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Method for determining high-cycle fatigue life of bolt hole in complex stress state

A stress state, high cycle fatigue technology, applied in the field of mechanical fatigue life calculation, to achieve the effect of accurate fatigue life

Active Publication Date: 2020-01-31
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Abstract
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  • Application Information

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Problems solved by technology

[0014] The purpose of this application is to provide a method for determining the high-cycle fatigue life of bolt holes under complex stress conditions, so as to solve or alleviate at least one of the problems in the background technology

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  • Method for determining high-cycle fatigue life of bolt hole in complex stress state
  • Method for determining high-cycle fatigue life of bolt hole in complex stress state
  • Method for determining high-cycle fatigue life of bolt hole in complex stress state

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Embodiment Construction

[0054] 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.

[0055]The purpose of this application is to solve the problems in the prior art that the plate width of the structure cannot be determined, and the stress concentration factor is also difficult to determine, and propose a method that can more accurately determine the fatigue life of bolt holes under complex stress states . The method of the present application is by first determining the stress concentration factor K tg and K tb , and then determine the plate width W to solve the stress severity factor SSF, and determine the nominal stress caused by the bypass load through the method of this application, so that the determination of the life of the bolt hole is more accurate.

[0056] In order to achieve t...

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Abstract

The invention relates to a method for determining the high-cycle fatigue life of a bolt hole in a complex stress state, and the method comprises the steps: obtaining the thickness of a structure and the diameter of the bolt hole, and determining an extrusion distribution coefficient according to the thickness and the diameter; establishing a finite element model of the structure; applying two different loads to the finite element model and the solid structure model of the structure to obtain the maximum stress of the bolt hole under the two loads and the nominal stress caused by the bypass load of the bolt hole, and determining a stress concentration coefficient according to the two loads and the maximum stress and the nominal stress under the corresponding loads; determining the plate width of the structure according to the extrusion stress concentration coefficient; determining a stress severity coefficient according to the local maximum stress under the stress load required to be solved by the structure, the nominal stress caused by the bypass load, the nail transmission load and the like; and finally, obtaining the high-cycle fatigue life of the bolt hole in the complex stressstate according to the stress severity coefficient.

Description

technical field [0001] The application belongs to the technical field of mechanical fatigue life calculation, and in particular relates to a method for determining the high cycle fatigue life of a bolt hole under a complex stress state. Background technique [0002] For the engineering environment where the bolt hole is subjected to shear, the stress severity coefficient method is usually used to calculate the high cycle fatigue life of the bolt hole. [0003] like figure 1 As shown, the following is a brief description of the stress severity factor method: [0004] figure 2 As a typical structural detail of the connector, part of the load on the structural plate with holes passes through the bypass, which is called the bypass load P pl , and the other part is transferred away by the fastener, called the nail transfer load P dc . [0005] Bypass load P pl The resulting local maximum stress is σ 1 , the local maximum stress σ 1 The calculation formula of is shown in ...

Claims

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Application Information

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IPC IPC(8): G06F30/23G06F119/04
Inventor 张鹤赵通
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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