WO2019080182A1 - 一种无人机机翼折叠机构 - Google Patents

一种无人机机翼折叠机构

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Publication number
WO2019080182A1
WO2019080182A1 PCT/CN2017/110242 CN2017110242W WO2019080182A1 WO 2019080182 A1 WO2019080182 A1 WO 2019080182A1 CN 2017110242 W CN2017110242 W CN 2017110242W WO 2019080182 A1 WO2019080182 A1 WO 2019080182A1
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WO
WIPO (PCT)
Prior art keywords
wing
rotating shaft
folding
degrees
folding wing
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Application number
PCT/CN2017/110242
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English (en)
French (fr)
Inventor
罗伟
Original Assignee
罗伟
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Filing date
Publication date
Application filed by 罗伟 filed Critical 罗伟
Publication of WO2019080182A1 publication Critical patent/WO2019080182A1/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
    • B64U30/10—Wings
    • B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep

Definitions

  • the invention relates to the field of drones, and in particular to a drone folding mechanism of a drone.
  • the wing of the drone is used as a component to provide the lift of the drone. Due to the limitation of flight principle, the wing is usually designed to be elongated to provide sufficient lift for the drone, but the longer the wing, the space occupied. The larger it is, the more inconvenient to store and transport the drone.
  • the existing solutions are mostly to disassemble the wing into several pieces, and then gradually install the wing when it needs to fly, and then debug it to ensure that the drone can fly normally. This method not only has complicated procedures, but also takes a lot of time, and it is easy to damage the wing during the disassembly process and affect the flight of the drone.
  • a UAV wing folding mechanism comprising: a fuselage, a side of the fuselage is provided with a pivoting seat; a propeller, the propeller is mounted on the fuselage a first folding wing, the first folding wing has a main body portion, one end of the main body portion is provided with a first rotating shaft, and the first rotating shaft is fixed with a pivoting shaft, and the pivoting shaft and the pivoting shaft
  • the pivotal connection is pivoted, with the horizontal line as a reference line, the angle of rotation of the tail end of the first folding wing about the pivotal axis is positive, and the maximum rotation angle ranges from 0 degrees to 90 degrees.
  • the main body portion is provided with a second rotating shaft at one end of the first rotating shaft; a second folding wing, the second folding wing is connected with the second rotating shaft; and a tail wing having a third rotating shaft at one end of the tail
  • the third rotating shaft is coupled to one side of the fuselage tail.
  • a damper device is disposed on the outer side of the air body, and the damper device is a shock absorbing cotton or a shock absorbing plastic.
  • the drone can reduce the body of the drone by folding the first folding wing and the second folding wing Accumulate, avoid drones occupying too much space, easy to store and transport.
  • the second folding wing has a maximum rotation angle ranging from 0 degrees to -180 degrees.
  • first rotating shaft is used as a fulcrum
  • the direction in which the main body portion rotates upward is positive
  • the maximum rotating angle of the main body portion ranges from 0 degrees to ⁇ 90 degrees
  • the second rotating shaft is used as a fulcrum.
  • the second folding wing has a maximum rotation angle ranging from 0 degrees to 180 degrees.
  • the pivoting seat is provided with a through hole, the through hole is in the shape of a cross, the pivoting shaft is provided with a fixing portion, the fixing portion is in a shape, and the fixing portion is opposite to the through hole Cooperate.
  • the second folding wing is a hollow structure, the second folding wing receives an auxiliary wing, and the second folding wing opens an opening on a side away from the first folding wing. In the case of an aileron, the aileron is ejected through the opening.
  • the drone can accommodate the auxiliary wing when the auxiliary wing is not used, and reduce the occupied space of the drone.
  • the auxiliary wing can be directly pulled out, and the operation is convenient and practical. Strong.
