WO2018027681A1 - 一种小型无人机折叠机翼 - Google Patents

一种小型无人机折叠机翼 Download PDF

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Publication number
WO2018027681A1
WO2018027681A1 PCT/CN2016/094423 CN2016094423W WO2018027681A1 WO 2018027681 A1 WO2018027681 A1 WO 2018027681A1 CN 2016094423 W CN2016094423 W CN 2016094423W WO 2018027681 A1 WO2018027681 A1 WO 2018027681A1
Authority
WO
WIPO (PCT)
Prior art keywords
arm
hole
fixing ring
small unmanned
arm mounting
Prior art date
Application number
PCT/CN2016/094423
Other languages
English (en)
French (fr)
Inventor
张琬彬
Original Assignee
张琬彬
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 张琬彬 filed Critical 张琬彬
Priority to PCT/CN2016/094423 priority Critical patent/WO2018027681A1/zh
Publication of WO2018027681A1 publication Critical patent/WO2018027681A1/zh

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Classifications

    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/02—Gyroplanes

Definitions

  • the present invention relates to the field of drone technology, and more particularly to a small drone folding wing.
  • UAVs are unmanned aircraft operated by radio remote control equipment and self-provided program control devices. Civil drones have important applications in aerial photography, agriculture, plant protection, disaster relief, etc.; currently used drone wing folding The structure is more complicated, and it is inconvenient to fold and unfold.
  • the technical problem to be solved by the present invention is that, in view of the above-mentioned drawbacks of the prior art, a small drone folding wing that is convenient for folding and unfolding is provided.
  • a small drone folding wing comprising an arm and an arm mount; wherein the arm mount end is provided with a blind hole that cooperates with the arm; the arm mount end a sidewall of each side is provided with a first through hole communicating with the blind hole, and an upper surface is provided with an opening; the end of the arm is provided with a second through hole that cooperates with the first through hole; a pin extending through the first through hole and the second through hole; the outer surface of the arm mounting end is sleeved with a fixing ring, and the inner wall of the fixing ring is provided with an internal thread; the arm mounting end The outer surface is provided with an external thread that cooperates with the internal thread.
  • the small drone folding wing of the present invention wherein the end of the arm and the bottom surface of the blind hole are all arranged in a curved surface.
  • the small unmanned aircraft folding wing of the present invention wherein the arm mounting seat is fixedly provided with a limiting ring for limiting the fixing ring.
  • the small UAV folding wing of the present invention wherein an end edge of the end portion of the arm mounting seat is provided with a flange for limiting the fixing ring.
  • the small drone folding wing of the present invention wherein an outer diameter of an end face end of the arm mounting seat is larger than an inner diameter of the fixing ring.
  • the utility model has the beneficial effects that: when the expansion is required, the arm is rotated and lowered, and then the fixing ring is rotated to shield the opening portion to fix the arm, the stability is strong and the structure is simple, and the operation is very convenient; when it is required to be stowed, Rotating the fixing ring to open the opening portion, the arm can be rotated to be stowed; the overall structure is simple, the cost is low, and the overall weight is light.
  • FIG. 1 is an exploded view showing the structure of a folding wing of a small unmanned aerial vehicle according to a preferred embodiment of the present invention.
  • the small UAV folding wing of the preferred embodiment of the present invention includes an arm 1 and an arm mount 2, and the end of the arm mount 2 is provided with a blind hole 20 that cooperates with the arm 1;
  • the side walls of the two ends of the arm mount 2 are respectively provided with a first through hole 21 communicating with the blind hole 20, and the upper surface is provided with an opening 22; the end of the arm 1 is provided with the first through hole 21
  • the through hole 10 further includes a pin extending through the first through hole 21 and the second through hole 10 (not shown);
  • the outer surface of the end portion of the arm mounting seat 2 is sleeved with a fixing ring 23, and the inner wall of the fixing ring 23 is disposed Internal thread (not shown);
  • the outer surface of the end of the arm mount 2 is provided with an external thread (not shown) that cooperates with the internal thread (not shown); when it is required to expand, the arm 1 is turned down.
  • the fixing ring 23 is rotated to fix the arm 1 to cover the opening portion 22.
  • the stability is strong and the structure is simple, and the operation is very convenient; when it is required to be retracted, the rotating fixing ring 23 opens the opening 22 to rotate.
  • the arm 1 is stowed; the overall structure is simple and the cost is low.
  • the end of the arm 1 and the bottom surface of the blind hole 20 are all arranged in a curved surface, and the contact friction is less when rotating, the equipment loss is reduced, and the expansion and the gathering are facilitated, and the positioning function can also be achieved.
  • the arm mounting seat 2 is fixedly provided with a limiting ring 25 for limiting the fixing ring 23 to prevent the fixing ring 23 from moving on the arm mounting seat 2 when the wing is folded.
  • the end edge of the end of the arm mount 2 is provided with a flange 26 for limiting the fixing ring 23 to prevent the fixing ring 23 from being tightly tightened when the wing is deployed, which causes inconvenience in disassembly and equipment damage.
  • the outer end surface of the end portion of the arm mounting base 2 is larger than the inner diameter of the fixing ring, which facilitates the fastening of the fixing ring 23.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Tents Or Canopies (AREA)

Abstract

一种小型无人机折叠机翼，包括机臂（1）和机臂安装座（2），机臂安装座（2）端部设置有与机臂（1）配合的盲孔（20）；机臂安装座（2）端部两侧侧壁均设置有与盲孔（20）连通的第一通孔（21），且上表面设置有开口（22）；机臂端部设置有与第一通孔（21）配合的第二通孔（10）；还包括贯穿第一通孔（21）和第二通孔（10）的销钉；机臂安装座（2）端部外表面套设有固定环（23），固定环（23）内壁设置有内螺纹；机臂安装座（2）端部外表面设置有与内螺纹配合的外螺纹；需要展开时，将机臂（1）转动放下，而后旋动固定环（23）以遮蔽开口（22）部位对机臂（1）进行固定即可，稳定性强且结构简单，操作十分便利；需要收起时，旋动固定环（23）打开开口（22）部位，即可转动机臂（1）进行收起；整体结构简单，成本低。

Description

一种小型无人机折叠机翼 技术领域
本发明涉及无人机技术领域，更具体地说，涉及一种小型无人机折叠机翼。
 背景技术
无人机是利用无线电遥控设备和自备的程序控制装置操纵的不载人飞机，民用无人机在航拍、农业、植保、救灾等领域有着较重要应用；目前使用的无人机机翼折叠收起结构较为复杂，折叠和展开时均较为不便。
 技术问题
本发明要解决的技术问题在于，针对现有技术的上述缺陷，提供一种折叠展开方便的小型无人机折叠机翼。
 技术解决方案
本发明解决其技术问题所采用的技术方案是：
构造一种小型无人机折叠机翼，包括机臂和机臂安装座；其中，所述机臂安装座端部设置有与所述机臂配合的盲孔；所述机臂安装座端部两侧侧壁均设置有与所述盲孔连通的第一通孔，且上表面设置有开口；所述机臂端部设置有与所述第一通孔配合的第二通孔；还包括贯穿所述第一通孔和所述第二通孔的销钉；所述机臂安装座端部外表面套设有固定环，所述固定环内壁设置有内螺纹；所述机臂安装座端部外表面设置有与所述内螺纹配合的外螺纹。
本发明所述的小型无人机折叠机翼，其中，所述机臂端部和所述盲孔底面均为弧面设置。
本发明所述的小型无人机折叠机翼，其中，所述机臂安装座上固定设置有为所述固定环限位的限位环。
本发明所述的小型无人机折叠机翼，其中，所述机臂安装座端部端面边缘设置有为所述固定环限位的凸边。
本发明所述的小型无人机折叠机翼，其中，所述机臂安装座端部端面外径大于所述固定环内径。
 有益效果
本发明的有益效果在于：需要展开时，将机臂转动放下，而后旋动固定环以遮蔽开口部位对机臂进行固定即可，稳定性强且结构简单，操作十分便利；需要收起时，旋动固定环打开开口部位，即可转动机臂进行收起；整体结构简单，成本低，且整体重量较轻。
附图说明
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将结合附图及实施例对本发明作进一步说明，下面描述中的附图仅仅是本发明的部分实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他附图：
图1是本发明较佳实施例的小型无人机折叠机翼结构爆炸图。
 本发明的实施方式
为了使本发明实施例的目的、技术方案和优点更加清楚，下面将结合本发明实施例中的技术方案进行清楚、完整的描述，显然，所描述的实施例是本发明的部分实施例，而不是全部实施例。基于本发明的实施例，本领域普通技术人员在没有付出创造性劳动的前提下所获得的所有其他实施例，都属于本发明的保护范围。
本发明较佳实施例的小型无人机折叠机翼如图1所示，包括机臂1和机臂安装座2，机臂安装座2端部设置有与机臂1配合的盲孔20；机臂安装座2端部两侧侧壁均设置有与盲孔20连通的第一通孔21，且上表面设置有开口22；机臂1端部设置有与第一通孔21配合的第二通孔10；还包括贯穿第一通孔21和第二通孔10的销钉（图中未显示）；机臂安装座2端部外表面套设有固定环23，固定环23内壁设置有内螺纹（图中未显示）；机臂安装座2端部外表面设置有与内螺纹（图中未显示）配合的外螺纹（图中未显示）；需要展开时，将机臂1转动放下，而后旋动固定环23以遮蔽开口22部位对机臂1进行固定即可，稳定性强且结构简单，操作十分便利；需要收起时，旋动固定环23打开开口22部位，即可转动机臂1进行收起；整体结构简单，成本低。
如图1所示，机臂1端部和盲孔20底面均为弧面设置，转动时接触摩擦较少，减少设备损耗，且便于展开和收拢，还能起到定位作用。
如图1所示，机臂安装座2上固定设置有为固定环23限位的限位环25，防止机翼收拢时固定环23在机臂安装座2上移动。
如图1所示，机臂安装座2端部端面边缘设置有为固定环23限位的凸边26，防止机翼展开时固定环23过渡旋紧，造成拆卸不便以及设备损伤。
如图1所示，机臂安装座2端部端面外径大于固定环内径，便于固定环23旋紧。
应当理解的是，对本领域普通技术人员来说，可以根据上述说明加以改进或变换，而所有这些改进和变换都应属于本发明所附权利要求的保护范围。

