WO2017166316A1 - Dispositif de verrouillage, hélice, moteur, transmission et véhicule aérien sans pilote - Google Patents

Dispositif de verrouillage, hélice, moteur, transmission et véhicule aérien sans pilote Download PDF

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Publication number
WO2017166316A1
WO2017166316A1 PCT/CN2016/078382 CN2016078382W WO2017166316A1 WO 2017166316 A1 WO2017166316 A1 WO 2017166316A1 CN 2016078382 W CN2016078382 W CN 2016078382W WO 2017166316 A1 WO2017166316 A1 WO 2017166316A1
Authority
WO
WIPO (PCT)
Prior art keywords
motor
propeller
driving member
driving
elastic member
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/CN2016/078382
Other languages
English (en)
Chinese (zh)
Inventor
赵喜峰
王平
贝世猛
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
SZ DJI Technology Co Ltd
Original Assignee
SZ DJI Technology Co Ltd
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 SZ DJI Technology Co Ltd filed Critical SZ DJI Technology Co Ltd
Priority to CN201680002466.2A priority Critical patent/CN107074368B/zh
Priority to CN201811289068.0A priority patent/CN109383817B/zh
Priority to PCT/CN2016/078382 priority patent/WO2017166316A1/fr
Publication of WO2017166316A1 publication Critical patent/WO2017166316A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/20—Transmission of mechanical power to rotors or propellers
    • B64U50/23—Transmission of mechanical power to rotors or propellers with each propulsion means having an individual motor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B64C27/14—Direct drive between power plant and rotor hub
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
    • H02P7/00—Arrangements for regulating or controlling the speed or torque of electric DC motors

Definitions

  • controller mounted on the body, the controller being electrically connected to the motor
  • the driving member 30 abuts the latching portion 12 to engage the latching portion 12 with the engaging portion 21, and the first body 10 and the second body 20 are relatively locked.
  • the latching portion 12 is disengaged from the mating portion 21 so that the first body 10 and the second body 20 are relatively detachable.
  • the driving member 30 is pressed at a preset position by using the axial elastic member 50.
  • the driving member 30 can be pressed at the position where the avoiding portion 32 and the holding portion 12 are aligned in the unlocked state. Keeping the position of the driving member 30 from swaying, such that when the second body 20 is assembled to the first body 10, and before the mating portion 21 of the second body 20 is aligned with the engaging portion 12 of the first body 10, The relief portion 32 can always be aligned with the catch portion 12 such that the catch portion 12 can be reliably held by the second body 20 into the escape portion 32 before switching to the locked state.
  • the top surface of the mounting protrusion 111 may be provided with a groove, and the second body 20 can be inserted into the groove; the engaging portion 21 can be specifically disposed in the groove of the second body 20 facing the groove.
  • a through hole for receiving the holding portion 12 may be formed in the groove wall of the groove, and the thickness of the groove wall may be smaller than a dimension in the moving direction of the holding portion 12, for example, when the holding portion 12 is a rigid ball The thickness of the groove wall may be smaller than the diameter of the rigid ball.
  • the hub Before the hub is mounted on the motor, the hub is not required due to the need to prevent the blocking of the latch 12
  • the method is mounted on the motor. Therefore, before the hub is installed, the latching portion 12 cannot protrude from the outer side of the motor.
  • the operator can operate the driving member 30 such that the avoiding portion 32 and the latching portion 12 of the driving member 30 Aligning to provide a escaping space for the accommodating portion 12, so that the hub can be fitted to the outside of the motor, and after the hub is fitted to the motor, the position of the driving member 30 is adjusted, so that the driving member 30 can abut the holding portion 12.
  • the catching portion 12 enters the engaging portion 21 on the hub, and the engaging portion 12 is engaged with the engaging portion 21, thereby ensuring reliable locking between the motor and the hub.
  • a top cover 112 may be disposed on the top of the mounting protrusion 111.
  • the top cover 112 is formed with an opening, and the connecting portion 302 is disposed through the opening, and the top cover 112 is used to limit the maximum limit position of the drive member 30 relative to the motor.
  • the driving member 30 is also operated such that the catching portion 12 is moved into the relief portion 32 of the driving member 30, and then the motor and the hub can be disengaged.
  • the propeller of the embodiment has a simple structure, reliable locking, and convenient disassembly and assembly.
  • the driving member 30 may include a guiding portion 301 and a connecting portion 302 formed on the top of the guiding portion 301.
  • the outer side surface of the guiding portion 301 may cooperate with the inner cavity of the mounting convex portion 111, and is guided.
  • the outer surface of the segment 301 is provided with a relief portion 32, and the relief portion 32 can accommodate the latch portion 12.
  • the outer side surface of the guiding section 301 can cooperate with the inner side wall of the inner cavity of the mounting convex portion 111, and the driving member 30 is linearly moved under the guidance of the inner side wall of the mounting convex portion 111.
  • the inner side wall of the mounting groove 251 and the outer side wall of the driving member 30 are matched with a slope, that is, the inner side surface of the mounting groove 251 is inclined from the outer end to the inner end from the bottom end to the top end, and correspondingly, the driving member 30 is also A guide surface that cooperates with the slope of the mounting groove 251 is opened. Thereby, the driving member 30 can be smoothly moved in a predetermined direction under the guidance of the inclined surface, and the operator can operate relatively smoothly.
  • the locking between the motor and the propeller is completed.
  • the driving member 30 is also operated such that the catching portion 12 is moved into the relief portion 32 of the driving member 30, and then the motor and the propeller are detached.
  • the motor of the embodiment has a simple structure and can be reliably locked to the propeller, and the disassembly and assembly between the two is convenient.
  • the driving member 30 is pressed at a preset position by using the axial elastic member 50.
  • the driving member 30 can be pressed at the position where the avoiding portion 32 and the holding portion 12 are aligned in the unlocked state.
  • the position of the driving member 30 is kept free from swaying, so that when the other of the propeller and the motor is assembled to one of the propeller and the motor, and on the other of the propeller and the mating portion 21 of the motor and the propeller and the motor Before the latching portion 12 is aligned, the relief portion 32 can always be aligned with the latching portion 12 such that the latching portion 12 can be reliably held by the other of the propeller and the motor into the avoiding portion 32 before switching to the locked state. .
  • the connecting section 302 can protrude from the mounting boss 111 to provide an operating position for operator operation. Specifically, the operator can drive the sliding of the driving member 30 by operating the connecting section 302.
  • one of the propeller and the motor includes a first positioning surface 14 facing the propeller and the other of the motor, and the propeller and the motor are further
  • the second positioning surface 23 is disposed on the first positioning surface 14
  • the second positioning portion 22 is a groove formed on the second positioning surface 23 .
  • the first positioning portion is a groove formed on the first positioning surface
  • the second positioning portion is a protrusion formed on the second positioning surface, and the protruding column is engaged with the protrusion. In the groove.
  • the driving member 30 abuts against the latching portion 12 such that the latching portion 12 engages with the engaging portion 21, and the motor and the propeller are relatively locked.
  • the catching portion 12 is disengaged from the engaging portion 21 to relatively disengage the motor from the propeller.
  • the catching portion 12 and the relief portion 32 are always aligned, and the driving end 31 relieves the latching portion 12.
  • the driving member 30 slides with respect to one of the propeller and the motor, the latching portion 12 can be disengaged from the relief portion 32 and enter the mating portion 21 under the abutment of the driving end 31 to switch to the locked state.
  • the present embodiment is based on any of the above embodiments from the seventy-ninth embodiment to the ninety-sixth embodiment. Please refer to FIG. 1 or FIG. 4 or FIG. 7. Further, the propeller and the motor are disposed on the same axis, the propeller or the motor. Rotate around the central axis. A first positioning portion 13 is disposed on one of the propeller and the motor, and the second positioning portion 22 is engaged with the first positioning portion 13 on the other of the propeller and the motor. The second positioning portion 22 and the first positioning portion 13 are locked. The state is connected so that the propeller and the motor rotate together around the central axis.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Remote Sensing (AREA)
  • Power Engineering (AREA)
  • Toys (AREA)
  • Lock And Its Accessories (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

