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A light-weight and high-rigidity composite wing blade integral molding

A composite material and integral molding technology, which is applied in the direction of wings, aircraft parts, heat reduction structures, etc., to improve the fatigue life of the structure and reduce the stress concentration of the opening

Active Publication Date: 2022-04-01
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The light-weight and high-rigidity composite wing blade integral molding of the present invention can solve or overcome at least one problem existing in the prior art

Method used

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  • A light-weight and high-rigidity composite wing blade integral molding
  • A light-weight and high-rigidity composite wing blade integral molding

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Embodiment Construction

[0017] In order to make the present invention easier to understand, the present invention will be described in detail below in conjunction with the accompanying drawings.

[0018] In describing the present invention, it is to be understood that the terms "central", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", The orientations or positional relationships indicated by "top", "bottom", "inner", "outer", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying the Means that a device or element must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be construed as limiting the scope of the invention.

[0019] Such as figure 1 and figure 2 It is a light-weight and high-rigidity composite wing blade integral molding...

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Abstract

The invention belongs to the field of aircraft structure design, and specifically relates to a light-weight and high-rigidity composite material wing knife integral molding, including: a base, a rectangular plate-shaped structure; a skin, a long plate structure with an "L" cross-section. The angle of the "L" is greater than 90°, and the two skins are arranged symmetrically and connected to the base to form a closed cavity with a "triangular" section; the aramid paper honeycomb is honeycomb-shaped The structure is filled in the airtight cavity; the base and the skin are made by curing molding process, which reduces the problem of stress concentration in the opening of the component and improves the fatigue life of the structure. The skin and base of composite materials And aramid paper honeycomb makes this structure have the advantages of high lightness, high rigidity, high modulus and so on.

Description

technical field [0001] The invention belongs to the field of aircraft structure design, and in particular relates to a lightweight and high-rigidity composite material wing knife integral molding. Background technique [0002] Wing (cabin) knives can prevent the spanwise flow of airflow on the surface of the wing to ease the separation of wingtips. Wing (cabin) knives are generally installed on the surface of the wing or functional cabin, requiring high structural rigidity and durability. Possibly low structural weight. In the past, the widely used metal sheet metal riveting assembly formed parts required a large number of fasteners, which increased the source of fatigue; while the metal profile machine-added wing (cabin) knife was limited by the process subsidence, requiring more structural weight gain , resulting in heavy weight of the wing (cabin) knife, many sources of fatigue, complex assembly of structural parts, and low service life. Contents of the invention [0...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C3/00B64C3/36
CPCB64C3/00B64C3/36
Inventor 隋晓东姜野杨立军朱亮何天闯
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA