Wing folding and unfolding mechanism for light unmanned aerial vehicle

A technology of unfolding mechanism and wing folding, applied in wing adjustment, unmanned aircraft, motor vehicles, etc. And the effect of convenient debugging, simple structure, and reduced occupied space

Inactive Publication Date: 2019-02-22
北京大翔航空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The existing wing folding and unfolding mechanism for UAVs has a complex and fixed structure, and is difficult to assemble and adjust. At the same time, the total weight of the mechanism is large, which is not suitable for light UAVs.

Method used

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  • Wing folding and unfolding mechanism for light unmanned aerial vehicle
  • Wing folding and unfolding mechanism for light unmanned aerial vehicle
  • Wing folding and unfolding mechanism for light unmanned aerial vehicle

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Embodiment Construction

[0024] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0025] as attached Figure 1-4 As shown, the present invention provides a light-duty UAV wing folding and unfolding mechanism, which includes an upper cover 1, a lower cover 2, a lower positioning cover 3, fastening long bolts 4, an upper positioning cover 5, and an upper bearing 6 , upper torsion spring 7, mandrel 8, plane bearing 9, nut 10, lower bearing 11 and lower torsion spring 12;

[0026] as attached Figure 5 As shown, the upper torsion spring 7 and the lower torsion spring 12 torsion springs are a concentric inner and outer double-layer structure, and the two ends of the torsion spring are respectively a straight end and a hook end. Located on the outer layer of the torsion spring, the straight end is used for fixed connection with the fixing component, and the hook-shaped end is used for matching and fixed connection with the groove of the win...

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Abstract

The invention discloses a wing folding and unfolding mechanism for a light unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicle deformation structures. The unfoldingmechanism comprises an upper cover, a lower cover, a fixed assembly, bearings and torsion springs, wherein the upper cover and the lower cover are separately mounted at upper and lower ends of the fixed assembly through the bearings; the upper cover and the lower cover are in rolling fit to the fixed assembly; the upper cover and the lower cover are fixedly connected with two wings separately; upper and lower positions of the two torsion springs are arranged on the outer peripheral surface of the fixed assembly in a concentric sleeving mode, and separately correspond to the position of the upper cover and the position of the lower cover; ends of the torsion springs are fixedly connected with the fixed assembly; the other ends of the torsion springs are fixedly connected with the wings; andthe unfolding mechanism is fixedly connected with the machine body through the lower end of the fixed assembly. The wing folding and unfolding mechanism is small in size, light in mass, is easily modified, and can be suitable for different light unmanned aerial vehicle platforms.

Description

technical field [0001] The invention relates to a folding and unfolding mechanism of an unmanned aerial vehicle, specifically designs a wing folding and unfolding mechanism that can be used for a light unmanned aerial vehicle, and belongs to the technical field of deformation structure of an unmanned aerial vehicle. Background technique [0002] Lightweight folding UAVs can change the spatial size and appearance characteristics of UAVs by folding and unfolding wings and other components during the storage, launch, flight, and recovery stages, which can effectively save space and facilitate UAVs It can be carried and transported, and can fully adapt to different working stages, improving its launch recovery performance and flight performance. [0003] The existing wing folding and unfolding mechanism for unmanned aerial vehicles has a complex and fixed structure, and is difficult to assemble and adjust. At the same time, the total weight of the mechanism is large, which is no...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/56
CPCB64C3/56B64U10/25B64U30/12
Inventor 叶波波姚冰熊婧
Owner 北京大翔航空科技有限公司
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