L'invention concerne un dispositif de verrouillage, comprenant : un loquet (12), qui peut être disposé mobile sur un premier corps (10) ; une partie d'ajustement (21), qui est disposée sur un second corps (20), étant apte à être ajustée avec le loquet (12) ou séparée de celui-ci ; un élément d'entraînement (30) qui peut être disposé coulissant sur le premier corps (10), apte à coulisser par rapport au premier corps (10) afin d'entrer dans un état verrouillé ou un état déverrouillé. Dans l'état verrouillé, l'élément d'entraînement (30) est en butée contre le loquet (12), le loquet (12) est ajusté avec la partie d'ajustement (21) et le premier corps (10) est verrouillé par rapport au second corps (20) ; et dans l'état déverrouillé, le loquet (12) est séparé de la partie d'ajustement (21) et le premier corps (10) peut être séparé par rapport au second corps (20). Le premier corps (10) est un moteur et le second corps (20) est une hélice ; ou le premier corps (10) est une hélice et le second corps (20) est un moteur.
PCT/CN2016/078382 2016-04-01 2016-04-01 Dispositif de verrouillage, hélice, moteur, transmission et véhicule aérien sans pilote Ceased WO2017166316A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
CN201680002466.2A CN107074368B (zh) 2016-04-01 2016-04-01 锁定装置、螺旋桨、电机、动力套装及无人飞行器
CN201811289068.0A CN109383817B (zh) 2016-04-01 2016-04-01 锁定装置、螺旋桨、电机、动力套装及无人飞行器
PCT/CN2016/078382 WO2017166316A1 (fr) 2016-04-01 2016-04-01 Dispositif de verrouillage, hélice, moteur, transmission et véhicule aérien sans pilote

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2016/078382 WO2017166316A1 (fr) 2016-04-01 2016-04-01 Dispositif de verrouillage, hélice, moteur, transmission et véhicule aérien sans pilote

Publications (1)

Publication Number Publication Date
WO2017166316A1 true WO2017166316A1 (fr) 2017-10-05

