WO2021035631A1 - Élément à desserrage rapide, ensemble hélice, et véhicule aérien sans pilote à rotors multiples - Google Patents

Élément à desserrage rapide, ensemble hélice, et véhicule aérien sans pilote à rotors multiples Download PDF

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Publication number
WO2021035631A1
WO2021035631A1 PCT/CN2019/103376 CN2019103376W WO2021035631A1 WO 2021035631 A1 WO2021035631 A1 WO 2021035631A1 CN 2019103376 W CN2019103376 W CN 2019103376W WO 2021035631 A1 WO2021035631 A1 WO 2021035631A1
Authority
WO
WIPO (PCT)
Prior art keywords
mounting
propeller
locking
propeller assembly
assembly according
Prior art date
Application number
PCT/CN2019/103376
Other languages
English (en)
Chinese (zh)
Inventor
谢旻钊
Original Assignee
深圳市大疆创新科技有限公司
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 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Priority to PCT/CN2019/103376 priority Critical patent/WO2021035631A1/fr
Priority to CN201980031414.1A priority patent/CN112119010A/zh
Publication of WO2021035631A1 publication Critical patent/WO2021035631A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts

Definitions

  • the present invention is implemented through the following technical solutions:
  • the locking mechanism includes a main body part and a locking part, the main body part is connected with the driving mechanism, and the main body part is provided with a receiving space, and the locking part is at least partially located in the receiving space;
  • Drive mechanism including drive shaft;
  • the drive shaft is connected to the propeller through the quick release component.
  • the propeller assembly is connected to an end of the arm away from the fuselage.
  • a propeller assembly comprising:
  • the propeller includes a hub, blades connected to the side wall of the hub, and a mounting portion provided at the bottom of the hub, the hub is provided with a first mounting hole, and the bottom surface of the hub is a flat surface Structure;
  • the driving mechanism includes a power device and a locking mechanism provided on the power device, the power device includes a drive shaft, the drive shaft passes through the locking mechanism and is fixedly connected to the first mounting hole;
  • a multi-rotor unmanned aerial vehicle comprising:
  • the first propeller assembly is one of a forward propeller and a reverse propeller
  • the second propeller assembly is the other of a forward propeller and a reverse propeller
  • the present invention connects the propeller and the driving mechanism through a quick release, and the user can realize the detachable connection of the propeller and the driving mechanism through a single rotation operation, and the operation is convenient and the structure is simple.
  • Fig. 1 is a schematic structural diagram of a first propeller assembly in an embodiment of the present invention
  • FIG. 3 is a schematic view showing the structure of the first propeller assembly in another direction in an embodiment of the present invention.
  • FIG. 4 is a schematic structural diagram of the first propeller of the first propeller assembly in an embodiment of the present invention.
  • FIG. 5D is a schematic structural diagram of another part of FIG. 5A;
  • Figure 8 is a schematic structural view of a second locking mechanism of a second propeller assembly in an embodiment of the present invention.
  • 330 quick release parts; 1: mounting part; 11: adapter part; 12: clamping part; 2: locking mechanism; 21: main body part; 211: receiving space; 212: mounting slot; 2121: first mounting slot; 2122: second mounting groove; 22: locking part; 221: clamping groove; 2211: opening part; 2212: stop part; 222: limit part; 23: connecting part; 231: second mounting hole; 24: prevention Wrong installation structure; 241: fixed part; 2411: third mounting hole; 242: wrong installation block; 25: second protrusion.
  • the driving mechanism 320 of this embodiment may include a power device, and the power device includes a drive shaft 321.
  • the power device is a motor, and the locking mechanism 2 is fixedly connected to the housing of the motor.
  • the power device can also choose other power mechanisms, not limited to motors.
  • the propeller 310 and the driving mechanism 320 are connected through the quick-release member 330, and the user can realize the detachable connection of the propeller 310 and the driving mechanism 320 through a single rotation operation, and the operation is convenient and the structure is simple.
  • the fitting manner of the mounting portion 1 and the locking portion 22 can be designed according to requirements, for example, the fitting can be performed by means of snap connection, plug connection, or the like.
  • the locking portion 22 may include a locking groove 221, and the locking groove 221 is provided in the receiving space 211. With the relative rotation of the mounting portion 1 and the clamping groove 221, the mounting portion 1 enters the clamping groove 221 to cooperate with the clamping groove 221 or moves out of the clamping groove 221 to separate from the clamping groove 221, correspondingly to make the installation portion 1
  • the lock portion 22 is in a locked position or an unlocked position.
  • the hub 311 of this embodiment is provided with a first mounting hole 3111, and the drive shaft 321 is fixedly fitted with the first mounting hole 3111 through a quick-release member 330.
  • an elastic part is provided on the driving shaft 321, and the elastic part is press-fitted with the first mounting hole 3111 to realize a stable connection between the driving shaft 321 and the propeller hub 311.
  • connecting portion 23 can be detachably connected to the housing of a power device such as a motor by a connecting member such as screws, so as to connect the locking mechanism 2 to the power device.
  • the adapter portion 11 and the clamping portion 12 are arranged vertically.
  • the angle between the adapter portion 11 and the clamping portion 12 can also be other angles.
  • the number of the mounting parts 1 is equal to the number of the locking parts 22, and the mounting parts 1 and the locking parts 22 are matched correspondingly.
  • both the mounting part 1 and the locking part 22 include one.
  • each of the mounting portion 1 and the locking portion 22 includes multiple, such as two, the multiple mounting portions 1 are arranged at intervals along the same circumference, and the multiple mounting portions 1 surround the first mounting hole 3111, which is designed in this way, The installation part 1 and the locking mechanism 2 are installed more firmly, which can effectively prevent the risk of propeller shooting.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Snaps, Bayonet Connections, Set Pins, And Snap Rings (AREA)

