the azimuth ⁇ circle described in the intervals 0-180 ° and 180-360 °.
  • V (i is the vector of translational speed and helicopter
  • ⁇ V is the vector of the true velocity of the oncoming flow
  • ⁇ is the vector of the induced velocity
  • R is the total aerodynamic force of the profile of the blade
  • Y is the lifting force of the profile in the speed coordinate system of the blade; Yi- profile lifting force in a high-speed coordinate system 1 of the helicopter; X - profile drag force in the speed coordinate system and blades;
  • P is the thrust vector in the speed coordinate system of the helicopter
  • a is the angle of attack of the profile
  • ⁇ is the angle of the blade relative to the plane of rotation.
  • the axis of rotation of the coaxial screw must be inclined at a certain angle with respect to the horizontal velocity vector of the helicopter. This angle is also about 90 ° (the axis of rotation of the screw is almost vertical), the vector of the resulting aerodynamic force in the azimuthal section 0-180 ° will receive an up-and-down direction, which is typical for the operation of the screw in normal mode and the maximum relative 1D will be around 0, 5-0.7 units.
  • the range of inclination of the axis of rotation of the propeller is optimal in the range of 78-70 ° ( ⁇ ⁇ " 78-70 °) for the speed range of 250-400 km / h.
  • the efficiency reaches a maximum of 0.92-0.95 at flight speeds 220-350 km / h and gradually decreases to values of 0.75-0.8 with an immediate speed of 350-400 km / h.
  • the proposed coaxial * high-speed verulet due to the possibility of adjusting the angle of inclination of the rotor system, allows one to obtain high speed characteristics combined with low energy consumption in flight due to the improved aerodynamics of the carrier system.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transmission Devices (AREA)
  • Toys (AREA)

Abstract

L'invention se rapporte au domaine de l'aéronautique, et concerne notamment un dispositif pour hélicoptères à système coaxial. Cet hélicoptère coaxial à grande vitesse comprend un fuselage, un moteur, un système de d'hélices portantes synchronisées coaxiales pouvant être commandées par le pas global et cyclique, une hélice aérienne de poussée avec un axe disposé horizontalement et capable de commander la pas de l'hélice, et des surfaces aérodynamiques pour la stabilisation et la commande, ainsi qu'un mécanisme d'inclinaison du système d'hélices portantes et un système de stabilisation de l'hélicoptère.
PCT/RU2012/001015 2012-12-04 2012-12-04 Hélicoptère coaxial à grande vitesse WO2014088443A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/RU2012/001015 WO2014088443A1 (fr) 2012-12-04 2012-12-04 Hélicoptère coaxial à grande vitesse

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/RU2012/001015 WO2014088443A1 (fr) 2012-12-04 2012-12-04 Hélicoptère coaxial à grande vitesse

Publications (1)

Publication Number Publication Date
WO2014088443A1 true WO2014088443A1 (fr) 2014-06-12

Family

ID=50883756

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU2012/001015 WO2014088443A1 (fr) 2012-12-04 2012-12-04 Hélicoptère coaxial à grande vitesse

Country Status (1)

Country Link
WO (1) WO2014088443A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190329878A1 (en) * 2018-04-30 2019-10-31 Bell Helicopter Textron Inc. Transmission mount
CN112373686A (zh) * 2020-11-26 2021-02-19 尚良仲毅(沈阳)高新科技有限公司 一种无人机及其矢量角度控制方法
CN112441216A (zh) * 2020-11-26 2021-03-05 广东国士健科技发展有限公司 一种人电混合驱动的平拍翼飞行器
CN112572812A (zh) * 2020-11-26 2021-03-30 广东国士健科技发展有限公司 一种双层旋翼同向同速转动的飞行器
US11834164B2 (en) 2020-05-18 2023-12-05 Iqinetics Technologies Inc. Pulse-induced cyclic control lift propeller

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040075017A1 (en) * 2002-06-12 2004-04-22 Thomas Sash Control of an aircraft as a thrust-vectored pendulum in vertical, horizontal and all flight transitional modes thereof
RU2324626C1 (ru) * 2006-07-24 2008-05-20 Леонид Петрович Шингель Безопасный самолет вертикального взлета и посадки
RU2370414C1 (ru) * 2008-02-11 2009-10-20 Дмитрий Сергеевич Дуров Многоцелевой дистанционно пилотируемый вертолет-самолет

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040075017A1 (en) * 2002-06-12 2004-04-22 Thomas Sash Control of an aircraft as a thrust-vectored pendulum in vertical, horizontal and all flight transitional modes thereof
RU2324626C1 (ru) * 2006-07-24 2008-05-20 Леонид Петрович Шингель Безопасный самолет вертикального взлета и посадки
RU2370414C1 (ru) * 2008-02-11 2009-10-20 Дмитрий Сергеевич Дуров Многоцелевой дистанционно пилотируемый вертолет-самолет

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
S. APRESOV.: "V pogone za skorostiu: vertolet s tolkaiushchim vintom.", August 2008 (2008-08-01), Retrieved from the Internet <URL:http://www.popmech.ru/articte/3624-v-pogone-za-skorostyu/>> *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190329878A1 (en) * 2018-04-30 2019-10-31 Bell Helicopter Textron Inc. Transmission mount
US10940944B2 (en) * 2018-04-30 2021-03-09 Textron Innovations Inc. Transmission mount
US11834164B2 (en) 2020-05-18 2023-12-05 Iqinetics Technologies Inc. Pulse-induced cyclic control lift propeller
CN112373686A (zh) * 2020-11-26 2021-02-19 尚良仲毅(沈阳)高新科技有限公司 一种无人机及其矢量角度控制方法
CN112441216A (zh) * 2020-11-26 2021-03-05 广东国士健科技发展有限公司 一种人电混合驱动的平拍翼飞行器
CN112572812A (zh) * 2020-11-26 2021-03-30 广东国士健科技发展有限公司 一种双层旋翼同向同速转动的飞行器
CN112373686B (zh) * 2020-11-26 2022-07-08 尚良仲毅(沈阳)高新科技有限公司 一种无人机及其矢量角度控制方法

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