WO2018040312A1 - 一种折翼式无人机 - Google Patents

一种折翼式无人机 Download PDF

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Publication number
WO2018040312A1
WO2018040312A1 PCT/CN2016/107103 CN2016107103W WO2018040312A1 WO 2018040312 A1 WO2018040312 A1 WO 2018040312A1 CN 2016107103 W CN2016107103 W CN 2016107103W WO 2018040312 A1 WO2018040312 A1 WO 2018040312A1
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Prior art keywords
folding
section
foldable
fuselage
folded
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PCT/CN2016/107103
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English (en)
French (fr)
Inventor
陈乐春
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数字鹰科技盐城有限公司
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Application filed by 数字鹰科技盐城有限公司 filed Critical 数字鹰科技盐城有限公司
Priority to KR1020187008592A priority Critical patent/KR102126142B1/ko
Publication of WO2018040312A1 publication Critical patent/WO2018040312A1/zh

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    • 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
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B64U30/293—Foldable or collapsible rotors or rotor supports
    • 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
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters

Definitions

  • the present application relates to the field of drone technology, and in particular to a drone that can be folded.
  • the arm of the conventional drone is fixedly connected to the fuselage, and has a large volume and inconvenient transportation.
  • domestic and foreign companies have actively developed a "flap" drone that can be folded with the arm and the fuselage.
  • the current common design is nothing more than a drooping flap design and a horizontal fold-over flap design. These designs are not good enough for space utilization.
  • the design of the drooping flap is to fold the front end of the horizontal arm vertically downwards, and the vertical arm has no need to occupy a large space;
  • the horizontal folding flap design is to horizontally extend the front end of the horizontal arm to one side. Folded, but the two arms have a large angle between them, resulting in a large area occupied by the horizontal space; and multiple arms occupy a space, the utilization of space is seriously insufficient.
  • a flapping drone comprising a fuselage and a plurality of arms mounted on the fuselage, the arm comprising a non-folding section, a folding mechanism and a foldable section, the unfolded section of the arm being fixed to the body
  • the foldable section of the arm is movably connected to the non-folding section by a folding mechanism, and the foldable section can be folded to a coaxial unfolded state or a non-coaxial flap state with respect to the unfolded section with the folding mechanism as an axis, In the folded state, the foldable sections of the plurality of arms are folded inwardly opposite each other.
  • the non-folded section and the foldable section of the arm are in the flap state, on the same level or at different levels.
  • the top ends of the foldable sections of the plurality of arms abut each other and are in contact with the body.
  • the foldable sections of the plurality of arms are stacked one on another in parallel.
  • the foldable sections of the plurality of arms overlap each other.
  • the application divides the arm into two sections, and the arm of the front end can be folded.
  • the arm of the section is folded inwardly when folded, or as close as possible to the fuselage, or stacked in parallel or cross each other. Stacking, so that the entire drone behind the flap is very small, easy to carry and transport, reducing the collision rate; at the same time, the arm is folded around the fuselage, which can effectively protect the fuselage and reduce the transportation process. Damage to the fuselage.
  • FIG. 1 is a schematic structural view of an unfolded state of the present application.
  • Fig. 2 is a structural schematic view showing the state of the flap in the first embodiment of the present application.
  • FIG 3 is a schematic structural view of a state of a flap in a second embodiment of the present application.
  • Fig. 4 is a structural schematic view showing the state of the flap in the third embodiment of the present application.
  • Embodiment 1 Horizontal Folding Folding UAV
  • the structure of the present embodiment is as follows: including a fuselage 1 and a plurality of arms, each arm including a non-folding section 2, a folding mechanism 3, and a foldable section 4, each of which is non-folded
  • the folding section 2 is fixedly connected to the fuselage 1, and the foldable sections 4 of the respective arms are movably connected to the corresponding non-folding sections 2 by the folding mechanism 3, respectively, and the foldable section 4 is pivoted relative to the unfolded section 2 Fold to a coaxial unfolded state or a non-coaxial flap state.
  • Embodiment 2 side parallel type folding wing drone
  • the structure of the present embodiment is as follows: including a fuselage 1 and a plurality of arms, each arm including a non-folding 2 segments, a folding mechanism 3, and a foldable segment 4, each of which is non-folded
  • the folding section 2 is fixedly connected to the fuselage 1, and the foldable sections 4 of the respective arms are movably connected to the corresponding non-folding sections 2 by the folding mechanism 3, respectively.
  • the foldable section 4 is folded with respect to the non-folding section by the folding mechanism 3 as an axis. 2 Turn to the coaxial unfolded state or the non-coaxial flap state. As shown in Fig.
  • Embodiment 3 side crossover folding wing drone
  • the structure of the embodiment is as follows: including a fuselage 1 and a plurality of arms, each arm including a non-folding 2 segments, a folding mechanism 3, and a foldable segment 4, each of which is non-folded
  • the folding section 2 is fixedly connected to the fuselage 1, and the foldable sections 4 of the respective arms are movably connected to the corresponding non-folding sections 2 by the folding mechanism 3, respectively.
  • the foldable section 4 is folded with respect to the non-folding section by the folding mechanism 3 as an axis. 2 Turn to the coaxial unfolded state or the non-coaxial flap state. As shown in Fig.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Air Bags (AREA)
  • Toys (AREA)
  • Mattresses And Other Support Structures For Chairs And Beds (AREA)

