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A Wing Flexible Skin Structure

A flexible and skinned technology, applied in the directions of wings, aircraft parts, transportation and packaging, it can solve the problems of low overall bearing capacity and uneven deformation.

Active Publication Date: 2021-04-27
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical problem to be solved by the present invention is to provide a flexible wing skin with a specific chiral unit structure in view of the defects of the existing skin structures such as rubber and sliced ​​skins, such as low overall load-carrying capacity and uneven deformation. Structure and Wing

Method used

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  • A Wing Flexible Skin Structure
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Embodiment Construction

[0032] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0033] see figure 1 and figure 2 , are respectively the three-dimensional structure diagram and the plan view of the chiral unit of the wing flexible skin structure according to the preferred embodiment of the present invention. Such as figure 1 As shown, this embodiment provides a plurality of flanges 2 and chiral units 1 periodically ar...

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Abstract

The invention relates to a wing flexible skin structure and a wing, wherein the wing flexible skin structure includes a plurality of flanges and chiral units periodically arranged between the flanges; the chiral units are related to the structure Centrosymmetric, including four structural subunits, wherein each structural subunit includes: a ring, a first arcuate ligament, and a second arcuate ligament; the first end of the first arcuate ligament and the second The first ends of the arc-shaped ligaments are all tangent to the ring, and the second ends of the first arc-shaped ligaments are connected to the second ends of the first arc-shaped ligaments of the adjacent structural subunits, so The second end of the second arc-shaped ligament is connected to the outer flange. The wing flexible skin structure of the invention can not only meet the requirement of large deformation, but also ensure the rigidity requirement of the structure.

Description

technical field [0001] The invention relates to the field of structural design, in particular to a wing flexible skin structure and the wing. Background technique [0002] During the flight of the aircraft, the wing skin needs to expand and contract with the wing skeleton on a large scale, and at the same time, it needs to have sufficient stiffness to resist aerodynamic loads. Traditional aircraft wings mainly use the second type of skin. The first type is a flexible rubber-like material. The rubber skin has good airtightness and can undergo large-scale deformation, and its bearing is mainly realized by the internal structure of the wing. The second type is the traditional hard skin that can be moved in pieces, which has good bearing capacity and can undergo large deformation, which meets the requirements of wing load-bearing and deformation. [0003] The rubber skin structure mainly adopts the combination of honeycomb composite structure and silicone rubber skin. However...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C3/26
CPCB64C3/26
Inventor 梁军高付超葛敬冉马超苏亚东王福雨汪嘉兴周志强
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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