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Foldable wing of small unmanned aerial vehicle

A small UAV and wing folding technology, applied in the direction of wing adjustment, can solve the problems of reducing the width of the UAV and reducing the reliability, so as to achieve the effect of convenient deployment and improved reliability

Pending Publication Date: 2017-05-31
北京奇正数元科技股份有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to solve the problem of inconvenient operation of unmanned aerial vehicle dismantling the outer section of the wing in the prior art, and the circuit is connected through the connector to bring about the problem of lower reliability. Wings folded to reduce drone width

Method used

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  • Foldable wing of small unmanned aerial vehicle
  • Foldable wing of small unmanned aerial vehicle
  • Foldable wing of small unmanned aerial vehicle

Examples

Experimental program
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Effect test

Embodiment 1

[0026] A small unmanned aerial vehicle with foldable and retractable wings. The wings include an inner section wing 1 and an outer section wing 8 connected by bolts. The wing folded part of the section wing 8 folded on the horizontal plane, one end of the wing folded part is fixed on the inner section wing 1, and the other end is installed in the folder sleeve 5 inside the outer section wing 8, and the outer section wing 8 passes through the folder sleeve 5. It can be realized to rotate around the wing fold and slide forward and backward along the wing fold. See image 3 , when the wings are unfolded, the outer wing 8 and the inner wing 1 are connected and fastened in parallel by bolts (installed in addition), and the outer wing 8 extends to both sides of the wing. See Figure 5-Figure 7 , in the folded state of the wing, there is no bolt constraint between the outer wing 8 and the inner wing 2 (the bolts are removed), the outer wing 8 is folded to the rear side of the wing ...

Embodiment 2

[0028] A small unmanned aerial vehicle with foldable and retractable wings. The wings include an inner section wing 1 and an outer section wing 8 connected by bolts. The wing folded part of the section wing 8 folded on the horizontal plane, one end of the wing folded part is fixed on the inner section wing 1, and the other end is installed in the folder sleeve 5 inside the outer section wing 8, and the outer section wing 8 passes through the folder sleeve 5. It can be realized to rotate around the wing fold and slide forward and backward along the wing fold. See image 3 , when the wings are unfolded, the outer wing 8 and the inner wing 1 are connected and fastened in parallel by bolts (installed in addition), and the outer wing 8 extends to both sides of the wing. See Figure 5-Figure 7 , in the folded state of the wing, there is no bolt constraint between the outer wing 8 and the inner wing 2 (the bolts are removed), the outer wing 8 is folded to the rear side of the wing ...

Embodiment 3

[0031] A small unmanned aerial vehicle with foldable and retractable wings. The wings include an inner section wing 1 and an outer section wing 8 connected by bolts. The wing folded part of the section wing 8 folded on the horizontal plane, one end of the wing folded part is fixed on the inner section wing 1, and the other end is installed in the folder sleeve 5 inside the outer section wing 8, and the outer section wing 8 passes through the folder sleeve 5. It can be realized to rotate around the wing fold and slide forward and backward along the wing fold. See image 3 , when the wings are unfolded, the outer wing 8 and the inner wing 1 are connected and fastened in parallel by bolts (installed in addition), and the outer wing 8 extends to both sides of the wing. See Figure 5-Figure 7 , in the folded state of the wing, there is no bolt constraint between the outer wing 8 and the inner wing 2 (the bolts are removed), the outer wing 8 is folded to the rear side of the wing ...

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Abstract

The invention relates to a foldable wing of a small unmanned aerial vehicle. The wing comprises an inner wing section and an outer wing section connected by a bolt, wherein a wing folding piece for folding the inner wing section and the outer wing section on a horizontal plane is arranged between the inner wing section and the outer wing section, one end of the wing folding piece is fixed on the inner wing section, and the other end of the wing folding piece is installed in a folding piece sleeve inside the outer wing section; in the unfolded state of the wing, the outer wing section is connected and fasted with the inner wing section by the bolt and parallel to the inner wing section, and the outer wing section extends to two sides of the wing; and in the folded state of the wing, the outer wing section is not constrained with the inner wing section by the bolt, and the outer wing section is folded towards the rear side of the wing and perpendicular to the inner wing section. The foldable wing has the advantages: 1, the wing is divided into the outer wing section and the inner wing section, which can be folded via the wing folding piece, so that the wing is convenient to unfold; and 2, when the inner wing section and the outer wing section are folded and installed, the outer wing section does not need to be taken down, and the circuit does not need to be broken, so that the reliability of the overall device is improved.

Description

technical field [0001] The invention relates to the technical field of small drones, in particular to a foldable wing of a small drone. Background technique [0002] The wings of UAVs are the source of lift. Due to the limitations of flight principles, the wings are often designed to be slender, which brings inconvenience to packaging and transportation. Most of the existing solutions are to divide the wing into pieces, and when it needs to be installed, the outer wing and the inner wing are mechanically connected together, and the mechanical joints are all docked. This installation method is not easy to operate, and will interrupt the circuit, requiring the use of electrical connectors, which reduces the reliability of the aircraft circuit. Contents of the invention [0003] The purpose of the present invention is to solve the problem of inconvenient operation of unmanned aerial vehicle dismantling the outer section of the wing in the prior art, and the circuit is connec...

Claims

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Application Information

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IPC IPC(8): B64C3/56
CPCB64C3/56
Inventor 杨砚恒崔艳鸿
Owner 北京奇正数元科技股份有限公司
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