  • a method for folding a wing of a drone comprising the steps of: a. providing a drone comprising a fuselage, a propeller, a first folding wing and a second folding wing, the propeller Mounted on the front end of the fuselage, a side of the fuselage is provided with a pivoting seat, the pivoting seat is provided with a through hole, the through hole is a cross shape, and the first folding wing has a main body, the main body One end of the portion is provided with a first rotating shaft, the first rotating shaft is fixed with a pivoting shaft, the pivoting shaft is provided with a fixing portion, the fixing portion is in a shape, and the fixing portion is matched with the through hole
  • the pivoting shaft is pivotally connected to the pivoting base, the main body portion is provided with a second rotating shaft at one end of the first rotating shaft, and the second folding wing is connected with the second rotating shaft; b.
  • first folding wing is rotated forward by 90 degrees around the first rotation axis
  • second folding wing is rotated backward by 180 degrees around the second rotation axis.
  • first folding wing is rotated 90 degrees behind the first rotation axis
  • second folding wing is rotated 180 degrees forward about the second rotation axis.
  • the second folding wing is a hollow structure, the second folding wing receives an auxiliary wing, and the second folding wing opens an opening on a side away from the first folding wing. In the case of an aileron, the aileron is ejected through the opening.
  • the working principle of the invention is that the first folding wing can rotate about the first rotating shaft, and the second folding wing can rotate about the second rotating shaft, so that the first folding wing and the second folding Wings folded together
  • the invention has the beneficial effects that the drone can reduce the volume of the drone and reduce the space occupied by the drone by folding the first folding wing and the second folding wing.
  • FIG. 1 is a front elevational view of an embodiment of the present invention
  • Figure 2 is a schematic view of the structure of Figure 1 after the aileron is deployed;
  • FIG. 3 is a schematic view of the first folding wing after rotating the first folding wing according to an embodiment of the present invention
  • FIG. 4 is a schematic view of the first folding wing after folding the first folding wing according to an embodiment of the present invention
  • Figure 5 is a schematic view showing the folding of the second folding wing according to an embodiment of the present invention.
  • Figure 6 is a top plan view of an embodiment of the present invention.
  • Figure 7 is a schematic view of Figure 6 after folding
  • Figure 8 is a schematic structural view of a pivot socket
  • FIG. 9 is a schematic diagram of another embodiment of the present invention.
  • an unmanned aerial wing folding mechanism includes a fuselage 1, a propeller 2, a first folding wing 3, a second folding wing 4, and a tail wing 5, the propeller 2 is mounted on the front end of the fuselage 1; a side of the fuselage 1 is provided with a pivoting seat 11, the pivoting seat 11 is provided with a through hole 111, and the through hole 111 is formed in a cross shape.
  • the first folding wing 3 has a main body portion 31. One end of the main body portion 31 is provided with a first rotating shaft 32. One side of the first rotating shaft 32 is mounted with a screw 6, and the screw 6 can control the first rotating shaft.
  • the first rotating shaft 32 is fixed with a pivoting shaft 33.
  • the pivoting shaft 33 is provided with a fixing portion 331.
  • the fixing portion 331 has a shape, and the fixing portion 331 is used for the through hole 111. Cooperate.
  • An opening is formed on a side of the pivoting seat 11 adjacent to the first rotating shaft 32.
  • the pivoting shaft 33 passes through the small hole and is pivotally connected to the pivoting seat 11.
  • the cross-sectional area of the fixing portion 331 is larger than The area of the small hole prevents the fixing portion 331 from coming off the pivoting seat 11.
  • the angle at which the tail end of the first folding wing 3 rotates upward about the pivot shaft 33 is positive, and the maximum rotation angle ranges from 0 degrees to 90 degrees, and the main body portion 31 is opposite
  • One end of the first rotating shaft 32 is provided with a second rotating shaft 34, and one side of the second rotating shaft 34 is also mounted with a screw 6 for controlling the rotation of the second rotating shaft 34.
  • the screw 6 is tightened, the The second shaft 34 is jammed so that it cannot rotate, and when the screw 6 is loosened, the second shaft 34 can rotate normally.
  • the second folding wing 4 is coupled to the second rotating shaft 34.
  • the direction in which the main body portion 31 rotates upward is positive, and the maximum rotating angle of the main body portion 31 ranges from 0 degrees to 90 degrees, with the second rotating shaft 34 as a fulcrum.
  • the second folding wing 4 has a maximum rotation angle ranging from 0 degrees to -180 degrees.
