WO2020151608A1 - Véhicule aérien sans pilote à voilure tournante - Google Patents

Véhicule aérien sans pilote à voilure tournante Download PDF

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Publication number
WO2020151608A1
WO2020151608A1 PCT/CN2020/072912 CN2020072912W WO2020151608A1 WO 2020151608 A1 WO2020151608 A1 WO 2020151608A1 CN 2020072912 W CN2020072912 W CN 2020072912W WO 2020151608 A1 WO2020151608 A1 WO 2020151608A1
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WO
WIPO (PCT)
Prior art keywords
wing
rotary
steering
steering rod
driving
Prior art date
Application number
PCT/CN2020/072912
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English (en)
Chinese (zh)
Inventor
陈翔斌
王敏
Original Assignee
深圳市旗客智能技术有限公司
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 深圳市旗客智能技术有限公司 filed Critical 深圳市旗客智能技术有限公司
Publication of WO2020151608A1 publication Critical patent/WO2020151608A1/fr

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    • 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
    • B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors

Definitions

  • This application relates to the field of unmanned aerial vehicles, in particular to a rotary-wing unmanned aerial vehicle.
  • the lift generated by the pressure difference formed by the air flowing through the upper and lower wing surfaces allows the aircraft to use a smaller thrust engine to obtain a longer empty time.
  • fixed-wing aircraft require longer runways for takeoff and landing.
  • Fixed-wing UAVs equipped with vertical take-off and landing rotors can better solve the problem of fixed-wing UAVs requiring run-up and landing on the runway.
  • the vertical take-off and landing can be achieved by setting the drive mechanism that drives the vertical take-off and landing rotors to change the direction
  • the descending rotor is used as the driving force for level flight, but the rotors of the current drones are generally set on the left and right ends of the wing.
  • the rotor has a long wheelbase, and the flight is unstable and easy to be disturbed by natural wind. It also requires high structural strength .
  • the main purpose of this application is to propose a rotary-wing unmanned aerial vehicle, which aims to solve the problems of poor stability of the existing unmanned aerial vehicle's rotor arrangement and high requirements on the structural strength of the airframe.
  • a rotary wing unmanned aerial vehicle comprising a fixed wing body, a rotary wing mechanism, and a steering mechanism arranged in the fixed wing body;
  • the fixed wing body includes a fuselage, connected to the left and right The main wing on the side and the segmented wing connected to the free end of the main wing, the main wing and the segmented wing on each side form an accommodation space;
  • the steering mechanism includes The rotary drive assembly inside and the steering rod assembly connected with the rotary drive assembly and protruding from the free end of the main wing on each side, and the rotary drive assembly is used to drive the steering rod assembly around a Axis rotation;
  • the rotor mechanism includes a fixed bracket located in the accommodation space and connected with the steering rod assembly, a drive member arranged on the fixed bracket, and rotors respectively arranged on both ends of the fixed bracket , The driving member is connected with the rotating shaft of the rotor.
  • the steering rod assembly includes a first steering rod arranged inside the fuselage, the rotation drive assembly is connected to the middle section of the first steering rod, and both ends of the first steering rod are respectively provided with A second steering rod protruding from the free end of the main wing, and a coupling is provided between the first steering rod and the second steering rod.
  • the fixing bracket is arranged on a second steering rod, and an end of the second steering rod away from the coupling is fixedly connected to the segmented wing.
  • the main wing and the segmented wing are connected by a first connecting rod and a second connecting rod separated by a predetermined distance, and the fixing bracket is arranged on the first connecting rod and the second connecting rod In between, the second steering rod extends into the segmented wing and is rotatably connected with the segmented wing.
  • a steering gear and a third connecting rod extending from the free end of the main wing and rotatably connected to the main wing are provided in the main wing, and one end of the third connecting rod is connected to the rudder
  • the output shaft of the aircraft is connected, and the other end is fixedly connected with the segmented wing, and the steering gear is used to drive the segmented wing to turn over.
  • the rotation drive assembly includes a driven gear coaxially arranged with the first steering rod, a driving gear meshing with the driven gear, and a steering drive motor for driving the driving gear to rotate; or,
  • the rotary drive assembly includes a steering drive motor, a driving pulley connected to the output shaft of the steering drive motor, a driven pulley coaxially arranged with the first steering rod, and a driven pulley connected between the driving pulley and the driven pulley. Synchronous belt between.
  • the rotary-wing drone further includes a locking mechanism, the locking mechanism includes a locking ring sleeved on the first steering rod with an opening, and a locking ring that drives the locking ring to hug the steering rod assembly Lock the drive motor.
  • the locking mechanism includes a locking ring sleeved on the first steering rod with an opening, and a locking ring that drives the locking ring to hug the steering rod assembly Lock the drive motor.
  • the rotary drive assembly includes a worm gear coaxially arranged with the first steering rod, a worm gear adapted to the worm gear, and a steering drive motor for driving the worm gear to rotate.
  • the steering rod assembly and the fixed bracket are combined into an "H" structure
  • the rotating shafts of the rotor are parallel to each other and are arranged perpendicular to the rotating axis of the steering rod assembly
  • the driving member includes an electric motor or a fuel engine.
  • the steering rod assembly is hollowed out for passage of lines or oil circuits connecting the driving parts.
  • a symmetrical rotor mechanism is provided in the middle section of the wing of the fixed-wing body, and a steering rod assembly connected to the rotor mechanism and a rotary drive assembly that drives the steering rod assembly to drive the rotary wing mechanism to turn over are arranged inside the fuselage.
  • This power layout can enable The wing length of the aircraft reduces the wheelbase of the rotor mechanisms on the left and right sides of the aircraft while meeting the lift requirements, making the aircraft structurally stronger, and at the same time ensuring sufficient lifting power and flat flight lift, making the flight process more stable.
  • Figure 1 is a schematic structural diagram of an embodiment of a rotary-wing drone of the application
  • FIG. 2 is a schematic structural diagram of the steering mechanism in the embodiment of Figure 1;
  • FIG. 3 is a schematic structural diagram of another embodiment of a rotary-wing drone of the application.
  • Fig. 4 is a schematic diagram of the structure of the steering mechanism in the embodiment of Fig. 3.
  • the rotary-wing drone includes a fixed-wing body 10, a rotor mechanism 20, and a steering mechanism 30 arranged in the fixed-wing body 10;
  • the fixed-wing body 10 It includes a fuselage, a main wing 11 arranged on both sides of the fuselage, and a segmented wing 12 connected to the main wing 11.
  • a accommodating space for a fixed bracket 21 is formed between the main wing 11 and the segmented wing 12;
  • a steering mechanism 30 It includes a rotary drive assembly arranged in the fuselage and a steering rod assembly 31 connected to the rotary drive assembly and respectively extending from the free end of the main wing 11 on each side.
  • the rotary drive assembly is used to drive the steering rod assembly around an axis Rotation;
  • the rotor mechanism 20 includes a fixed bracket 21 respectively arranged in the middle section of the steering rod assembly 31, a driver 22 arranged at both ends of the fixed bracket 21, and a rotor connected to the output shaft of the driver 22.
  • the fixed-wing body 10 includes a fuselage, a main wing 11 arranged on both sides of the fuselage, and a segmented wing 12 connected to the main wing 11.
  • the steering mechanism 30 includes a steering rod assembly 31 that traverses the fuselage and is arranged along the extending direction of the wing.
