WO2017028501A1 - Structure de liaison d'hélice et véhicule aérien sans pilote - Google Patents

Structure de liaison d'hélice et véhicule aérien sans pilote Download PDF

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Publication number
WO2017028501A1
WO2017028501A1 PCT/CN2016/072731 CN2016072731W WO2017028501A1 WO 2017028501 A1 WO2017028501 A1 WO 2017028501A1 CN 2016072731 W CN2016072731 W CN 2016072731W WO 2017028501 A1 WO2017028501 A1 WO 2017028501A1
Authority
WO
WIPO (PCT)
Prior art keywords
propeller
connecting portion
groove
connection structure
hole
Prior art date
Application number
PCT/CN2016/072731
Other languages
English (en)
Chinese (zh)
Inventor
王军
Original Assignee
深圳曼塔智能科技有限公司
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 深圳曼塔智能科技有限公司 filed Critical 深圳曼塔智能科技有限公司
Publication of WO2017028501A1 publication Critical patent/WO2017028501A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H23/00—Transmitting power from propulsion power plant to propulsive elements
    • B63H23/32—Other parts
    • B63H23/34—Propeller shafts; Paddle-wheel shafts; Attachment of propellers on shafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/02—Hub construction

Definitions

  • the utility model belongs to the technical field of flying devices, and particularly relates to a propeller connecting structure and a drone.
  • the UAV propeller generally uses a screw connection between the nut and the rotor shaft of the motor to press the propeller, but this method requires the tool to be tightened, and the installation is not in place to cause the nut to vibrate loosely. The possibility is not conducive to the operator's safe use of drones.
  • the object of the present invention is to overcome the above-mentioned deficiencies of the prior art, and to provide a propeller connection structure capable of canceling the vibration loosening force generated by the high-speed rotation of the motor rotor and enabling quick installation and disassembly.
  • the utility model is realized by: providing a propeller connection structure, comprising a motor rotor casing and a propeller, wherein the motor rotor casing is provided with a connecting portion for connecting the propeller, and the propeller crucible is provided with a through hole matched with the connecting portion and a groove at a first angle with the through hole and for preventing the connecting portion from being disengaged from the propeller, the outer sleeve of the connecting portion is provided for being elastically compressed in the mounting propeller
  • the elastic mechanism that freely turns the connecting portion and abuts the groove in the elastic recovery ⁇ .
  • the connecting portion includes a first connecting portion disposed at an end of the motor rotor casing near the propeller, rotatably disposed on the first connecting portion, and configured to be engaged in the a second connecting portion in the recess, and an annular portion disposed around the first connecting portion and the second connecting portion and having an inner side wall for abutting on the outer side wall of the propeller at the mounting weir.
  • the elastic mechanism includes a spring and a spacer that are sequentially sleeved on the first connecting portion, and a fixing member that is disposed on the second connecting portion and that fixes the spring.
  • an inner sidewall of the through hole is formed with an annular limiting portion that abuts against the gasket and is used to press the spring.
  • the second connecting portion is T-shaped, and the groove is a first groove and a second groove disposed on two sides of the through hole and communicating with the through hole, The second connecting portion includes a vertical portion connected to the first connecting portion and a horizontal portion at which both ends abut in the first groove and the second groove, respectively.
  • the fixing member is a serpentine meson.
  • the first angle is 90 degrees.
  • the present invention also provides a drone, including the propeller connection structure described above.
  • the propeller connecting structure of the utility model is matched with the groove of the propeller through the connecting portion on the rotor shell of the motor so that the propeller can follow the high-speed rotation of the rotor of the motor, and the propeller is fixed on the connecting portion by the elastic mechanism, and the elastic
  • the mechanism can offset the loose force generated by the high-speed rotation of the motor rotor; in addition, the quick installation and disassembly of the propeller can be achieved by providing the elastic mechanism and the groove.
  • FIG. 1 is an exploded view of a propeller connection structure provided by an embodiment of the present invention
  • FIG. 2 is a plan view of a propeller connection structure according to an embodiment of the present invention.
  • Figure 3 is a cross-sectional view taken along the line in Figure 2;
  • FIG. 4 is an enlarged view of a C area in FIG. 3;
  • FIG. 5 is a cross-sectional view taken along line B in FIG. 2.
  • a propeller connection structure provided by an embodiment of the present invention includes a motor rotor casing 1, a propeller 2, and an elastic mechanism 3.
  • the elastic mechanism 3 is disposed on the rotor housing 1 of the motor and is used to detachably connect the propeller 2 to the rotor housing 1 of the motor.
  • a connection portion 11 for connecting the propeller 2 is provided on the motor rotor casing 1.
  • a through hole 21 and a recess 22 are provided in the center of the propeller 2.
  • the through hole 21 is matched with the connecting portion 11 so that the connecting portion 11 can extend, the groove 22 has a first angle with the through hole 21, and the connecting portion 11 is disengaged from the propeller 2, that is, the connecting portion 11 is inserted.