Claims (5)

  1. 一种小型无人机折叠机翼，包括机臂和机臂安装座；其特征在于，所述机臂安装座端部设置有与所述机臂配合的盲孔；所述机臂安装座端部两侧侧壁均设置有与所述盲孔连通的第一通孔，且上表面设置有开口；所述机臂端部设置有与所述第一通孔配合的第二通孔；还包括贯穿所述第一通孔和所述第二通孔的销钉；所述机臂安装座端部外表面套设有固定环，所述固定环内壁设置有内螺纹；所述机臂安装座端部外表面设置有与所述内螺纹配合的外螺纹。
  2. 根据权利要求1所述的小型无人机折叠机翼，其特征在于，所述机臂端部和所述盲孔底面均为弧面设置。
  3. 根据权利要求1所述的小型无人机折叠机翼，其特征在于，所述机臂安装座上固定设置有为所述固定环限位的限位环。
  4. 根据权利要求1所述的小型无人机折叠机翼，其特征在于，所述机臂安装座端部端面边缘设置有为所述固定环限位的凸边。
  5. 根据权利要求1所述的小型无人机折叠机翼，其特征在于，所述机臂安装座端部端面外径大于所述固定环内径。
PCT/CN2016/094423 2016-08-10 2016-08-10 一种小型无人机折叠机翼 WO2018027681A1 (zh)

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN202797281U (zh) * 2012-08-07 2013-03-13 东莞骅国电子有限公司 天线的改良结构
CN204297074U (zh) * 2014-11-13 2015-04-29 昆山优力电能运动科技有限公司 多旋翼无人机
US20150321755A1 (en) * 2014-04-28 2015-11-12 Arch Aerial, Llc Collapsible multi-rotor uav
CN204895844U (zh) * 2015-06-01 2015-12-23 深圳市大疆创新科技有限公司 多旋翼无人机
CN106081053A (zh) * 2016-08-10 2016-11-09 张琬彬 一种小型无人机折叠机翼

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN202797281U (zh) * 2012-08-07 2013-03-13 东莞骅国电子有限公司 天线的改良结构
US20150321755A1 (en) * 2014-04-28 2015-11-12 Arch Aerial, Llc Collapsible multi-rotor uav
CN204297074U (zh) * 2014-11-13 2015-04-29 昆山优力电能运动科技有限公司 多旋翼无人机
CN204895844U (zh) * 2015-06-01 2015-12-23 深圳市大疆创新科技有限公司 多旋翼无人机
CN106081053A (zh) * 2016-08-10 2016-11-09 张琬彬 一种小型无人机折叠机翼

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