Abstract

公开了一种折翼式无人机，包括机身（1）和机臂，机臂包括非折叠段（2）、折叠机构（3）以及可折叠段（4），非折叠段（2）与机身（1）固定连接，可折叠段（4）通过折叠机构（3）与非折叠段（2）活动连接。在折翼状态下，多个机臂的可折叠段（4）两两相对向里折叠。可折叠段（4）的顶端两两相互抵接，并且与机身（1）相接触；或者，可折叠段（4）两两平行叠放；或者，可折叠段（4）相互交叉交叠。上述结构可使折翼后的无人机体积尽可能地小，便于搬运及输送，减少碰撞率；同时机臂折叠在机身周围，可以有效的对机身起到防护作用，减少运输过程中对机身的损害。

Description

一种折翼式无人机 技术领域
本申请涉及无人机技术领域，尤其涉及一种机臂可折叠的无人机。
背景技术
传统的无人机的机臂与机身是固定连接的，存在体积较大，运输不便的问题。针对上述情况，国内外已经积极开展研制机臂与机身可折叠的“折翼”无人机。目前常见的设计无外乎下垂式折翼设计以及水平翻折式折翼设计。这些设计方案在空间利用上都做的不够好。例如，下垂式折翼设计是将水平机臂的前端垂直向下折，垂直段机臂无谓占用了很大一块空间；水平翻折式折翼设计则是将水平机臂的前端水平向一侧折，但两段机臂之间具有较大的夹角，造成水平空间上占用了很大一块面积；且多个机臂各自占据一块空间，对空间的利用率严重不足。
申请内容
本申请的目的在于提供一种折叠时体积尽可能小的折翼式无人机。
为达到上述目的，本申请的实施例采用如下技术方案：
一种折翼式无人机，包括机身和安装在机身上的多个机臂，所述机臂包括非折叠段、折叠机构以及可折叠段，机臂的非折叠段与机身固定连接，机臂的可折叠段通过折叠机构与非折叠段活动连接，所述可折叠段可相对于非折叠段以折叠机构为轴折转至同轴展开状态或者非同轴折翼状态，在折翼状态下，多个机臂的可折叠段两两相对向里折叠。
依照本申请的一个方面，所述机臂的非折叠段和可折叠段在折翼状态下，处于同一水平面上或者处于不同水平面上。
依照本申请的一个方面，在折翼状态下，多个机臂的可折叠段的顶端两两相互抵接，且与所述机身相接触。
依照本申请的一个方面，在折翼状态下，多个机臂的可折叠段两两平行叠放在一起。
依照本申请的一个方面，在折翼状态下，多个机臂的可折叠段相互交叉交叠在一起。
本申请实施的优点：
本申请将机臂分为前后两段，前端的一段机臂可以折叠，该段机臂在折叠时两两相对向里折叠，要么尽可能的靠近机身，要么平行叠放，要么相互交叉交叠，从而使得折翼后的整个无人机体积非常小，便于搬运及输送，减少碰撞率；同时机臂折叠在机身周围，可以有效的对机身起到防护作用，减少运输过程中对机身的损害。
附图说明
为了更清楚地说明本申请实施例中的技术方案，下面将对实施例中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本申请的一些实施例，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的附图。
图1是本申请展开状态的结构示意图。
图2是本申请第一种实施例折翼状态的结构示意图。
图3是本申请第二种实施例折翼状态的结构示意图。
图4是本申请第三种实施例折翼状态的结构示意图。
具体实施方式
下面将结合本申请实施例中的附图，对本申请实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本申请一部分实施例，而不是全部的实施例。基于本申请中的实施例，本领域普通技术人员在没有做 出创造性劳动前提下所获得的所有其他实施例，都属于本申请保护的范围。
实施例一，水平折抵式折翼无人机
如图1和图2所示，本实施例的结构如下：包括机身1和多个机臂，每个机臂包括非折叠段2、折叠机构3以及可折叠段4，各个机臂的非折叠段2与机身1固定连接，各个机臂的可折叠段4分别通过折叠机构3与相应的非折叠段2活动连接，可折叠段4以折叠机构3为轴可相对于非折叠段2折转至同轴的展开状态或者非同轴的折翼状态。如图2所示，在折翼状态，各个机臂的非折叠段2和可折叠段4处于同一水平面上，且各个机臂的可折叠段4的顶端两两相互抵接，并且与机身1相接触。在图2中为了更清楚地展示折翼状态，特此隐藏了无人机的旋翼部分。
实施例二，侧面平行式折翼无人机
如图1和图3所示，本实施例的结构如下：包括机身1和多个机臂，每个机臂包括非折叠2段、折叠机构3以及可折叠段4，各个机臂的非折叠段2与机身1固定连接，各个机臂的可折叠段4分别通过折叠机构3与相应的非折叠段2活动连接，可折叠段4以折叠机构3为轴可相对于非折叠段折2转至同轴的展开状态或者非同轴的折翼状态。如图3所示，在折翼状态，各个机臂的非折叠段2和可折叠段4处于不同水平面上，且各个机臂的可折叠段4两两平行叠放在一起。在图3中为了更清楚地展示折翼状态，特此隐藏了无人机的旋翼部分。
实施例三，侧面交叉交叠式折翼无人机
如图1和图4所示，本实施例的结构如下：包括机身1和多个机臂，每个机臂包括非折叠2段、折叠机构3以及可折叠段4，各个机臂的非折叠段2与机身1固定连接，各个机臂的可折叠段4分别通过折叠机构3与相应的非折叠段2活动连接，可折叠段4以折叠机构3为轴可相对于非折叠段折2转至同轴的展开状态或者非同轴的折翼状态。如图4所示，在折翼状态，各个机臂的非折叠段2和可折叠段4处于不同水平面上，且各个机臂的可折叠段4两两相互交叉交叠在一起。在图4中为了更清楚地展示折翼状态，特此 隐藏了无人机的起落架部分和旋翼部分。
以上所述，仅为本申请的具体实施方式，但本申请的保护范围并不局限于此，任何熟悉本领域技术的技术人员在本申请公开的技术范围内，可轻易想到的变化或替换，都应涵盖在本申请的保护范围之内。因此，本申请的保护范围应以所述权利要求的保护范围为准。

