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Quick-dismantling wing and unmanned aerial vehicle

A wing and position-limiting technology, applied in the field of quick-release wings and unmanned aerial vehicles, can solve the problems of large bending moment at the joint of the wing, and achieve the effects of ensuring reliability, convenient disassembly, and improving reliability.

Active Publication Date: 2019-01-22
GOERTEK ROBTICS CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the problem that the wing of the fixed-wing aircraft proposed in the above-mentioned background technology flips over and causes a large bending moment at the joint of the wing, the present invention provides a quick-release wing and an unmanned aerial vehicle

Method used

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  • Quick-dismantling wing and unmanned aerial vehicle
  • Quick-dismantling wing and unmanned aerial vehicle
  • Quick-dismantling wing and unmanned aerial vehicle

Examples

Experimental program
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Effect test

Embodiment 1

[0031] Such as figure 1 , figure 2 , image 3 , Figure 4 and Figure 5 As shown, the quick-release wing provided by this embodiment includes a first wing module 10 and a second wing module 20, the first wing module 10 is provided with a main beam 11 extending along the length direction of the wing, and the main beam 11 is the main frame of the first wing module 10, which can be in the shape of a circle or a rectangle to support the first wing module 10 and increase its strength. The second wing module 20 is provided with a plug-in beam 21 inserted into the inner cavity of the main beam 11 along the length direction of the wing, so that the second wing module 20 is mated with the first wing module 10 .

[0032] At least two limiting channels are arranged on the main beam 11 , and the at least two limiting channels are distributed along the length direction of the wing at a predetermined distance, for example, the spacing between two adjacent limiting channels is set on th...

Embodiment 2

[0049] In this example, if Figure 7 As shown, there are also two limiting channels and two limiting holes 211 , and the structure of the corresponding limiting module 30 is different from the structure of the limiting module 30 in the first embodiment. Specifically, the limit module 30 The limit module 30 includes two limit pins 31, the first ends of the two limit pins 31 form two limit parts, the second ends of the two limit pins 31 pass through the connecting rod 321 Fixed connection. The operating part includes an operating rod 322 , a first end of the operating rod 322 is connected to the connecting rod 321 , and a second end of the operating rod 322 extends to the outside of the first wing module 10 . That is, the operating part in this embodiment is the operating lever 322 parallel to the limiting pin 31 , and the user grasps the operating lever 322 to move the limiting pin 31 . The connecting rod 321 may be located inside the first wing module 10 or outside the first...

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Abstract

The invention discloses a quick-dismantling wing and an unmanned aerial vehicle. The quick-dismantling wing comprises a first wing module and a second wing module. The first wing module is provided with a main girder extending along the length of the wing. At least two limit channels are arranged on the main girder, and the at least two limit channels are distributed along the length of the wing with a preset interval. The second wing module is provided with a plug beam inserted into the inner cavity of the main girder along the length direction of the wing, and the plug beam is provided withat least two limit holes corresponding to at least two limit channels one by one. The quick-dismantling wing further comprises a limit module, wherein the limit module comprises at least two limit portions corresponding to the limit channels one by one; at least two limit portions have a locking position where that limit hole is inserted from the limiting channel and a quick release position wherethe limit hole is disengaged, respectively. At least two limit portion cooperate with that limiting passage to limit the turnover of the quick dismantle wing and transfer the torque to the main girder, thereby avoiding the force and torque at the wing joint and improving the reliability of the quick-dismantling wing.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a quick-release wing and an unmanned aerial vehicle. Background technique [0002] With the rise of the unmanned aerial vehicle industry, unmanned aerial vehicles have been widely used in various industries. [0003] In the prior art, due to the stability and structural strength of the fixed wing compared with the rotary wing, it has greater advantages. Many people's favor. However, due to the large size and long wingspan of UAV fixed-wing aircraft, the packaging and transportation of the aircraft are very inconvenient, which brings great difficulties to the transportation process. In the actual operation process, for the rotorcraft, the usual method is to disassemble the rotor from the aircraft for transportation; and then put the rotor back on the aircraft when in use. However, this method is not suitable for fixed-wing flying. Therefore, for fixed-wing air...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/00
CPCB64C3/00B64U10/25
Inventor 郑立坤颜安石翔
Owner GOERTEK ROBTICS CO LTD