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2016/078382 Ceased WO2017166316A1 (fr) 2016-04-01 2016-04-01 Dispositif de verrouillage, hélice, moteur, transmission et véhicule aérien sans pilote

Country Status (2)

Country Link
CN (2) CN109383817B (fr)
WO (1) WO2017166316A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107585290A (zh) * 2017-08-18 2018-01-16 广州极飞科技有限公司 桨叶固定结构及无人机
CN108438200A (zh) * 2018-05-11 2018-08-24 南京航天猎鹰飞行器技术有限公司 一种可快速拆装机翼的固定翼无人机
CN111332456A (zh) * 2020-04-14 2020-06-26 北京远度互联科技有限公司 一种固锁结构和无人机
CN112109890A (zh) * 2019-06-22 2020-12-22 咸宁市天意模型科技有限公司 一种用于无人机的折叠桨夹驱动组件
CN114906315A (zh) * 2022-05-19 2022-08-16 亿维特(南京)航空科技有限公司 一种用于推进螺旋桨的可拆卸安装结构
CN116106216A (zh) * 2021-11-10 2023-05-12 北京鉴知技术有限公司 光谱仪用压样装置
CN116588329A (zh) * 2023-06-28 2023-08-15 浙江都尔特轮车业有限公司 纯电驱动的多桨动力滑翔机
CN117922818A (zh) * 2024-02-26 2024-04-26 南昌三瑞智能科技股份有限公司 一种折叠桨机构及飞行器

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CN209274912U (zh) * 2018-11-30 2019-08-20 深圳市大疆创新科技有限公司 舵机及无人机
CN109279038A (zh) * 2018-11-30 2019-01-29 上海歌尔泰克机器人有限公司 无人机快拆机构和无人机
EP3760539B1 (fr) 2019-06-26 2021-09-29 LEONARDO S.p.A. Rotor anticouple pour hélicoptère
WO2021003609A1 (fr) * 2019-07-05 2021-01-14 深圳市大疆创新科技有限公司 Ensemble de puissance et véhicule aérien sans pilote
CN112119009A (zh) * 2019-08-01 2020-12-22 深圳市大疆创新科技有限公司 锁定结构、螺旋桨、动力装置、动力组件和无人机
CN111516443B (zh) * 2020-05-08 2021-07-13 中国人民解放军陆军炮兵防空兵学院 一种中空轮多旋翼飞行车
CN119262368B (zh) * 2024-12-11 2025-03-25 深圳市好盈科技股份有限公司 一种桨叶的快拆装置及无人机

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CN204956901U (zh) * 2015-08-18 2016-01-13 王军 一种螺旋桨连接结构及无人机
CN205499336U (zh) * 2016-04-01 2016-08-24 深圳市大疆创新科技有限公司 螺旋桨、电机、动力套装及无人飞行器

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CN202185744U (zh) * 2011-07-19 2012-04-11 晟进科技股份有限公司 治夹具的联结闭锁装置
CN204210728U (zh) * 2014-11-04 2015-03-18 深圳市大疆创新科技有限公司 锁定机构,具有锁定机构的螺旋桨及飞行器
CN204279920U (zh) * 2014-11-04 2015-04-22 深圳市大疆创新科技有限公司 锁定机构,具有锁定机构的螺旋桨及飞行器
CN105492316A (zh) * 2014-11-04 2016-04-13 深圳市大疆创新科技有限公司 锁定机构，具有锁定机构的螺旋桨及飞行器
CN105517892A (zh) * 2014-11-04 2016-04-20 深圳市大疆创新科技有限公司 锁定机构，具有锁定机构的螺旋桨及飞行器
CN205602090U (zh) * 2016-04-01 2016-09-28 深圳市大疆创新科技有限公司 螺旋桨、电机、动力套装及无人飞行器

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107585290A (zh) * 2017-08-18 2018-01-16 广州极飞科技有限公司 桨叶固定结构及无人机
CN108438200A (zh) * 2018-05-11 2018-08-24 南京航天猎鹰飞行器技术有限公司 一种可快速拆装机翼的固定翼无人机
CN112109890A (zh) * 2019-06-22 2020-12-22 咸宁市天意模型科技有限公司 一种用于无人机的折叠桨夹驱动组件
CN111332456A (zh) * 2020-04-14 2020-06-26 北京远度互联科技有限公司 一种固锁结构和无人机
CN116106216A (zh) * 2021-11-10 2023-05-12 北京鉴知技术有限公司 光谱仪用压样装置
CN114906315A (zh) * 2022-05-19 2022-08-16 亿维特(南京)航空科技有限公司 一种用于推进螺旋桨的可拆卸安装结构
CN116588329A (zh) * 2023-06-28 2023-08-15 浙江都尔特轮车业有限公司 纯电驱动的多桨动力滑翔机
CN117922818A (zh) * 2024-02-26 2024-04-26 南昌三瑞智能科技股份有限公司 一种折叠桨机构及飞行器

Also Published As

Publication number Publication date
CN109383817B (zh) 2021-09-07
CN109383817A (zh) 2019-02-26
CN107074368A (zh) 2017-08-18
CN107074368B (zh) 2019-01-08

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