  • One end of the empennage 5 is provided with a third rotating shaft 51, and the third rotating shaft 51 is connected to one side of the tail of the fuselage 1, and the empennage 5 can be rotated upward through the third rotating shaft 51.
  • the drone can reduce the volume of the drone by folding the first folding wing 3, the second folding wing 4 and the tail wing 5, thereby preventing the drone from occupying an excessive space and facilitating storage and transportation.
  • a damper device is disposed on the outer side of the air body, and the damper device is a shock absorbing cotton or a shock absorbing plastic.
  • Second shaft 34 is a fulcrum
  • the second folding wing 4 has a maximum rotation angle ranging from 0 degrees to 180 degrees.
  • the second folding wing 4 is a hollow structure, and the second folding wing 4 houses an auxiliary wing 41, and the second folding wing 4 is away from the first folding wing 3.
  • One side of the opening defines an opening 42 through which the auxiliary wing 41 is ejected when the auxiliary wing 41 is deployed.
  • the drone can accommodate the auxiliary wing 41 to reduce the occupied space of the drone.
  • the auxiliary wing 41 can be directly pulled out, and the operation is convenient. , practical.
  • the folding manner of the UAV wing includes the following steps: first rotating the tail fin 5 upward by 90 degrees around the third rotating shaft 51, so that the board surface of the tail fin 5 abuts In the body 1. Then, the first folding wing 3 is pulled away from the body 1 to disengage the fixing portion 331 from the through hole 111, with the horizontal line as a reference line, and the tail end of the first folding wing 3 Rotating 90 degrees upward about the pivot shaft 33, so that the upper surface of the main body portion 31 is changed from the upward direction to the front direction, and then the first folding wing 3 is pushed toward the body 1 to make the The fixing portion 331 is again engaged with the through hole 111.
