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Simple covering cap structure for flexible skin opening of solar unmanned aerial vehicle

A kind of flexible and solar-powered technology, applied in the direction of aircraft accessories, etc., can solve the problems of unsuitable lightweight flexible skin wings, etc., and achieve the effect of light weight, guaranteed strength and good flexibility

Active Publication Date: 2019-11-22
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to solve the problem that the above-mentioned existing flap structure is not suitable for lightweight flexible skin wings, the present invention proposes a simple flap structure for solar UAV flexible skin openings, which can be completed by simple push-pull rotation operations The quick disassembly and assembly of the cover not only fits perfectly with the flexible skin but also is extremely light in weight

Method used

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  • Simple covering cap structure for flexible skin opening of solar unmanned aerial vehicle
  • Simple covering cap structure for flexible skin opening of solar unmanned aerial vehicle
  • Simple covering cap structure for flexible skin opening of solar unmanned aerial vehicle

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Embodiment Construction

[0028] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0029] The present invention is used for the simple cover structure of solar UAV flexible skin opening, including cover base 1 and detachable cover 2, such as figure 1 shown.

[0030] like figure 2 As shown, the flap base 1 includes a lower base 101, an intermediate lap 102, and an upper slot 103, all of which are formed by curing with a layer of carbon cloth brush glue, and have the same outer contour, which is similar to the shape of a playground, that is, An approximate ellipse composed of a central rectangle and semicircles on the left and right sides of the rectangle; the diameter of the semicircles on both sides of the central rectangle is 140mm, and the distance between the centers of the two semicircles is 20mm. The lower base 101 , the middle overlapping piece 102 and the upper groove piece 103 of the above-mentioned shape are arranged from bottom...

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Abstract

The invention discloses a simple covering cap structure for a flexible skin opening of a solar unmanned aerial vehicle, and designs a carbon fiber simple covering cap structure aiming at the characteristic that the solar unmanned aerial vehicle in a near space adopts a flexible film as a film covering material. The simple covering cap structure is provided with upper, middle and lower layers of carbon sheets, and the three layers of carbon sheets are bonded and fixed; holes are formed in the three layers of carbon sheets, the holes in the middle layer are designed to be slightly larger, and gaps are formed between the upper and lower layers of carbon sheets. Furthermore, the covering cap is designed to be inserted into the hole of the middle layer, rapid disassembly and assembly of the covering cap are completed by simply pushing, pulling and rotating the covering cap, and the designed covering cap can be perfectly attached to the flexible skin and is extremely light in weight. The simple covering cap structure can be widely applied to the simple opening structure of the flexible skin.

Description

technical field [0001] The invention belongs to the field of aircraft design, and relates to a simple cover structure for the opening of a flexible skin of a solar unmanned aerial vehicle, specifically a simple cover structure that can meet the requirements for the opening of a flexible skin wing. Background technique [0002] Most of the aircraft will design opening covers on the skin where the steering gear and other equipment are installed to facilitate the replacement and maintenance of equipment. Since its skin is generally a rigid material, the designed cover is also rigid, so it can be disassembled by screws. However, for near-space solar-powered UAVs, in order to reduce the structural weight as much as possible and facilitate the arrangement of solar panels, flexible films can only be used as coating materials. Traditional rigid flaps are too bulky for such flexible-skinned aircraft, and screws cannot be used to attach the flaps to the skin. Therefore can not adopt...

Claims

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Application Information

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IPC IPC(8): B64C1/14
CPCB64C1/14
Inventor 马东立姚远杨穆清张良
Owner BEIHANG UNIV
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