  • the steering rod assembly 31 includes a long rod disposed across the wing.
  • a mounting seat 35 is also provided inside the fuselage.
  • the mounting seat 35 includes a fixing plate fixed inside the fuselage, two supporting plates extending upward from the fixing plate, and two supporting sleeves arranged on the two supporting plates.
  • the rod assembly 31 is rotatably connected by bearings.
  • Rotary drive components can choose gear transmission, belt transmission or worm gear transmission.
  • the driving member 22 is preferably an electric motor, a gasoline engine or a diesel engine.
  • the rotor wing is arranged on the output shaft of the driving member 22, that is, each rotor wing is driven by a motor or a fuel engine.
  • the two rotors on the same side are simultaneously driven by a fuel engine through a shaft or a timing belt. It is worth noting that the best position of the steering rod assembly 31 is to pass through the center of gravity of the airframe to slow down the overturning of the airframe when the rotor mechanism 20 adjusts the angle of rotation.
  • the steering rod assembly 31 preferably penetrates the steering rod of the fuselage, and the fixing bracket 21 is arranged in the middle section of the steering rod and distributed symmetrically with respect to the fuselage.
  • the steering rod passes through the end face of the main wing 11, the fixed bracket 21 is arranged at the end face of the steering rod close to the main wing 11, and the segmented wing 12 is arranged at the protruding end of the steering rod and is fixedly connected to the steering rod and held by the rotor shaft vertical.
  • a steering rod assembly 31 arranged across the wings of the fuselage, a rotary drive assembly for driving the steering rod assembly 31 to rotate, and a rotor mechanism 20 arranged on the steering rod assembly 31 and located in the middle section of the wing are arranged inside the fuselage.
  • the rotor assembly 20 is arranged symmetrically with respect to the fuselage and forms an "H" structure with the steering rod assembly 31.
  • the fixed-wing aircraft type attitude is adjusted by the rotating drive assembly to maintain the fuselage in a level flight attitude.
  • the wheelbase of the rotor mechanisms 20 on the left and right sides of the aircraft under this power layout is reduced.
  • the wingspan can be further increased to provide greater lift.
  • the concentration of power also makes the structure of the aircraft The intensity is higher and the level flight process is more stable.
  • the steering rod assembly 31 can also be arranged in sections, including a first steering rod 31a arranged inside the fuselage, and the rotary drive assembly is arranged in the middle section of the first steering rod 31a.
  • a second steering rod 31b is provided at both ends, and a coupling 31c is provided between the first steering rod 31a and the second steering rod 31b.
  • the steering rod assembly 31 is arranged in sections, and the two ends of the first steering rod 31a are respectively provided with the second steering rods 31b through the coupling 31c.
  • the first steering rod 31a and the second steering rod 31b A certain included angle can be maintained between them, that is, the dihedral angle to improve the lateral stability of the rotary-wing UAV during level flight.
  • the dihedral angle here is set at 6 to 8 degrees.
  • the fixing bracket 21 is arranged on the second steering rod 31b, and the end of the second steering rod 31b away from the coupling 31c is fixedly connected to the segmented wing 12.
  • the fuselage and rotor are arranged horizontally, and the segmented wing 12 is kept in a vertical state to act as a flow guide. At this time, the rotor provides lift.
  • the segmented wing 12 flips with the rotor and remains in a horizontal state to provide lift for the plane's level flight.
  • a first connecting rod 13 and a second connecting rod 14 are provided between the main wing 11 and the segmented wing 12, and the second steering rod 31b rotates with the segmented wing 12 connection.
  • the first connecting rod 13 and the second connecting rod 14 are arranged in parallel, and both ends of the first connecting rod 13 and the second connecting rod 14 are respectively connected to the main wing 11 and the segmented wing 12, and the fixing bracket 21 It is arranged between the two connecting rods and rotates in it.
  • the fixing bracket 21 is provided with two opposite bends to respectively accommodate the first connecting rod 13 and the second connecting rod 14 to avoid interference during the rotation.
  • the first connecting rod 13 and the second connecting rod 14 are provided to improve the connection strength of the entire wing.
  • the main wing 11 is provided with a steering gear whose output shaft and the wing point in the same direction, and a third connecting rod is arranged on the output shaft of the steering gear, and the third connecting rod is connected to the segmented wing,
  • the steering gear is used to drive the segmented wing to rotate.
  • the segmented wing 12 is connected to the main wing 11 only through the third connecting rod, and the steering gear can be used to drive the segmented wing to flip to increase the wind resistance and decelerate during the plane's level flight.
  • the rotation driving assembly includes a driven gear coaxially arranged with the steering rod assembly 31, a driving gear meshing with the driven gear, and a steering driving motor for driving the driving gear to rotate; or the rotation driving assembly includes a steering driving motor 34 , A driving pulley connected with the output shaft of the steering drive motor 34, a driven pulley coaxially arranged with the steering rod assembly, and a timing belt connected between the driving pulley and the driven pulley.
  • the rotary wing drone when the rotary drive assembly adopts a transmission mode without self-locking function, such as gear transmission, the rotary wing drone is also provided with a locking mechanism inside, and the locking mechanism includes the steering rod assembly 31
  • the locking ring 40 and the driving locking ring 40 lock the locking driving motor of the steering rod assembly 31.
  • the locking ring 40 is provided with an opening, and includes a locking portion sleeved on the outer wall of the steering rod assembly 31, a fixed end extending from one end of the opening and fixedly connected to the inner wall of the fuselage or the mounting seat 35, and the other end extending from the opening and connecting with Lock the locking end connected to the driving motor.
  • the locking ring 40 locks the steering rod assembly 31 to achieve locking, avoiding the rotor mechanism 20 and the body of the rotary-wing drone during flight The abnormal deflection occurs between them to ensure stable flight.
  • the rotating drive assembly includes a worm gear 32 coaxially arranged with the steering rod assembly 31 and a worm 33 adapted to the worm gear 32.
  • the worm 33 is driven by a steering drive motor 34 fixedly arranged inside the fuselage, and the worm gear 32 is located in the middle section of the steering rod assembly 31.
  • the steering drive motor 34 can drive the worm gear mechanism to operate, thereby adjusting the angle between the rotor assembly 20 and the fixed wing body. Since the worm gear mechanism has a self-locking function, a locking mechanism is not required in this embodiment to realize the overall weight reduction of the drone.
  • the fixing bracket 21 includes a mounting rod connected to the steering rod assembly 31 and mounting positions provided at both ends of the mounting rod, and the mounting positions are used to install the driving member 22.
  • the two fixed brackets 21 and the steering rod assembly 31 in the rotor mechanism 20 constitute an "H"-shaped structure, and the driving member 22 and the rotors on it are arranged at the four ends of the "H"-shaped structure.
  • the two ends of the fixing bracket 21 are provided with installation positions for installing the driver 22.
  • the symmetrical four-point distribution of the driving member 22 and the rotor provides stable lift or level flight power for the flight of the fuselage.
  • the steering rod assembly 31 is hollow and is used for the passage of the line or oil circuit connecting the driving member 22.
  • the steering rod assembly 31 and the fixing bracket 21 are hollow, and the connecting line or oil pipeline of the driving member 22 can be connected to the power supply or fuel tank inside the fuselage through the steering rod assembly 31 and the fixing bracket 21 to lower the fuselage.
  • the overall weight, wiring is simpler, easy to install and maintain.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

