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An aircraft panel structure

A technology of aircraft siding and siding, applied in the direction of the fuselage bulkhead, etc., can solve the problems of mass distribution and stiffness characteristics, and achieve the effect of changing the flutter speed

Active Publication Date: 2022-02-22
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

[0005] The purpose of this application is to provide a method to solve the problems of traditional aircraft panel structure mass distribution and rigidity characteristics

Method used

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Embodiment Construction

[0028] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the scope of protection of this application. Embodiments of the present application will be described in detail below in conjunction...

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Abstract

This application belongs to the field of aircraft structure design, and in particular relates to an aircraft panel structure. This application needs to solve the problems of traditional aircraft panel structure mass distribution and rigidity characteristics; Inside and / or on the inside of the skin, channels can be introduced with fluids to alter the weight distribution of the panel structure and thereby alter its flutter velocity.

Description

technical field [0001] The application belongs to the field of aircraft structure design, and in particular relates to an aircraft panel structure. Background technique [0002] The traditional aircraft panel structure mainly includes structural types such as metal integral panel, metal composite panel, composite material integral panel, etc., and the mass distribution and stiffness characteristics are all fixed. For the aircraft structure, especially the airfoil structure, its mass distribution and stiffness characteristics remain unchanged, which means that its flutter velocity is a fixed value, and the flutter velocity is one of the key requirements restricting the design of the aircraft airfoil structure. [0003] In order to avoid entering the flutter state, the traditional aircraft usually designs the wing structure according to the actual flutter velocity of the structure much higher than the critical flutter velocity value, sacrificing a lot of precious structural we...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/12
CPCB64C1/12
Inventor 吴斌胡宗浩王向明陈旭颜苏亚东
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA