WO2018027684A1 - 一种无人机机翼快速折叠展开机构 - Google Patents

一种无人机机翼快速折叠展开机构 Download PDF

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Publication number
WO2018027684A1
WO2018027684A1 PCT/CN2016/094427 CN2016094427W WO2018027684A1 WO 2018027684 A1 WO2018027684 A1 WO 2018027684A1 CN 2016094427 W CN2016094427 W CN 2016094427W WO 2018027684 A1 WO2018027684 A1 WO 2018027684A1
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WO
WIPO (PCT)
Prior art keywords
arm
sliding sleeve
guide post
positioning hole
screw
Prior art date
Application number
PCT/CN2016/094427
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/CN2016/094427 priority Critical patent/WO2018027684A1/zh
Publication of WO2018027684A1 publication Critical patent/WO2018027684A1/zh

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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

Definitions

  • the invention relates to the technical field of drones, and more particularly to a rapid folding deployment mechanism for a drone 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 to provide a quick folding and unfolding mechanism for a drone wing that can quickly fold the deployment arm for the above-mentioned drawbacks of the prior art.
  • a rapid folding and unfolding mechanism for a drone wing comprising an arm and an arm mount; wherein an upper surface of the arm mount is provided with a guide post, and an outer surface of the guide post is sleeved with a sliding sleeve, a positioning hole is disposed on one side of the sliding sleeve; a plurality of screw holes matching the positioning hole are disposed on the guiding post; and a screw matching the screw hole is further included; and the sliding sleeve is further connected And a connecting arm of the arm, the connecting arm is rotatably connected to the surface of the arm; the end of the arm is rotatably connected to the arm mounting seat.
  • the UAV wing quick folding deployment mechanism of the present invention wherein the arm mount is provided with an opening that cooperates with the arm, the opening is of a fan-column type and the fan is located at the arm mount on.
  • the UAV wing quick folding deployment mechanism of the present invention further includes a reinforcing block that is fixedly coupled to the guide post and the arm mount.
  • the UAV wing rapid folding deployment mechanism of the present invention wherein the reinforcing block has a sleeve shape and the bottom is matched with the surface shape of the arm mounting seat.
  • the utility model has the beneficial effects that: when the folding or unfolding is required, the sliding sleeve is adjusted, and the sliding sleeve is positioned by the positioning hole and the screw, and the motive arm is rotated by the connecting arm, the structure stability is strong and the operation is very convenient; the overall structure Simple and low cost.
  • FIG. 1 is a schematic view showing the structure of a quick folding and unfolding mechanism of a drone of a preferred embodiment of the present invention.
  • the rapid folding and unfolding mechanism of the UAV wing of the preferred embodiment of the present invention includes an arm 1 and an arm mount 2; the upper surface of the arm mount 2 is provided with a guide post 20, and the guide post 20 is external.
  • the sliding sleeve 21 is disposed on the surface of the sleeve, and the positioning hole 210 is disposed on one side of the sliding sleeve 21; the plurality of screw holes 200 cooperate with the positioning hole 210; and the screw corresponding to the screw hole 200 Also included; the connecting arm 3 connecting the sliding sleeve 21 and the arm 1 is rotatably connected to the surface of the arm 1; the end of the arm 1 is rotatably connected with the arm mounting 2; When the sliding sleeve 21 is adjusted, the sliding sleeve 21 is positioned by the positioning hole 210 and the screw (not shown), and the driving arm 1 is rotated by the connecting arm 3, which has strong structural stability and convenient operation; the overall structure Simple and low cost.
  • the arm mount 2 is provided with an opening 22 that cooperates with the arm 1.
  • the opening 22 has a fan-column type and the sector is located on the arm mount 2, and the transfer reliability is strong and the arm displacement is effectively prevented. .
  • the reinforcing block 23 is also fixedly connected to the guide post 20 and the arm mount 2 to strengthen the fixed connection and ensure stability.
  • the reinforcing block 23 has a sleeve shape and the bottom is matched with the surface shape of the arm mounting seat 2, and the connection stability is strong, which is convenient for welding.

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

Abstract

一种无人机机翼快速折叠展开机构，包括机臂（1）和机臂安装座（2）；机臂安装座（2）上表面设置有导柱（20），导柱（20）外表面套设有滑动套筒（21），滑动套筒（21）一侧设置有定位孔（210）；导柱（20）上设置有多个与定位孔（210）配合的螺孔（200）；还包括与螺孔（200）配合的螺钉；还包括连接滑动套筒（21）和机臂（1）的连接臂（3），连接臂（3）与机臂（1）表面转动连接；机臂（1）端部与机臂安装座（2）转动连接；需要折叠或展开时，调节滑动套筒（21），并通过定位孔（210）和螺钉进行对滑动套筒（21）定位，通过连接臂（3）带动机臂（1）转动，结构稳定性强且操作十分方便；整体结构简单，成本低。

