Folding wing structure of unmanned aerial vehicle

By using a rotating shaft and a spring-type locking device in a cannon-launched UAV, and using torsion springs to reserve expansion force, the wings can be quickly deployed and locked, which solves the problems of multiple components, complex structures, and high costs in the existing technology, and adapts to It meets the requirements of miniaturization design, reduces processing costs and simplifies the folding mechanism.

CN111470031AInactive Publication Date: 2020-07-31XIAN SHENTONG INTELLIGENT CONTROL TECH CO LTD
3 Cites 6 Cited by

Patent Information

Application Number
CN202010038157.9
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2020-01-14
Publication Date
2020-07-31
Estimated Expiration
Not applicable · inactive patent

AI Technical Summary

Technical Problem

The existing canopy-launched UAV wing folding mechanism has many components, complex structural design, high cost, and is not suitable for miniaturization design.

Method used

Using a rotating shaft embedded in the fuselage, the lower wing and upper wing spring pieces are installed in the inner cavity, equipped with wedge-shaped or hemispherical locking blocks and torsion springs. The torsion spring reserves the expansion force to achieve rapid expansion and locking of the wings, simplifying The folding mechanism is eliminated and the processing cost is reduced.

Benefits of technology

It achieves a small number of parts and simple processing, reduces the processing cost of the drone, adapts to the design of a more compact cannon-launched drone, simplifies the folding mechanism, and improves the flexibility and cost-effectiveness of the structure.

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Abstract

The invention discloses a folding wing structure of an unmanned aerial vehicle, which comprises a rotating shaft embedded in a vehicle body, wherein a lower wing elastic sheet and an upper wing elastic sheet are mounted in an inner cavity of the rotating shaft from bottom to top, a first locking block and a second locking block are respectively arranged at the free ends of the lower wing elastic sheet and the upper wing elastic sheet, the first locking block and the second locking block are respectively matched with a first notch and a second notch which are formed in the rotating shaft, the outer side of the rotating shaft is sequentially sleeved with a lower wing and an upper wing from bottom to top, the upper surface of the lower wing and the lower surface of the upper wing are each provided with a groove, the two grooves are oppositely formed to form a torsional spring groove, a torsional spring is arranged in the torsional spring groove, and the upper inner sides of the lower wingand the upper wing are provided with a first locking groove and a second locking groove correspondingly; and the outer side of the rotating shaft is further sleeved with a roller bearing, a baffle isinstalled at the top of the rotating shaft, and the roller bearing is located between the upper wing and the baffle. The processing cost of the unmanned aerial vehicle is reduced, the folding wing structure is insensitive to the structural size, and the folding wing structure can adapt to a more miniaturized barrel-shooting unmanned aerial vehicle.
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Citation Information

Patent Citations

  • Synchronous folding and unfolding mechanism of wings of unmanned aerial vehicle

    CN105799915A

  • Unmanned aerial vehicle folding wing expandes and stop device

    CN208699042U

  • Folding wing structure of unmanned aerial vehicle

    CN211618064U

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