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Honeycomb supporting structure comprising flexible skin and preparation method of flexible skin

A support structure, honeycomb technology, used in chemical instruments and methods, transportation and packaging, synthetic resin layered products, etc., to achieve the effect of reducing output requirements, maintaining aerodynamic shape, and uniform surface

Active Publication Date: 2022-06-10
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to solve the above technical problems, the present invention proposes a honeycomb support structure including a flexible skin and a preparation method of the flexible skin, which can effectively solve the problems of poor aerodynamic effect and The problem of low tear resistance

Method used

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  • Honeycomb supporting structure comprising flexible skin and preparation method of flexible skin
  • Honeycomb supporting structure comprising flexible skin and preparation method of flexible skin

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0029] The webs 1b are arranged spanwise between the zero Poisson's ratio honeycombs 1a on the upper and lower surfaces, and a through groove 1b1 is provided in the middle of each web 1b. The central side strip 1c is arranged at the height center position of the side of the web 1b, and is fixedly connected with all the webs 1b. The trailing edge section 1d is fixedly connected with the zero Poisson's ratio honeycomb 1a and the central side strip 1c. The zero Poisson's ratio honeycomb 1a is fixedly connected to the leading edge installation section 1e. Both ends of the inclined side tie rod 1f are fixedly connected to the front edge installation section 1e and the central side strip 1c respectively. The front end of the trailing edge section 1d is provided with a support plate 1d1, and the middle part of the support plate 1d1 is provided with a spanwise chute 1d1a.

[0030] The honeycomb support structure is an integrated overall structure, which is made of polyamide or polye...

Embodiment 2

[0033] Among them, the preparation method of the flexible skin can be as follows: the curing agent composed of silicone rubber Sylgard184, vinyl silicone oil and platinum catalyst is weighed according to the mass ratio of 10:1, and 0-10% diluent is added, mechanically stirred and ultrasonically The method of dispersion is mixed to obtain the resin; the configured resin is poured into the mold to make it soak into the unidirectional elastic nylon fabric; pressure is applied to squeeze out the excess resin. After adding the resin, let it stand at room temperature, then put it into an oven, and complete the curing under the condition of 60-100°C. Curing is considered complete when the surface is not tacky. After taking out the mold, let it cool down to room temperature naturally, take out the material from the mold, cut it properly, and get a flexible skin. Among them, when infiltrating the unidirectional elastic nylon fabric, the method of stacking layer by layer is adopted. Af...

Embodiment 3

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Abstract

The invention relates to the technical field of aircrafts, in particular to a honeycomb supporting structure comprising a flexible skin and a preparation method of the flexible skin, the honeycomb supporting structure is a non-full-thickness penetrating type structure and comprises a zero-Poisson-ratio honeycomb, a web, a center side strip, a rear edge section, a front edge mounting section, an inclined side pull rod and the flexible skin; the flexible skin is formed by compounding a one-way elastic nylon fabric and silicone rubber; the zero-Poisson-ratio honeycombs are arranged on the upper surface and the lower surface of the honeycomb supporting structure; the webs are arranged between the zero-Poisson-ratio honeycombs on the upper surface and the lower surface in the spanwise direction, and a through groove is formed in the middle of each web; a supporting plate is arranged at the front end of the rear edge section, a sliding groove in the spanwise direction is formed in the middle of the supporting plate, and connecting pieces are arranged on the two sides of the supporting plate respectively. The through groove and the sliding groove are connected through a driving shaft, and the honeycomb supporting structure is driven to be bent and subjected to torsional deformation. According to the invention, the problems of poor pneumatic effect and low tear resistance can be effectively solved.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a honeycomb support structure including a flexible skin and a preparation method of the flexible skin. Background technique [0002] Adjusting the camber of the wing is an important method to realize the maneuver control of the aircraft and improve the aerodynamic efficiency. The front and rear edges of the flexible variable camber can change the camber of the wing airfoil in a smooth and continuous manner. Compared with the traditional rigid variable camber, it has superior performance. It can avoid the diffraction of traveling waves formed by the gap, avoid sudden changes in curvature, effectively weaken the flow separation, and improve the aircraft. attitude control ability. Existing flexible variable-camber wings usually use elastic structures as internal support structures, and the support structures must not only have sufficient bearing capacity, but also have the ability...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/44B64C3/26B32B27/34B32B27/28B32B27/12B32B5/02B32B5/26B32B3/12B29C70/36B29C70/54
CPCB64C3/44B64C3/26B32B27/34B32B27/285B32B27/12B32B5/02B32B5/26B32B3/12B29C70/36B29C70/54B32B2260/021B32B2260/048B32B2307/7242B32B2605/18Y02T50/40Y02T90/00
Inventor 周玥李博杨东文友谊白大山
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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