L'invention concerne un véhicule aérien sans pilote à voilure tournante. Le véhicule aérien sans pilote à voilure tournante comprend un corps d'aile fixe (10), des mécanismes à voilure tournante (20) et un mécanisme de direction (30) ; le corps d'aile fixe comprend un fuselage, des ailes principales (11) reliées aux côtés gauche et droit du fuselage, et des ailes segmentées (12) relié à des extrémités libres des ailes principales, un espace de logement étant formé entre l'aile principale et l'aile segmentée de chaque côté ; le mécanisme de direction (30) comprend un ensemble d'entraînement rotatif disposé dans le fuselage et des ensembles tige de direction (31) reliés à l'ensemble d'entraînement rotatif et s'étendant respectivement à partir des extrémités libres des ailes principales des deux côtés, l'ensemble d'entraînement rotatif étant utilisé pour entraîner les ensembles de tiges de direction pour tourner autour d'un axe ; les mécanismes d'ailes rotatives (20) comprennent chacun un support fixe (21) situé dans l'espace de réception et relié à l'ensemble tige de direction, un élément d'entraînement disposé sur le support fixe, et des ailes rotatives disposées respectivement au niveau de deux extrémités du support fixe, l'élément d'entraînement étant relié à des arbres rotatifs des ailes rotatives. La manière d'agencement pour les ailes rotatives du véhicule aérien sans pilote offre une bonne stabilité, et le corps a une résistance structurale élevée, de telle sorte que le processus de vol soit plus stable.
PCT/CN2020/072912 2019-01-25 2020-01-19 Véhicule aérien sans pilote à voilure tournante WO2020151608A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201920148225.X 2019-01-25
CN201920148225.XU CN209567080U (zh) 2019-01-25 2019-01-25 旋转翼无人机