Abstract

La présente invention concerne un élément à desserrage rapide (330), un ensemble hélice (300) et un véhicule aérien sans pilote à rotors multiples. L'élément à desserrage rapide est utilisé pour monter de manière amovible une hélice (310) sur un mécanisme d'entraînement (320). L'élément à desserrage rapide comprend une partie de montage (1) raccordée à et formée sur l'un ou l'autre parmi l'hélice et le mécanisme d'entraînement, et un mécanisme de verrouillage (2) formé sur ou raccordé à l'autre parmi l'hélice et le mécanisme d'entraînement. Le mécanisme de verrouillage comprend une partie corps principal (21) et une partie de verrouillage (22). La partie corps principal est raccordée au mécanisme d'entraînement. La partie corps principal présente un espace de réception (211). La partie de verrouillage est au moins partiellement située dans l'espace de réception. La partie de montage est logée dans l'espace de réception, et se met en rotation par rapport à la partie de verrouillage dans l'espace de réception, de telle sorte qu'une commutation entre une position verrouillée et une position déverrouillée est effectuée sur la partie de montage et la partie de verrouillage, et une commutation correspondante entre un état verrouillé et un état déverrouillé est effectuée sur l'hélice et le mécanisme d'entraînement. La présente invention permet à un utilisateur de mettre en œuvre un raccordement détachable entre l'hélice et le mécanisme d'entraînement au moyen d'une seule opération de rotation, et est facile à utiliser.
PCT/CN2019/103376 2019-08-29 2019-08-29 Élément à desserrage rapide, ensemble hélice, et véhicule aérien sans pilote à rotors multiples WO2021035631A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/CN2019/103376 WO2021035631A1 (fr) 2019-08-29 2019-08-29 Élément à desserrage rapide, ensemble hélice, et véhicule aérien sans pilote à rotors multiples
CN201980031414.1A CN112119010A (zh) 2019-08-29 2019-08-29 快拆件、螺旋桨组件及多旋翼无人飞行器