  • the screw 6 on the first rotating shaft 32 is loosened, and the first folding wing 3 is rotated forward by 90 degrees around the first rotating shaft 32, so that the plate surface of the main body portion 31 abuts against the body. 1.
  • the second folding wing 4 is rotated backward by -180 degrees around the second rotating shaft 34, so that the surface of the second folding wing 4 abuts against the The first folding wing 3 is described so that the entire drone is finally elongated, so that the wing does not occupy too much space.
  • the first folding wing 3 is rotated 90 degrees backward about the first rotating shaft 32, and the second folding wing 4 is rotated forward by 180 degrees around the second rotating shaft 34.
  • the plate surface of the main body portion 31 abuts against the fuselage 1, and the plate surface of the second folding wing 4 abuts against the first folding wing 3.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

一种无人机机翼折叠机构，其包括一机身（1），机身（1）的侧面设有一枢接座（11）；一螺旋桨（2），螺旋桨（2）安装于机身（1）前端；一第一折叠翼（3），第一折叠翼（3）具有一主体部（31），主体部（31）的一端设有一第一转轴（32），第一转轴（32）固设有一枢接轴（33），枢接轴（33）与枢接座（11）枢接，主体部（31）在相对第一转轴（32）的一端设有一第二转轴（34）；一第二折叠翼（4），第二折叠翼（4）与第二转轴（34）连接；一尾翼（5），尾翼（5）的一端设有一第三转轴（51），第三转轴（51）与机身（1）尾部的一侧相连接。无人机可以通过折叠第一折叠翼（3）和第二折叠翼（4）缩小无人机的体积，减小无人机占用的空间。

Description

一种无人机机翼折叠机构 技术领域
本发明涉及一种无人机领域，特别是涉及一种无人机机翼折叠机构。
背景技术
无人机的机翼作为提供无人机升力的部件，由于飞行原理限制，机翼通常都要设计成细长形来为无人机提供足够的升力，但机翼越细长，占用的空间就越大，对无人机的存放与运输就更加不便。现有的解决方法多为将机翼拆卸成好几块，在需要飞行时再把机翼逐步安装好，接着还要经过调试才能确保无人机能正常飞行。这种方法不仅工序繁杂，花费的时间多，且拆卸的过程中容易对机翼造成损伤，影响无人机的飞行。
因此，有必要设有一种新的无人机机翼折叠机构以及折叠方法解决上述问题。
发明内容
为实现上述目的，本发明采用如下技术方案：一种无人机机翼折叠机构，包括：一机身，所述机身的侧面设有一枢接座；一螺旋桨，所述螺旋桨安装于机身前端；一第一折叠翼，所述第一折叠翼具有一主体部，所述主体部的一端设有一第一转轴，所述第一转轴固设有一枢接轴，所述枢接轴与所述枢接座枢接，以水平线为基准线，所述第一折叠翼的尾端绕所述枢接轴向上旋转的角度为正，其最大旋转角度范围为0度至90度，所述主体部在相对所述第一转轴的一端设有一第二转轴；一第二折叠翼，所述第二折叠翼与所述第二转轴连接；一尾翼，所述尾翼的一端设有一第三转轴，所述第三转轴与所述机身尾部的一侧相连接。一减震装置，所述减震装置设置于机身外侧方，所述减震装置为减震棉或减震塑胶。
无人机可以通过折叠所述第一折叠翼和所述第二折叠翼，缩小无人机的体 积，避免无人机占用过大的空间，便于存放和运输。
进一步地，以所述第一转轴为支点，所述主体部往上旋转的方向为正，所述主体部最大旋转角度范围为0度至90度，以所述第二转轴为支点，所述第二折叠翼最大旋转角度范围为0度至-180度。
进一步地，以所述第一转轴为支点，所述主体部往上旋转的方向为正，所述主体部最大旋转角度范围为0度至-90度，以所述第二转轴为支点，所述第二折叠翼最大旋转角度范围为0度至180度。
进一步地，所述枢接座设有一通孔，所述通孔为十字状，所述枢接轴设有一固定部，所述固定部为一字状，所述固定部与所述通孔相配合。
进一步地，所述第二折叠翼为中空结构，所述第二折叠翼内收纳一辅翼，所述第二折叠翼在远离所述第一折叠翼的一侧开设一开口，当展开所述辅翼时，所述辅翼经所述开口弹出。
无人机在不使用所述辅翼的时候可以收纳所述辅翼，减小无人机的占用空间，在需要获得更多升力时，可以直接拉出所述辅翼，操作方便，实用性强。
一种无人机机翼的折叠方式，其方法包括有以下步骤：a、提供一无人机，其包括一机身，一螺旋桨，一第一折叠翼和一第二折叠翼，所述螺旋桨安装于机身前端，所述机身的侧面设有一枢接座，所述枢接座设有一通孔，所述通孔为十字状，所述第一折叠翼具有一主体部，所述主体部的一端设有一第一转轴，所述第一转轴固设有一枢接轴，所述枢接轴设有一固定部，所述固定部为一字状，所述固定部与所述通孔配合，所述枢接轴与所述枢接座枢接，所述主体部在相对所述第一转轴的一端设有一第二转轴，所述第二折叠翼与所述第二转轴连接；b、将所述尾翼绕所述第三转轴向上旋转90度，使所述尾翼的板面紧靠于所述机身；c、将所述第一折叠翼往远离所述机身的方向拉出，使所述固定部脱离所述通孔，以水平线为基准线，所述第一折叠翼的尾端绕所述枢接轴向上旋转90度，使得所述主体部的上表面从面向上方改为面向前方，再将所述第一折叠翼往所述机身方向推进去，使所述固定部再次与所述通孔配合；d、将所述第一折叠翼绕第一转轴旋转90度，使所述主体部的板面紧靠于所述机身；e、将所述第二折叠翼绕第二转轴旋转-180度，使所述第二折叠翼的板面紧靠于所 述第一折叠翼。
进一步地，所述第一折叠翼绕第一转轴向前旋转90度，所述第二折叠翼绕第二转轴向后旋转180度。
进一步地，所述第一折叠翼绕第一转轴向后旋转90度，所述第二折叠翼绕第二转轴向前旋转180度。
进一步地，所述第二折叠翼为中空结构，所述第二折叠翼内收纳一辅翼，所述第二折叠翼在远离所述第一折叠翼的一侧开设一开口，当展开所述辅翼时，所述辅翼经所述开口弹出。
本发明的工作原理为：所述第一折叠翼可以绕所述第一转轴旋转，所述第二折叠翼可以绕所述第二转轴旋转，使得所述第一折叠翼和所述第二折叠翼折叠在一起
本发明的有益效果为：无人机可以通过折叠所述第一折叠翼和所述第二折叠翼，缩小无人机的体积，减小无人机占用的空间。
附图说明
附图对本发明作进一步说明，但附图中的实施例不构成对本发明的任何限制。
图1为本发明一实施例提供的正面示意图；
图2为图1展开辅翼后的结构示意图；
图3为本发明一实施例旋转第一折叠翼后的示意图；
图4为本发明一实施例折叠第一折叠翼后的示意图；
图5为本发明一实施例折叠第二折叠翼后的示意图；
图6为本发明一实施例提供的俯视示意图；
图7为图6折叠后的示意图；
图8为枢接座的结构示意图；
图9为本发明另一实施例提供的示意图。
具体实施方式
如图1-8中所示，本发明一实施例提供的一种无人机机翼折叠机构，包括一机身1，一螺旋桨2，一第一折叠翼3，一第二折叠翼4和一尾翼5，所述螺旋桨2安装于机身1前端；所述机身1的侧面设有一枢接座11，所述枢接座11设有一通孔111，所述通孔111为十字状，所述第一折叠翼3具有一主体部31，所述主体部31的一端设有一第一转轴32，所述第一转轴32的一侧安装有螺丝6，螺丝6可以控制所述第一转轴32的转动，当拧紧螺丝6时，所述第一转轴32会被卡死导致不能旋转，当拧松螺丝6时，所述第一转轴32可以正常旋转。所述第一转轴32固设有一枢接轴33，所述枢接轴33设有一固定部331，所述固定部331为一字状，所述固定部331用来跟所述通孔111相配合。所述枢接座11靠近所述第一转轴32的一面设有一小孔，所述枢接轴33穿过小孔与与所述枢接座11枢接，所述固定部331的截面积大于小孔的面积，防止所述固定部331脱离所述枢接座11。以水平线为基准线，所述第一折叠翼3的尾端绕所述枢接轴33向上旋转的角度为正，其最大旋转角度范围为0度至90度，所述主体部31在相对所述第一转轴32的一端设有一第二转轴34，所述第二转轴34的一侧同样安装有螺丝6，螺丝6可以控制所述第二转轴34的转动，当拧紧螺丝6时，所述第二转轴34会被卡死导致不能旋转，当拧松螺丝6时，所述第二转轴34可以正常旋转。所述第二折叠翼4与所述第二转轴34连接。以所述第一转轴32为支点，所述主体部31往上旋转的方向为正，所述主体部31最大旋转角度范围为0度至90度，以所述第二转轴34为支点，所述第二折叠翼4最大旋转角度范围为0度至-180度。所述尾翼5的一端设有一第三转轴51，所述第三转轴51与所述机身1尾部的一侧相连接，所述尾翼5可以通过所述第三转轴51向上旋转。无人机可以通过折叠所述第一折叠翼3、所述第二折叠翼4和所述尾翼5，缩小无人机的体积，避免无人机占用过大的空间，便于存放和运输。一减震装置，所述减震装置设置于机身外侧方，所述减震装置为减震棉或减震塑胶。