  • the through hole 21 is then rotated by a first angle to abut against the recess 22.
  • the elastic mechanism 3 is sleeved outside the connecting portion 11, and is used for elastically compressing the mounting propeller 2, so that the connecting portion 11 is freely steered and abuts against the recess 22 in the elastic recovery.
  • the groove 22 is brought into contact with the connecting portion 11 when the connecting portion 11 is aligned with the groove 22, and the propeller 2 can be fixed by this.
  • the propeller connection structure of the present invention is matched with the groove 22 of the propeller 2 through the connecting portion 11 on the rotor housing 1 of the motor so that the propeller 2 can follow the high speed rotation of the motor rotor, and the propeller 2 is fixed to the connecting portion 11 by the elastic mechanism 3.
  • the elastic mechanism 3 can cancel the loose force generated by the high-speed rotation of the motor rotor; in addition, by providing the elastic mechanism 3 and the groove 22, the rapid installation and disassembly of the propeller 2 can be realized.
  • the connecting portion 11 includes a first connecting portion 111, a second connecting portion 112, and an annular portion 113.
  • the first connecting portion 111 is disposed at one end of the rotor housing 1 of the motor near the propeller 2
  • the second connecting portion 112 is disposed at an end of the first connecting portion 111 away from the rotor housing 1 of the motor, and is rotatable relative to the first connecting portion 111.
  • the second connecting portion 112 is also used to mount the cassette in the recess 22.
  • the annular portion 113 is disposed around the first connecting portion 111 and the second connecting portion 112, and is mounted with its inner side wall abutting on the outer side wall of the propeller 2. [0024] Further, in conjunction with FIG.
  • the elastic mechanism 3 includes a spring 31, a spacer 32, and a fixing member 33.
  • the spring 31 and the spacer 32 are sequentially sleeved on the first connecting portion 111, and the fixing member 33 is disposed on the second connecting portion 112 and is used for fixing the spring 31.
  • an annular groove for placing the fixing member 33 is disposed at an end of the second connecting portion 112 adjacent to the first connecting portion 111.
  • annular stopper portion 211 is formed on the inner side wall of the through hole 21, and the annular stopper portion 211 abuts against the gasket 32 at the mounting jaw and is used to press the spring 31.
  • the second connecting portion 112 is T-shaped, and the second connecting portion 112 includes a vertical portion connected to the first connecting portion 111 and The vertical part of the vertical part.
  • the groove 22 is a first groove 221 and a second groove 222 which are disposed on both sides of the through hole 21 and communicate with the through hole 21. Further, both ends of the horizontal portion abut against the first groove 221 and the second groove 222, respectively.
  • the second connecting portion 112 can also be of other shapes as long as it can be rotated and clamped in the recess 22 for the purpose of fixing the propeller 2. And the shape of the groove 22 also changes according to the change in the shape of the second connecting portion 112.
  • the fixing member 33 is an E-shaped meson.
  • the first angle is 90 degrees.
  • the present invention also provides a drone, including the propeller connection structure described above.
  • the propeller connection structure and the drone of the present invention are implemented, and the connecting portion 11 on the rotor housing 1 of the motor cooperates with the groove 22 of the propeller 2 so that the propeller 2 can follow the rotor speed of the motor.
  • the elastic mechanism 3 can cancel the loose force generated by the high-speed rotation of the motor rotor; in addition, by providing the elastic mechanisms 3 and 22, the rapid installation and disassembly of the propeller 2 can be realized. .

Landscapes

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

Abstract

L'invention concerne une structure de liaison d'hélice et un véhicule aérien sans pilote. La structure de liaison comprend une coque de rotor de moteur (1) et une hélice (2). La coque de rotor de moteur (1) comprend une partie de liaison (11) pour relier l'hélice (2). L'hélice (2) comprend un trou traversant (21) monté avec la partie de liaison (11), et une rainure (22) pour empêcher la partie de liaison (11) d'être détachée de l'hélice (2), un premier angle étant formé entre le trou traversant (21) et la rainure (22). Un mécanisme élastique (3) est emmanché à l'extérieur de la partie de liaison (11), le mécanisme élastique (3) étant, lorsque l'hélice (2) est installée, comprimé élastiquement pour permettre à la partie de liaison (11) de tourner librement et venant en butée contre la rainure (22) lorsqu'il est rappelé élastiquement. La partie de liaison (11) sur la coque de rotor de moteur (1) est montée avec la rainure (22) de l'hélice (2) pour permettre à l'hélice (2) de tourner à une grande vitesse avec un rotor de moteur, l'hélice (2) est fixée à la partie de liaison (11) au moyen du mécanisme élastique (3), et le mécanisme élastique (3) peut annuler une force de desserrage générée par la rotation à grande vitesse du rotor de moteur, en obtenant ainsi une installation et un détachement rapide de l'hélice (2).
PCT/CN2016/072731 2015-08-18 2016-01-29 Structure de liaison d'hélice et véhicule aérien sans pilote WO2017028501A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201520623224.8 2015-08-18
CN201520623224.8U CN204956901U (zh) 2015-08-18 2015-08-18 一种螺旋桨连接结构及无人机