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2019/103376 WO2021035631A1 (fr) 2019-08-29 2019-08-29 Élément à desserrage rapide, ensemble hélice, et véhicule aérien sans pilote à rotors multiples

Publications (1)

Publication Number Publication Date
WO2021035631A1 true WO2021035631A1 (fr) 2021-03-04

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Application Number Title Priority Date Filing Date
PCT/CN2019/103376 WO2021035631A1 (fr) 2019-08-29 2019-08-29 Élément à desserrage rapide, ensemble hélice, et véhicule aérien sans pilote à rotors multiples

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CN (1) CN112119010A (fr)
WO (1) WO2021035631A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20210024204A1 (en) * 2019-10-29 2021-01-28 SZ DJI Technology Co., Ltd. Rotor mount assembly
CN114701643A (zh) * 2021-12-20 2022-07-05 中国航天空气动力技术研究院 一种快速装拆桨叶的螺旋桨装置

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2022236820A1 (fr) * 2021-05-14 2022-11-17 深圳市大疆创新科技有限公司 Hélice, appareil électrique, système électrique, et véhicule aérien sans pilote

Citations (5)

* Cited by examiner, † Cited by third party
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CN104986330A (zh) * 2015-06-29 2015-10-21 深圳一电科技有限公司 桨臂连接组件及飞行器
CN205469777U (zh) * 2016-01-11 2016-08-17 优利科技有限公司 飞行器
CN207242034U (zh) * 2017-09-08 2018-04-17 亿航智能设备（广州）有限公司 一种具有快速锁定功能的螺旋桨组件
CN109018308A (zh) * 2018-08-09 2018-12-18 上海歌尔泰克机器人有限公司 一种螺旋桨快拆装置及具有其的无人机
WO2019056756A1 (fr) * 2017-09-21 2019-03-28 深圳市道通智能航空技术有限公司 Hélice, ensemble d'alimentation et véhicule aérien sans pilote

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Publication number Priority date Publication date Assignee Title
CN206218221U (zh) * 2016-10-28 2017-06-06 深圳市大疆创新科技有限公司 锁定机构、螺旋桨、电机、动力系统组件及飞行器
WO2018094669A1 (fr) * 2016-11-24 2018-05-31 深圳市大疆创新科技有限公司 Mécanisme de verrouillage d'hélice, hélice, moteur, unité d'alimentation et véhicule aérien sans pilote
CN206664924U (zh) * 2016-12-14 2017-11-24 深圳市道通智能航空技术有限公司 飞行器及其螺旋桨快拆装置、螺旋桨、螺旋桨底座组件
CN208530841U (zh) * 2018-07-06 2019-02-22 广州极飞科技有限公司 旋翼组件和飞行器

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104986330A (zh) * 2015-06-29 2015-10-21 深圳一电科技有限公司 桨臂连接组件及飞行器
CN205469777U (zh) * 2016-01-11 2016-08-17 优利科技有限公司 飞行器
CN207242034U (zh) * 2017-09-08 2018-04-17 亿航智能设备（广州）有限公司 一种具有快速锁定功能的螺旋桨组件
WO2019056756A1 (fr) * 2017-09-21 2019-03-28 深圳市道通智能航空技术有限公司 Hélice, ensemble d'alimentation et véhicule aérien sans pilote
CN109018308A (zh) * 2018-08-09 2018-12-18 上海歌尔泰克机器人有限公司 一种螺旋桨快拆装置及具有其的无人机

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20210024204A1 (en) * 2019-10-29 2021-01-28 SZ DJI Technology Co., Ltd. Rotor mount assembly
CN114701643A (zh) * 2021-12-20 2022-07-05 中国航天空气动力技术研究院 一种快速装拆桨叶的螺旋桨装置

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Publication number Publication date
CN112119010A (zh) 2020-12-22

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