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Lightweight and high-rigidity composite fin integrally formed part

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

Active Publication Date: 2019-01-18
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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  • Lightweight and high-rigidity composite fin integrally formed part
  • Lightweight and high-rigidity composite fin integrally formed part

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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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PUM

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Abstract

The invention belongs to the field of aircraft structure design, in particular to a lightweight and high-rigidity composite fin integrally formed part, which comprises a base, a rectangular plate-likestructure; A skin having a long plate structure with a cross section of L, wherein the angle of the L is greater than 90 DEG, and two skins are symmetrically arranged on the back of the skin and connected to the base to form a closed cavity with a cross section of triangle; Aramid paper honeycomb, which is a honeycomb structure and is filled in the closed cavity; The base and the diaphragm are made by adopting a curing molding process, thereby reducing the problem of stress concentration in the opening of the component and improving the fatigue life of the structure. The diaphragm of the composite material, the base and the aramid paper honeycomb make the structure have the advantages of high light weight, high rigidity, high modulus and the like.

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 Applications(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