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Method for simulating full-size fatigue test result by adopting quasi full-size test piece

A technology of fatigue test and test results, applied in the direction of applying stable tension/pressure to test material strength, aircraft component testing, mechanical component testing, etc., to achieve economic cost savings and significant practical value

Active Publication Date: 2021-09-24
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 simulating full-scale fatigue test results using quasi-full-scale test pieces to solve or alleviate at least one of the problems in the background technology

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  • Method for simulating full-size fatigue test result by adopting quasi full-size test piece
  • Method for simulating full-size fatigue test result by adopting quasi full-size test piece

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Embodiment Construction

[0025] 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.

[0026] Such as figure 1 As shown, the method provided by the application for simulating full-scale fatigue test results using a quasi-full-scale test piece includes the following steps:

[0027] First, identify key fatigue weak spots

[0028] Fatigue strength analysis is carried out on the full-scale structure, and the key fatigue weak parts are determined according to the results of the fatigue strength analysis.

[0029] For example, in one embodiment of the present application, the full-scale structure is a full-scale canopy canopy. By analyzing the fatigue strength of the canopy full-scale structure, it can be obtained that the position of the side profile of the canopy canopy and the bolt hole connecti...

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Abstract

The invention provides a method for simulating a full-size fatigue test result by adopting a quasi-full-size test piece, and the method comprises the steps: 1, carrying out the fatigue strength analysis of a full-size structure, and obtaining a key fatigue weak part of the full-size structure; 2, determining a structural form and a cross section size of the test piece of the key fatigue weak part according to a load transfer route, a boundary condition, stress and a stress concentration coefficient of the full-size structure; 3, according to the loading and fixing requirements of the key fatigue weak part simulation test piece, constructing a key fatigue weak part test clamp; 4, according to the key fatigue weak part load obtained through calculation under the static strength design load condition, converting the fatigue load spectrum of the full-size structure, and determining a key fatigue weak part load spectrum; 5, selecting test equipment according to the load transfer route and the boundary conditions, and determining a supporting and loading method of the test piece; and 6, comparing and analyzing the results of the quasi-full-size test and the full-size test to obtain a quasi-full-size test evaluation result.

Description

technical field [0001] The application belongs to the technical field of aircraft maintenance, and in particular relates to a method for simulating full-scale fatigue test results by using a full-scale test piece. Background technique [0002] The service life of combined large components in aircraft design is usually given by the results of full-scale fatigue tests. The full-scale fatigue test cycle is long and the cost is high. In the use and maintenance of aircraft, for structures that deviate from the design state, time and cost factors should be considered , its service life often cannot be assessed by carrying out full-scale fatigue tests. Therefore, when dealing with such problems, it will be quite difficult for designers because there is no reference to test results. [0003] In view of the above reasons, it is necessary to establish a method for simulating the results of full-scale fatigue tests on quasi-full-scale specimens, so as to evaluate the results of full-sc...

Claims

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Application Information

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IPC IPC(8): G01N3/04G01N3/08G01M13/00B64F5/60
CPCG01N3/08G01N3/04G01M13/00B64F5/60G01N2203/0003G01N2203/0062G01N2203/0073
Inventor 解放刘汉海单兴业隋福成邓永先
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA