WO2018232787A1 - Véhicule aérien sans pilote à voilure fixe à décollage et atterrissage verticaux - Google Patents

Véhicule aérien sans pilote à voilure fixe à décollage et atterrissage verticaux Download PDF

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Publication number
WO2018232787A1
WO2018232787A1 PCT/CN2017/091952 CN2017091952W WO2018232787A1 WO 2018232787 A1 WO2018232787 A1 WO 2018232787A1 CN 2017091952 W CN2017091952 W CN 2017091952W WO 2018232787 A1 WO2018232787 A1 WO 2018232787A1
Authority
WO
WIPO (PCT)
Prior art keywords
wing
fixed
fuselage
auxiliary
motor
Prior art date
Application number
PCT/CN2017/091952
Other languages
English (en)
Chinese (zh)
Inventor
鲍静云
范晋红
王威
殷兰兰
Original Assignee
深圳市龙云创新航空科技有限公司
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 深圳市龙云创新航空科技有限公司 filed Critical 深圳市龙云创新航空科技有限公司
Publication of WO2018232787A1 publication Critical patent/WO2018232787A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
    • 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
    • B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/50—Foldable or collapsible UAVs

Definitions

  • the invention belongs to the technical field of fixed-wing drones, and in particular relates to a vertical take-off and landing fixed-wing drone.
  • UAVs on the market are generally divided into fixed-wing UAVs and multi-axis without Man-machine.
  • the fixed-wing UAV has the advantages of high efficiency, heavy load, long air time and fast flight speed, but its requirements for landing and landing sites are very strict, which makes its application severely limited by the site; multi-axis UAVs take off and land
  • the requirements of the site are not high, and the control is convenient, the hovering can be fixed at a fixed point, the vertical take-off and landing can be taken off and landing in a small space, but the efficiency is low, the load is small, and the flying speed is compared to the fixed-wing drone. slow.
  • a vertical take-off and landing fixed-wing UAV is introduced on the market, combining the advantages of fixed-wing UAVs and multi-axis UAVs, which not only ensures the flight performance of the UAV, but also solves the limitation of the landing site.
  • the problem, but this type of drone often simply superimposes the fixed-wing UAV and the multi-axis UAV, uses the relevant structure of the multi-axis UAV for vertical take-off and landing, and converts to fixed after take-off.
  • the wing flight mode in this way, its multi-axis propeller is directly exposed, resulting in very large flight resistance, resulting in a large increase in the energy consumption of the drone, and the corresponding flight time and maximum flight speed are also significantly reduced.
  • the propeller exposure leads to its The increase in volume seriously affects its appearance, and the packaging volume and transportation cost also increase significantly.
  • the technical problem to be solved by the present invention is to provide a vertical take-off and landing fixed-wing UAV that can be accommodated by an auxiliary wing.
  • a vertical takeoff and landing drone comprising a fuselage, a wing fixed on the fuselage, and a tail wing fixed to the tail of the fuselage. Further comprising two pairs of auxiliary wings, the two pairs of auxiliary wings are rotatably disposed at side ends of the fuselage, and two pairs of the auxiliary wings are respectively disposed on the front end and the rear of the fuselage relative to the wing. The pair of auxiliary wings are symmetrically disposed on two sides of the fuselage, and the airframe is provided with a receiving slot corresponding to the two pairs of auxiliary wing positions for receiving the 2 when the fixed wing is flying. For the slats.
  • the auxiliary wing comprises an arm, a retracting frame, a motor and a lifting wing
  • the receiving frame is fixed at one end of the arm
  • the motor is fixed on the arm At the other end
  • the lifting wing is fixed to the motor
  • the arm is fixed to a motor mount at one end of the motor, and the motor is fixed on the motor mount.
  • the number of the accommodating grooves is two, and each of the accommodating grooves can simultaneously accommodate two of the auxiliary wings on one side of the fuselage.
  • a pair of the auxiliary wings located at the front end of the wing have their lifting wings fixed at the upper end or the lower end of the arm, correspondingly, a pair of the rear end of the wing
  • a pair of T-shaped slots communicating with the accommodating slots are defined in a side surface of the fuselage, and two T-shaped slots are respectively disposed at upper and lower ends of the accommodating slots to receive the 2 auxiliary wings at the front and rear ends of the wing.
  • the front end fixed wing mechanism fixed to the front end of the fuselage is further included.
  • the front end fixed wing mechanism includes a front end motor base, a front end motor and a front end fixed wing, the front end motor base is fixed to the front end of the fuselage, and the front end motor is fixed to the front end On the motor base, the front end fixed wing is rotatably coupled to the output shaft of the front end motor to provide power to fly.
  • the empennage includes a horizontal empennage and a vertical empennage, and the horizontal empennage is horizontally and symmetrically fixed on both sides of the tail end of the fuselage, and the vertical empennage is fixed in a vertical direction. Used for the tail end of the fuselage.
  • the vertical take-off and landing fixed-wing UAV of the present invention has two pairs of auxiliary wings fixed at two ends of the fuselage, two pairs of auxiliary wings can be rotated relative to the fuselage, and two ends of the fuselage corresponding to two pairs of auxiliary wing positions are respectively opened.
  • the two pairs of auxiliary wings can be rotated into the accommodating groove with respect to the fuselage, thereby solving a series of technical problems caused by the exposure of the auxiliary wing in the prior art, and the vertical take-off and landing fixing of the present invention is fixed.
  • the winged drone has the advantages of convenient storage and deployment of the auxiliary wing, good flight performance and convenient packaging and transportation.
  • FIG. 1 is a schematic view showing the overall structure of a vertical take-off and landing fixed-wing UAV of the present invention
  • Figure 2 is a front elevational view of the vertical take-off and landing fixed-wing UAV of the present invention
  • Figure 3 is a side view of the shaft of the vertical take-off and landing fixed-wing UAV of the present invention
  • FIG. 4 is a schematic view showing the split structure of the removal body of the present invention.
  • Figure 5 is a schematic structural view of an auxiliary wing of the present invention.
  • FIG. 6 is a schematic structural view of the deployment of the auxiliary wing when the body is removed according to the present invention.
  • Fig. 7 is a schematic view showing the structure of the auxiliary wing when the body is removed according to the present invention.
  • the vertical take-off and landing fixed-wing UAV of the present invention includes a fuselage 1, a wing 2, a tail wing and an auxiliary wing 3.
  • the wing 2 is fixed on the fuselage 1 near the front end position, and the tail fin is fixed at the tail end of the fuselage 1.
  • the fuselage 1, the wing 2 and the tail wing constitute a main structure of the vertical take-off and landing fixed-wing UAV.
  • the number of the auxiliary wings 3 is two pairs, and the two pairs of auxiliary wings 3 are symmetric with respect to both sides of the fuselage 1, and one pair of auxiliary wings 3 are disposed at the front end of the wing 1 and the other pair of auxiliary wings 3
  • the auxiliary wing 3 is rotatably disposed on the body 1, and the pair of auxiliary wings 3 are rotatable relative to the body 1 in a direction perpendicular to the body 1, for vertical take-off and landing, and converted into a fixed
  • the pair of auxiliary wings 3 are rotated relative to the body 1 to be parallel to the longitudinal direction of the body 1, so as to accommodate the two pairs of auxiliary wings 3.
  • the auxiliary wing 3 is exposed, and the accommodating groove 10 is opened at the position corresponding to the auxiliary wing 3 on both sides of the fuselage 1.
  • the auxiliary wing 3 can be rotated relative to the body 1
  • the inside of the groove 10 is placed to accommodate the auxiliary wing 3 into the inside of the accommodating groove 10, and the exposure of the auxiliary wing 3 is avoided.
  • the two ends of the accommodating groove 10 are respectively disposed corresponding to the positions of the two auxiliary wings 3 at the front end and the rear end of the wing 2, so that the two auxiliary wings 3 are accommodated in the same accommodating groove 10.
  • the main structure of the vertical take-off and landing fixed-wing UAV of the present invention is a bracket 4, and the upper end of the bracket 4 is fixed by adding an aerodynamic outer casing to the outside of the bracket 4.
  • the wing connecting frame 40 is provided to realize the fixed connection of the wing 2, and the auxiliary wing connecting frame 41 is fixed on both sides thereof, and is fixedly connected to the auxiliary wing 3 through the auxiliary wing connecting frame 41.
  • the auxiliary wing 3 includes an arm 30, a retracting frame 31, a motor 32 and a lifting wing 33, and the retracting frame 31 is fixed at one end of the arm 30, and the auxiliary wing The other end of the 3 is fixed with a motor 32.
  • the lifting wing 33 is rotatably connected to the output end of the motor 32.
  • the receiving frame 31 is fixed at the end of the receiving slot 10, and is fixedly connected with the auxiliary wing connecting frame 41.
  • the rack 31 can control the rotation of the auxiliary wing 3 to expand or receive the auxiliary wing 3 in the accommodating groove 10.
  • the arm 30 is fixed to the motor base 34 at one end thereof for mounting the motor 32, and the motor 32 is fixed on the motor base 34.
  • the two auxiliary wings 3 located at the front end of the wing 2 have their lifting wings 33 disposed at the upper or lower end of the arm 30 in the vertical direction of the body 1, correspondingly, two auxiliary devices located at the rear end of the wing 2.
  • the wing 3 has its lifting wing 33 disposed at the lower end or the upper end of the arm 30 in the vertical direction of the body 1.
  • the front and rear end lifting wings 33 of the wing 2 are staggered in the vertical direction of the body 1, in the auxiliary wing 3
  • the lifting wings 33 are staggered at the same position in the receiving slot 10, which effectively saves space for the receiving slots 10.
  • the T-shaped groove 11 communicating with the accommodating groove 10 is further disposed on the side surface of the body 1.
  • the T-shaped grooves 11 are respectively disposed on the upper and lower sides of the accommodating groove 10, and are accommodated in the auxiliary wing 3 When accommodating the inside of the groove 10, the T-shaped grooves 11 on the upper and lower sides are respectively used for accommodating the two lifting wings 33.
  • the vertical take-off and landing fixed-wing UAV of the present invention further includes a front end fixed wing mechanism fixed to the front end of the fuselage 1, and the front end fixed wing mechanism includes a front end fixed wing 12,
  • the front end motor 13 and the front motor base 14 are fixed at the front end position of the body 1.
  • the front end motor 13 is fixed on the front motor base, and the front fixed wing 12 is rotatably connected to the output shaft of the front end motor.
  • the front end of the vertical take-off and landing fixed-wing UAV it has a power source to make it more efficient.
  • the tail fin includes a vertical tail fin 15 and a horizontal tail fin 16, and the vertical tail fin 15 is fixed to the tail end of the fuselage 1 in the vertical direction of the fuselage 1, and the horizontal tail fin 16 is symmetrically fixed on the machine in the horizontal direction of the fuselage 1. Both sides of the tail end of the body 1 have a better balance of the vertical take-off and landing fixed-wing drone through the vertical tail 15 and the horizontal tail 16.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)

Abstract

L'invention concerne un véhicule aérien sans pilote à voilure fixe qui décolle et atterrit verticalement, comprenant un corps (1), une aile (2) disposée à demeure sur le corps (1) et un empennage disposé à demeure au niveau de la queue du corps (1), et comprenant en outre deux paires d'ailes auxiliaires (3), les deux paires d'ailes auxiliaires (3) étant disposées mobiles en rotation au niveau d'extrémités latérales du corps (1), les deux paires d'ailes auxiliaires (3) étant respectivement disposées au niveau d'une extrémité avant et d'une extrémité arrière, par rapport à l'aile (2), du corps (1), chaque paire des ailes auxiliaires (3) étant disposée symétriquement des deux côtés du corps (1), et des rainures de réception (10) servant à recevoir les deux paires d'ailes auxiliaires (3) lorsqu'une voilure fixe est en vol étant ménagées aux positions correspondant aux deux paires d'ailes auxiliaires (3), sur le corps (1). Le véhicule aérien sans pilote qui décolle et atterrit verticalement présente l'avantage d'une mise en place et d'un déploiement pratiques des ailes auxiliaires (3), a une bonne performance de vol et est pratique à emballer et à transporter.
PCT/CN2017/091952 2017-06-19 2017-07-06 Véhicule aérien sans pilote à voilure fixe à décollage et atterrissage verticaux WO2018232787A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201720715781.1 2017-06-19
CN201720715781.1U CN206984353U (zh) 2017-06-19 2017-06-19 一种垂直起降固定翼无人机

Publications (1)

Publication Number Publication Date
WO2018232787A1 true WO2018232787A1 (fr) 2018-12-27

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PCT/CN2017/091952 WO2018232787A1 (fr) 2017-06-19 2017-07-06 Véhicule aérien sans pilote à voilure fixe à décollage et atterrissage verticaux

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CN (1) CN206984353U (fr)
WO (1) WO2018232787A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4244133A4 (fr) * 2020-11-13 2024-04-10 Innovaero Technologies Pty Ltd Engins volants

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109515705A (zh) * 2018-11-20 2019-03-26 西安爱生无人机技术有限公司 一种垂直起降的无人机
US11305872B2 (en) * 2019-07-29 2022-04-19 Aurora Flight Sciences Corporation Retractable propulsor assemblies for vertical take-off and landing (VTOL) aircraft
CN112027075B (zh) * 2020-09-15 2022-04-29 惠州众合航空科技有限公司 用于无人机的垂直升降机翼
CN115520384B (zh) * 2022-11-28 2023-02-03 成都睿铂科技有限责任公司 一种垂直起降固定翼无人机

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9120560B1 (en) * 2011-10-13 2015-09-01 Latitude Engineering, LLC Vertical take-off and landing aircraft
CN106081060A (zh) * 2016-07-05 2016-11-09 北京航空航天大学 一种垂直起降复合布局无人机旋翼收放装置
CN106672232A (zh) * 2017-03-02 2017-05-17 北京天宇新超航空科技有限公司 一种高效垂直起降飞行器
CN106809394A (zh) * 2017-03-10 2017-06-09 佛山市神风航空科技有限公司 一种飞机的起降系统及方法

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9120560B1 (en) * 2011-10-13 2015-09-01 Latitude Engineering, LLC Vertical take-off and landing aircraft
CN106081060A (zh) * 2016-07-05 2016-11-09 北京航空航天大学 一种垂直起降复合布局无人机旋翼收放装置
CN106672232A (zh) * 2017-03-02 2017-05-17 北京天宇新超航空科技有限公司 一种高效垂直起降飞行器
CN106809394A (zh) * 2017-03-10 2017-06-09 佛山市神风航空科技有限公司 一种飞机的起降系统及方法

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4244133A4 (fr) * 2020-11-13 2024-04-10 Innovaero Technologies Pty Ltd Engins volants

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