在另一实施例中，以所述第一转轴32为支点，所述主体部31往上旋转的方向为正，所述主体部31最大旋转角度范围为0度至-90度，以所述第二转轴 34为支点，所述第二折叠翼4最大旋转角度范围为0度至180度。
如图1-2中所示，所述第二折叠翼4为中空结构，所述第二折叠翼4内收纳一辅翼41，所述第二折叠翼4在远离所述第一折叠翼3的一侧开设一开口42，当展开所述辅翼41时，所述辅翼41经所述开口弹出。无人机在不使用所述辅翼41的时候可以收纳所述辅翼41，减小无人机的占用空间，在需要获得更多升力时，可以直接拉出所述辅翼41，操作方便，实用性强。
如图3-7中所示，无人机机翼的折叠方式包括有以下步骤：先将所述尾翼5绕所述第三转轴51向上旋转90度，使所述尾翼5的板面紧靠于所述机身1。接着将所述第一折叠翼3往远离所述机身1的方向拉出，使所述固定部331脱离所述通孔111，以水平线为基准线，所述第一折叠翼3的尾端绕所述枢接轴33向上旋转90度，使得所述主体部31的上表面从面向上方改为面向前方，再将所述第一折叠翼3往所述机身1方向推进去，使所述固定部331再次与所述通孔111配合。再把所述第一转轴32上的螺丝6拧松，将所述第一折叠翼3绕第一转轴32向前旋转90度，使所述主体部31的板面紧靠于所述机身1。紧接着拧松所述第二转轴34上的螺丝6，将所述第二折叠翼4绕第二转轴34向后旋转-180度，使所述第二折叠翼4的板面紧靠于所述第一折叠翼3，使得无人机整体最后呈长条状，避免机翼占用过多空间。
如图9所示，在其它实施例中，所述第一折叠翼3绕第一转轴32向后旋转90度，所述第二折叠翼4绕第二转轴34向前旋转180度，所述主体部31的板面紧靠所述机身1，所述第二折叠翼4的板面紧靠于所述第一折叠翼3。
以上所述实施例的各技术特征可以进行任意的组合，为使描述简洁，未对上述实施例中的各个技术特征所有可能的组合都进行描述，然而，只要这些技术特征的组合不存在矛盾，都应当认为是本说明书记载的范围。
以上所述实施例仅表达了本发明的几种实施方式，其描述较为具体和详细，但并不能因此而理解为对发明专利范围的限制。应当指出的是，对于本领域的普通技术人员来说，在不脱离本发明构思的前提下，还可以做出若干变形和改进，这些都属于本发明的保护范围。因此，本发明专利的保护范围应以所附权利要求为准。

Claims (5)

  1. 一种无人机机翼折叠机构，其特征在与包括：
    一机身，所述机身的侧面设有一枢接座；
    一螺旋桨，所述螺旋桨位于机身前端，所述螺旋桨的一端设有一旋转座，所述旋转座以向上旋转的角度为正，其最大旋转角度范围为0度至90度；
    一第一折叠翼，所述第一折叠翼具有一主体部，所述主体部的一端设有一第一转轴，所述第一转轴固设有一枢接轴，所述枢接轴与所述枢接座枢接，以水平线为基准线，所述第一折叠翼的尾端绕所述枢接轴向上旋转的角度为正，其最大旋转角度范围为0度至90度，所述主体部在相对所述第一转轴的一端设有一第二转轴；
    一第二折叠翼，所述第二折叠翼与所述第二转轴连接；
    一尾翼，所述尾翼的一端设有一第三转轴，所述第三转轴与所述机身尾部的一侧相连接；
    一减震装置，所述减震装置设置于机身外侧方，所述减震装置为减震棉或减震塑胶。
  2. 根据权利要求1所述的无人机机翼折叠机构，其特征在于：以所述第一转轴为支点，所述主体部往上旋转的方向为正，所述主体部最大旋转角度范围为0度至90度，以所述第二转轴为支点，所述第二折叠翼最大旋转角度范围为0度至-180度。
  3. 根据权利要求1所述的无人机机翼折叠机构，其特征在于：以所述第一转轴为支点，所述主体部往上旋转的方向为正，所述主体部最大旋转角度范围为0度至-90度，以所述第二转轴为支点，所述第二折叠翼最大旋转角度范围为0度至180度。
  4. 根据权利要求1所述的无人机机翼折叠机构，其特征在于：所述枢接座设有一通孔，所述通孔为十字状，所述枢接轴设有一固定部，所述固定部为一字状，所述固定部与所述通孔相配合。
  5. 根据权利要求1所述的无人机机翼折叠机构，其特征在于：所述第二折叠翼为中空结构，所述第二折叠翼内收纳一辅翼，所述第二折叠翼在远离所述第一折叠翼的一侧开设一开口，当展开所述辅翼时，所述辅翼经所述开口弹出。
PCT/CN2017/110242 2017-10-27 2017-11-09 一种无人机机翼折叠机构 WO2019080182A1 (zh)

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