Publications (1)

Publication Number Publication Date
WO2017028501A1 true WO2017028501A1 (fr) 2017-02-23

Family

ID=55051982

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2016/072731 WO2017028501A1 (fr) 2015-08-18 2016-01-29 Structure de liaison d'hélice et véhicule aérien sans pilote

Country Status (2)

Country Link
CN (1) CN204956901U (fr)
WO (1) WO2017028501A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NO20170379A1 (en) * 2017-03-14 2018-09-17 FLIR Unmanned Aerial Systems AS Quick Release Rotor Attachment

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN204956901U (zh) * 2015-08-18 2016-01-13 王军 一种螺旋桨连接结构及无人机
CN204956919U (zh) * 2015-08-18 2016-01-13 王军 一种螺旋桨连接结构及无人机
WO2017166316A1 (fr) * 2016-04-01 2017-10-05 深圳市大疆创新科技有限公司 Dispositif de verrouillage, hélice, moteur, transmission et véhicule aérien sans pilote
CN105711815B (zh) * 2016-04-20 2018-08-14 曾治蛟 一种螺旋桨快速拆装自锁机构
CN105799916B (zh) * 2016-06-05 2017-10-03 吴敏 互嵌式快开桨座
WO2018039994A1 (fr) * 2016-08-31 2018-03-08 深圳市大疆创新科技有限公司 Dispositif d'entrainement, hélice et système d'alimentation
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
CN106741856A (zh) * 2017-01-17 2017-05-31 东莞市银燕电气科技有限公司 一种桨叶的快速拆装结构
CN106672210B (zh) * 2017-02-21 2023-09-05 上海未来伙伴机器人有限公司 一种快拆桨及采用其的无人机
CN107585290B (zh) * 2017-08-18 2019-09-27 广州极飞科技有限公司 桨叶固定结构及无人机
WO2020232585A1 (fr) * 2019-05-17 2020-11-26 深圳市大疆创新科技有限公司 Ensemble de raccordement à libération rapide, ensemble d'alimentation, kit d'alimentation et véhicule aérien sans pilote

Citations (7)

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Publication number Priority date Publication date Assignee Title
US4642057A (en) * 1983-12-19 1987-02-10 Brunswick Corporation Shock absorbing propeller
CN202219088U (zh) * 2011-08-25 2012-05-16 汕头市雅得塑胶玩具有限公司 一种玩具飞机的螺旋桨连接结构
CN202896873U (zh) * 2012-11-08 2013-04-24 广州金海航空技术有限公司 一种螺旋桨快速拆装结构
CN203714173U (zh) * 2013-09-24 2014-07-16 广州供电局有限公司 螺旋桨安装座
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
CN204279899U (zh) * 2014-11-10 2015-04-22 深圳市大疆创新科技有限公司 驱动装置、螺旋桨及动力系统
CN204956901U (zh) * 2015-08-18 2016-01-13 王军 一种螺旋桨连接结构及无人机

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4642057A (en) * 1983-12-19 1987-02-10 Brunswick Corporation Shock absorbing propeller
CN202219088U (zh) * 2011-08-25 2012-05-16 汕头市雅得塑胶玩具有限公司 一种玩具飞机的螺旋桨连接结构
CN202896873U (zh) * 2012-11-08 2013-04-24 广州金海航空技术有限公司 一种螺旋桨快速拆装结构
CN203714173U (zh) * 2013-09-24 2014-07-16 广州供电局有限公司 螺旋桨安装座
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
CN204279899U (zh) * 2014-11-10 2015-04-22 深圳市大疆创新科技有限公司 驱动装置、螺旋桨及动力系统
CN204956901U (zh) * 2015-08-18 2016-01-13 王军 一种螺旋桨连接结构及无人机

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NO20170379A1 (en) * 2017-03-14 2018-09-17 FLIR Unmanned Aerial Systems AS Quick Release Rotor Attachment
NO343097B1 (en) * 2017-03-14 2018-11-05 FLIR Unmanned Aerial Systems AS Quick Release Rotor Attachment
US10519773B2 (en) 2017-03-14 2019-12-31 FLIR Unmanned Aerial Systems AS Quick release rotor attachment systems and methods

Also Published As

Publication number Publication date
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