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Method for verifying influence of assembly stress on structure fatigue life

A technology of fatigue life and assembly stress, which is applied in special data processing applications, instruments, electrical digital data processing, etc., to avoid the influence of profile stiffness and to achieve accurate evaluation results

Pending Publication Date: 2020-12-04
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

[0004] The purpose of this application is to provide a method for verifying the influence of assembly stress on structural fatigue life to solve at least one problem in the prior art

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  • Method for verifying influence of assembly stress on structure fatigue life
  • Method for verifying influence of assembly stress on structure fatigue life

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Embodiment Construction

[0026] 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 creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...

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Abstract

The invention belongs to the field of airplane strength design, and particularly relates to a method for verifying the influence of assembly stress on structure fatigue life. The method comprises thesteps:1, obtainig a force bearing structure of an airplane, and determining a fatigue key part of the force bearing structure; 2, acquiring an assembly gap value of the fatigue key part and a workingstress value corresponding to the assembly gap value, judging whether the influence of different assembly gap values on the working stress value is obvious or not, and if so, entering a step 3; 3, designing a test piece according to the force bearing structure, wherein the test piece comprises a simulation piece and a profile, and the profile is connected with the simulation piece through a fastener; 4, setting the distance between the section bar and the simulation piece as a preset gap value through a fastener, and installing two ends of the test piece on a fatigue testing machine to carry out a fatigue life test, so as to obtain the fatigue life of the test piece; and 5, replacing the test piece, adjusting the preset gap value, and repeating the step 4 to obtain a corresponding curve graph of the assembly gap value and the fatigue life of the test piece.

Description

technical field [0001] The application belongs to the field of aircraft strength design, and in particular relates to a method for verifying the influence of assembly stress on structural fatigue life. Background technique [0002] The aircraft structure is composed of a large number of parts connected by fasteners. The number of parts is huge, the configuration is diverse, and the assembly level and mutual constraint relationship are complex. The release of residual stress, in the process of aircraft assembly step by step, is affected by factors such as temperature and gravity, and various errors of component parts, such as manufacturing errors, assembly deformation, coordination errors, etc., are superimposed and transmitted to each other, resulting in gaps between the bonding surfaces between structures. There is an assembly gap, and assembly stress is generated under the action of fasteners. The assembly stress is generally perpendicular to the structural working stress...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/20G06F119/04G06F119/14
CPCG06F30/15G06F30/20G06F2119/14G06F2119/04
Inventor 李伟李兆远管宇闫雨哲
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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