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Rotor wing folding structure for unmanned aerial vehicle, and unmanned aerial vehicle

A technology of folding structure and rotor, applied in the direction of rotorcraft, unmanned aircraft, fuselage, etc., can solve the problems of inability to fold the rotor, occupy a large space, and the rotor volume is large, and achieve compact structure, convenient folding, Good flight stability

Active Publication Date: 2018-02-16
四川金瑞穗科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At present, there are various drones on the market, but none of these drones can fold the rotors, which is not only inconvenient to carry, but also easy to damage the rotors during transportation, and when the rotors are unfolded, they are larger and take up a lot of space , not easy to place

Method used

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  • Rotor wing folding structure for unmanned aerial vehicle, and unmanned aerial vehicle
  • Rotor wing folding structure for unmanned aerial vehicle, and unmanned aerial vehicle
  • Rotor wing folding structure for unmanned aerial vehicle, and unmanned aerial vehicle

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Embodiment approach 1

[0032] refer to Figure 1-4 As shown, the UAV rotor folding structure provided by Embodiment 1 of the present invention includes a frame 11 , a rotor assembly 12 and a folding assembly 13 .

[0033] The folding assembly 13 includes a first adapter 131 and a second adapter 132 .

[0034] One end of the first adapter 131 is rotatably connected to one end of the second adapter 132 , and the first adapter 131 and the second adapter 132 may be connected by a pin or by a hinge.

[0035] A buckle 133 for keeping the first adapter 131 and the second adapter 132 relatively fixed may also be provided between the first adapter 131 and the second adapter 132; when the buckle 133 is locked, the first adapter 131 Keep relatively fixed with the second adapter 132; when the buckle 133 is opened, the first adapter 131 and the second adapter 132 can rotate relatively. The buckle 133 includes a lock hook 1331 and a lock core 1332, the lock hook 1331 is arranged on the second adapter 132, the f...

Embodiment approach 2

[0044] refer to Figure 5 As shown, an unmanned aerial vehicle provided by Embodiment 2 of the present invention includes a control system and an unmanned aerial vehicle rotor folding structure.

[0045] It should be noted that in this embodiment, the UAV rotor folding structure can adopt the UAV rotor folding structure in Embodiment 1, and its structure, working principle and technical effects can refer to the corresponding content in Embodiment 1. No detailed description is given here.

[0046] In this embodiment, the number of rotor assemblies 12 is four, and the four rotor assemblies 12 are respectively fixed at four corners of the upper end of the frame 11 through folding assemblies 13 .

[0047] It should be noted that the rotor assembly 12 can adopt the prior art, and the number of the rotor assembly 12 can also be more than four. In order to ensure the stability of the drone during flight, the number of the rotor assembly 12 should be an even number, and symmetrically...

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Abstract

The invention provides a rotor wing folding structure for an unmanned aerial vehicle, and the unmanned aerial vehicle and belongs to the technical field of unmanned aerial vehicles. The rotor wing folding structure for the unmanned aerial vehicle comprises vehicle frames, rotor wing assemblies and folding assemblies; the rotor wing assemblies are supported on the vehicle frames through the foldingassemblies; the folding assemblies comprise first adapting heads and second adapting heads; the first adapting heads are fixed to the upper ends of the vehicle frames; one ends of the second adaptingheads are connected with one ends of the rotor wing assemblies; the ends, away from the rotor wing assemblies, of the second adapting heads are rotationally connected with one ends of the first adapting heads; buckles enabling the first adapting heads and the second adapting heads to keep relative fixing are further arranged between the first adapting heads and the second adapting heads; and therotor wing folding structure for the unmanned aerial vehicle has the first state that the first adapting heads and the second adapting heads are unfolded, and the buckles are locked and the second state that the buckles are unlocked, and the first adapting heads and the second adapting heads are folded. The rotor wing folding structure is simple in structure, and rotor wings can be folded and arecompact in structure after being folded. The rotor wings of the unmanned aerial vehicle are compact in structure and accordingly convenient to store or carry after being folded.

Description

technical field [0001] The present invention relates to the technical field of unmanned aerial vehicles, in particular, to an unmanned aerial vehicle rotor folding structure and an unmanned aerial vehicle. Background technique [0002] At present, there are various drones on the market, but none of these drones can fold the rotors, which is not only inconvenient to carry, but also easy to damage the rotors during transportation, and when the rotors are unfolded, they are larger and take up a lot of space , not easy to place. Contents of the invention [0003] The purpose of the embodiments of the present invention is to provide a folding structure for the rotor of the drone, which has a simple structure and the foldable rotor, which can better improve the above problems. [0004] Another object of the embodiments of the present invention is to provide a drone with a compact structure and good stability. [0005] The embodiment of the present invention is realized like th...

Claims

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Application Information

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IPC IPC(8): B64C1/06B64C1/30B64C27/08
CPCB64C1/063B64C1/30B64C27/08B64U10/10
Inventor 陈鹏元黎伟
Owner 四川金瑞穗科技有限公司
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