Claims (5)

  1. 一种折翼式无人机，其特征在于：包括机身和安装在机身上的多个机臂，所述机臂包括非折叠段、折叠机构以及可折叠段，机臂的非折叠段与机身固定连接，机臂的可折叠段通过折叠机构与非折叠段活动连接，所述可折叠段可相对于非折叠段以折叠机构为轴折转至同轴展开状态或者非同轴折翼状态，在折翼状态下，多个机臂的可折叠段两两相对向里折叠。
  2. 根据权利要求1所述的折翼式无人机，其特征在于：所述机臂的非折叠段和可折叠段在折翼状态下，处于同一水平面上或者处于不同水平面上。
  3. 根据权利要求1或2所述的折翼式无人机，其特征在于：在折翼状态下，多个机臂的可折叠段的顶端两两相互抵接，且与所述机身相接触。
  4. 根据权利要求1或2所述的折翼式无人机，其特征在于：在折翼状态下，多个机臂的可折叠段两两平行叠放在一起。
  5. 根据权利要求1或2所述的折翼式无人机，其特征在于：在折翼状态下，多个机臂的可折叠段相互交叉交叠在一起。
PCT/CN2016/107103 2016-08-31 2016-11-24 一种折翼式无人机 WO2018040312A1 (zh)

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CN108609169A (zh) * 2018-06-15 2018-10-02 芜湖万户航空航天科技有限公司 可稳定折叠的无人机
CN108860586A (zh) * 2018-06-15 2018-11-23 芜湖万户航空航天科技有限公司 新型无人机
CN108773480A (zh) * 2018-06-15 2018-11-09 芜湖万户航空航天科技有限公司 无人机
CN108545190B (zh) * 2018-06-15 2020-07-07 芜湖万户航空航天科技有限公司 微型无人机
CN108910012A (zh) * 2018-07-26 2018-11-30 瀚伦贝尔通用航空器有限公司 一种可折叠的飞行器大梁装置
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