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Wing folding mechanism of unmanned aerial vehicle

A wing folding mechanism and UAV technology, which is applied in the fuselage, aircraft parts, aircraft control, etc., can solve the problems that affect the flight of UAVs, take a lot of time, and complicated procedures, so as to reduce the occupied space , easy to operate, and avoid taking up too much space

Inactive Publication Date: 2018-03-30
ZHAOQING CITY HI TECH ZONE XIAOJING TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This method is not only complicated and time-consuming, but also easy to cause damage to the wings during the disassembly process, affecting the flight of the UAV.

Method used

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  • Wing folding mechanism of unmanned aerial vehicle
  • Wing folding mechanism of unmanned aerial vehicle
  • Wing folding mechanism of unmanned aerial vehicle

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Embodiment Construction

[0027] Such as figure 1 - As shown in 8, a UAV wing folding mechanism provided by an embodiment of the present invention includes a fuselage 1, a propeller 2, a first folding wing 3, a second folding wing 4, and an empennage 5 , a shock absorber and a forced landing device, the propeller 2 is installed on the front end of the fuselage 1; the side of the fuselage 1 is provided with a pivot seat 11, and the pivot seat 11 is provided with a through hole 111, the through hole 111 The hole 111 is cross-shaped. The first folding wing 3 has a main body 31. One end of the main body 31 is provided with a first rotating shaft 32. A screw 6 is installed on one side of the first rotating shaft 32. The screw 6 can Control the rotation of the first rotating shaft 32. When the screw 6 is tightened, the first rotating shaft 32 will be stuck and cannot rotate. When the screw 6 is loosened, the first rotating shaft 32 can rotate normally. The first shaft 32 is fixed with a pivot shaft 33, and ...

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Abstract

The invention relates to a wing folding mechanism of an unmanned aerial vehicle. The wing folding mechanism comprises an unmanned aerial vehicle body, a propeller, a first folding wing, a second folding wing and a tail wing, wherein a pivoted base is arranged on the side surface of the unmanned aerial vehicle body; the propeller is mounted at the front end of the unmanned aerial vehicle body; thefirst folding wing is provided with a body part; a first rotating shaft is arranged at one end of the body part; the first rotating shaft is fixedly provided with a pivoted shaft; the pivoted shaft isconnected with the pivoted base in a pivoted manner; a second rotating shaft is arranged at the end opposite to the first rotating shaft, of the body part; the second folding wing is connected with the second rotating shaft; and a third rotating shaft is arranged at one end of the tail wing and is connected with one side of the tail of the unmanned aerial vehicle body. According to the unmanned aerial vehicle disclosed by the invention, the size of the unmanned aerial vehicle and the space occupied by the unmanned aerial vehicle can be reduced by folding the first folding wing and the secondfolding wing.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle wing folding mechanism. Background technique [0002] The wing of the UAV is used to provide the lift of the UAV. Due to the limitation of the flight principle, the wing is usually designed to be slender to provide enough lift for the UAV. However, the more slender the wing, the more space it occupies. The bigger it is, the more inconvenient it is for the storage and transportation of drones. Most of the existing solutions are to disassemble the wing into several pieces, and then install the wing step by step when it needs to fly, and then it needs to be debugged to ensure that the drone can fly normally. This method not only has complicated procedures and takes a lot of time, but also easily causes damage to the wings during the disassembly process, which affects the flight of the drone. [0003] Therefore, be necessary to be provided with a k...

Claims

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Application Information

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IPC IPC(8): B64C1/30
CPCB64C1/30
Inventor 张紫婷
Owner ZHAOQING CITY HI TECH ZONE XIAOJING TECH CO LTD
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