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WO2020151608A1 true WO2020151608A1 (fr) 2020-07-30

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Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN209567080U (zh) * 2019-01-25 2019-11-01 深圳市旗客智能技术有限公司 旋转翼无人机
CN111874226A (zh) * 2020-07-09 2020-11-03 常州华创航空科技有限公司 一种倾转旋翼飞行器
CN113978716B (zh) * 2021-10-27 2023-11-03 广西电网有限责任公司电力科学研究院 一种翻翼式线路勘灾无人机

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CN109250101A (zh) * 2018-10-30 2019-01-22 佛山市神风航空科技有限公司 一种四轴垂直起降固定翼飞机
CN109250100A (zh) * 2018-10-30 2019-01-22 佛山市神风航空科技有限公司 一种倾转垂直起降固定翼飞机
CN209567080U (zh) * 2019-01-25 2019-11-01 深圳市旗客智能技术有限公司 旋转翼无人机

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20080035760A (ko) * 2006-10-20 2008-04-24 홍순영 세 쌍의 로터를 가진 수직이착륙기
CN106986005A (zh) * 2017-03-29 2017-07-28 北京华信智航科技有限公司 一种油动倾转旋翼飞机的倾转结构
CN107097951A (zh) * 2017-03-29 2017-08-29 北京华信智航科技有限公司 一种倾转旋翼飞机翼内传动结构
CN207106879U (zh) * 2017-08-29 2018-03-16 陕西安康领航智能股份有限公司 一种控制倾转伺服机构
CN108513557A (zh) * 2017-09-27 2018-09-07 深圳市大疆创新科技有限公司 机翼组件及无人飞行器
CN207826549U (zh) * 2018-01-26 2018-09-07 宁波云远智能科技有限公司 一种可垂直起降的无人机平台
CN208021740U (zh) * 2018-01-26 2018-10-30 易瓦特科技股份公司 用于固定翼无人机的可调式旋翼机身装置
CN208021734U (zh) * 2018-01-26 2018-10-30 易瓦特科技股份公司 用于固定翼无人机的可调式旋翼机头装置
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CN109250100A (zh) * 2018-10-30 2019-01-22 佛山市神风航空科技有限公司 一种倾转垂直起降固定翼飞机
CN209567080U (zh) * 2019-01-25 2019-11-01 深圳市旗客智能技术有限公司 旋转翼无人机

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