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Small-scale empennage synchronous folding mechanism

A technology of folding mechanism and tail, applied in the field of aviation unmanned aerial vehicle, can solve problems such as unreliability and instability, and achieve the effect of reducing folding size, light weight and high structural efficiency

Pending Publication Date: 2019-01-29
CAIHONG DRONE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In this application, the development process of the left and right vertical tails is not synchronized, resulting in instability and unreliability

Method used

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  • Small-scale empennage synchronous folding mechanism
  • Small-scale empennage synchronous folding mechanism
  • Small-scale empennage synchronous folding mechanism

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Experimental program
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Effect test

Embodiment Construction

[0033] Such as Figure 1-9 As shown, the present invention aims at the folding wing technology under the existing technical conditions and mainly aims at the problem of the wing structure, the empennage does not fold or folds slightly, and proposes a small-sized empennage synchronous folding mechanism, including: empennage 1, empennage bushing 2 , empennage casing 3 and torsion spring 4; Wherein empennage 1 comprises empennage main body 11 and is positioned at the end of empennage main body 11 and is perpendicular to empennage joint 12 of main body 11;

[0034] Mounting holes for the empennage bushing 2 are arranged symmetrically on the fuselage, and the empennage bushing 2 is fixedly mounted on the corresponding mounting hole. The empennage joint 12 passes through the empennage bushing 2 and extends into the inside of the empennage bushing 3, and is fixed with the empennage bushing 3 connect;

[0035] The torsion spring 4 is sleeved on the empennage sleeve 3, one end is conn...

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Abstract

The invention relates to a small-scale empennage synchronous folding mechanism. The small-scale empennage synchronous folding mechanism comprises empennages, empennage linings, empennage sleeves and torsional springs; the empennages further comprise empennage main bodies and empennage connectors, wherein the empennage connectors are located on the end portions of the empennage main bodies and perpendicular to the empennage main bodies; installation holes of the empennage linings are symmetrically formed in a fuselage, the empennage linings are fixedly installed on the corresponding installation holes, the empennage connectors penetrate through the empennage linings, extend into the empennage sleeves and are fixedly connected with the empennage sleeves; the empennage sleeves are sleeved with the torsional springs, one ends of the torsional springs are connected to bolts on which the empennage linings are fixedly connected with the empennage sleeves, and the other ends of the torsional springs are connected to bolts on which the empennage sleeves are fixedly connected with the empennage connectors; and corresponding limiting bosses are arranged on the empennage linings and the empennage sleeves, cooperative use enables the empennages to be limited after unfolded, the empennages rotate around the empennage sleeves to realize synchronous folding of the empennages, so that the empennages are folded by 90 degrees, and the fuselage size is shortened.

Description

technical field [0001] The invention relates to a small-sized empennage synchronous folding mechanism, which belongs to the field of aviation unmanned aerial vehicles. Background technique [0002] At present, small UAVs are developing rapidly, and their application fields have been extended to military, scientific research, civilian and other fields. Traditional drones cannot be folded, and are bulky and difficult to carry. If it is designed as a detachable structure, it will bring cumbersome disassembly and assembly work during use, which is time-consuming and labor-intensive. Therefore, the folding of the wing surface can reduce the volume of the drone, which is convenient for transportation, portability and use. [0003] For small tube-fired folding-wing UAVs, the folding wing technology under the existing technical conditions is mainly aimed at the wing structure, the tail is not folded or slightly folded, and the tail folding technology has problems such as asynchron...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/30
CPCB64C1/30
Inventor 徐涛史旭东汪艳伟
Owner CAIHONG DRONE TECH CO LTD
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