Description

一种无人机机翼快速折叠展开机构 技术领域
本发明涉及无人机技术领域，更具体地说，涉及一种无人机机翼快速折叠展开机构。
 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，提供一种能快速折叠展开机臂的无人机机翼快速折叠展开机构。
 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：
构造一种无人机机翼快速折叠展开机构，包括机臂和机臂安装座；其中，所述机臂安装座上表面设置有导柱，所述导柱外表面套设有滑动套筒，所述滑动套筒一侧设置有定位孔；所述导柱上设置有多个与所述定位孔配合的螺孔；还包括与所述螺孔配合的螺钉；还包括连接所述滑动套筒和所述机臂的连接臂，所述连接臂与所述机臂表面转动连接；所述机臂端部与所述机臂安装座转动连接。
本发明所述的无人机机翼快速折叠展开机构，其中，所述机臂安装座设置有与所述机臂配合的开口，所述开口呈扇柱型且扇面位于所述机臂安装座上。
本发明所述的无人机机翼快速折叠展开机构，其中，还包括与所述导柱和所述机臂安装座均固定连接的加强块。
本发明所述的无人机机翼快速折叠展开机构，其中，所述加强块呈套筒状且底部与所述机臂安装座表面形状匹配。
 有益效果
本发明的有益效果在于：需要折叠或展开时，调节滑动套筒，并通过定位孔和螺钉进行对滑动套筒定位，通过连接臂带动机臂转动，结构稳定性强且操作十分方便；整体结构简单，成本低。
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无人机机翼快速折叠展开机构结构示意图。
 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无人机机翼快速折叠展开机构如图1所示，包括机臂1和机臂安装座2；机臂安装座2上表面设置有导柱20，导柱20外表面套设有滑动套筒21，滑动套筒21一侧设置有定位孔210；导柱20上设置有多个与定位孔210配合的螺孔200；还包括与螺孔200配合的螺钉（图中未显示）；还包括连接滑动套筒21和机臂1的连接臂3，连接臂3与机臂1表面转动连接；机臂1端部与机臂安装座2转动连接；需要折叠或展开时，调节滑动套筒21，并通过定位孔210和螺钉（图中未显示）进行对滑动套筒21定位，通过连接臂3带动机臂1转动，结构稳定性强且操作十分方便；整体结构简单，成本低。
如图1所示，机臂安装座2设置有与机臂1配合的开口22，开口22呈扇柱型且扇面位于机臂安装座2上，转接可靠性强且有效防止机臂移位。
如图1所示，还包括与导柱20和机臂安装座2均固定连接的加强块23，加强固定连接，保证稳定性。
如图1所示，加强块23呈套筒状且底部与机臂安装座2表面形状匹配，连接稳定性强，便于焊接。
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 (4)

  1. 一种无人机机翼快速折叠展开机构，包括机臂和机臂安装座；其特征在于，所述机臂安装座上表面设置有导柱，所述导柱外表面套设有滑动套筒，所述滑动套筒一侧设置有定位孔；所述导柱上设置有多个与所述定位孔配合的螺孔；还包括与所述螺孔配合的螺钉；还包括连接所述滑动套筒和所述机臂的连接臂，所述连接臂与所述机臂表面转动连接；所述机臂端部与所述机臂安装座转动连接。
  2. 根据权利要求1所述的无人机机翼快速折叠展开机构，其特征在于，所述机臂安装座设置有与所述机臂配合的开口，所述开口呈扇柱型且扇面位于所述机臂安装座上。
  3. 根据权利要求1所述的无人机机翼快速折叠展开机构，其特征在于，还包括与所述导柱和所述机臂安装座均固定连接的加强块。
  4. 根据权利要求3所述的无人机机翼快速折叠展开机构，其特征在于，所述加强块呈套筒状且底部与所述机臂安装座表面形状匹配。
PCT/CN2016/094427 2016-08-10 2016-08-10 一种无人机机翼快速折叠展开机构 WO2018027684A1 (zh)

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Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4022403A (en) * 1976-01-28 1977-05-10 Louis Francois Chiquet Convertible aircraft
CN103661919A (zh) * 2013-12-23 2014-03-26 北京理工大学 基于柔性翼飞行器的机翼折叠机构
CN103693188A (zh) * 2014-01-03 2014-04-02 南京航空航天大学 无人机机翼折叠展开机构
CN203638085U (zh) * 2013-09-30 2014-06-11 中国航天科工集团第六研究院二一○所 飞行器用增力型可折叠双翼板支架
CN105620720A (zh) * 2016-03-17 2016-06-01 舒丹丹 一种航拍折叠翼无人机
CN105711811A (zh) * 2016-01-27 2016-06-29 北京航空航天大学 一种机翼折叠机构
CN105818962A (zh) * 2016-06-01 2016-08-03 中电科（德阳广汉）特种飞机系统工程有限公司 一种翼展可伸缩的折叠翼
CN106240792A (zh) * 2016-08-10 2016-12-21 张琬彬 一种无人机机翼快速折叠展开机构

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4022403A (en) * 1976-01-28 1977-05-10 Louis Francois Chiquet Convertible aircraft
CN203638085U (zh) * 2013-09-30 2014-06-11 中国航天科工集团第六研究院二一○所 飞行器用增力型可折叠双翼板支架
CN103661919A (zh) * 2013-12-23 2014-03-26 北京理工大学 基于柔性翼飞行器的机翼折叠机构
CN103693188A (zh) * 2014-01-03 2014-04-02 南京航空航天大学 无人机机翼折叠展开机构
CN105711811A (zh) * 2016-01-27 2016-06-29 北京航空航天大学 一种机翼折叠机构
CN105620720A (zh) * 2016-03-17 2016-06-01 舒丹丹 一种航拍折叠翼无人机
CN105818962A (zh) * 2016-06-01 2016-08-03 中电科（德阳广汉）特种飞机系统工程有限公司 一种翼展可伸缩的折叠翼
CN106240792A (zh) * 2016-08-10 2016-12-21 张琬彬 一种无人机机翼快速折叠展开机构

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