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Fatigue life prediction method for fiber metal laminate under complex load

A technology for fiber metal laminates and fatigue life prediction, applied in the direction of using stable tension/compression to test material strength, measuring devices, instruments, etc.

Pending Publication Date: 2020-12-08
SHENYANG JIANZHU UNIVERSITY
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  • Abstract
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  • Application Information

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Problems solved by technology

Therefore, the technical methods suitable for life prediction of traditional composite materials will no longer be applicable to fiber metal laminates.

Method used

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  • Fatigue life prediction method for fiber metal laminate under complex load
  • Fatigue life prediction method for fiber metal laminate under complex load
  • Fatigue life prediction method for fiber metal laminate under complex load

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Embodiment Construction

[0064] The invention will be further described below in conjunction with the accompanying drawings and specific implementation examples. The average stress correction model—Constant Life Diagrams (CLD) is a predictive tool for evaluating the fatigue life of materials under constant amplitude loading. It can reflect the comprehensive influence of material properties and average stress on fatigue life performance. Among them, the main parameters used to construct the CLD model are: stress amplitude, average stress and stress ratio, and the stress ratio is the ratio of the trough value to the peak value of the cyclic stress.

[0065] The piecewise linear difference method (also known as the piecewise linear CLD model) is developed by σ m -σ a The different S-N curves on the coordinate plane are deduced by the principle of linear interpolation, and the model is constructed by the ultimate compressive strength, ultimate tensile strength and some known S-N curves. The stress ratio ...

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Abstract

The invention provides a fatigue life prediction method for a fiber metal laminate under a complex load. Firstly, a fatigue life test with the stress ratio of cyclic stress of 0.06, -1 and 10 is applied to a fiber metal laminate, a static tensile test and a static compression test are carried out on the fiber metal laminate, and then a constant-amplitude fatigue life value under each cyclic stressin a complex load spectrum is calculated based on a piecewise linear difference method. Finally, the cumulative damage rate of the complex load spectrum to the fiber metal laminate is calculated to obtain the fatigue life of the fiber metal laminate under any complex load. The average stress correction model suitable for the fiber metal laminate is provided, the fatigue life value under any stress ratio can be accurately solved, the irregular load spectrum characteristics are considered, the damage accumulation model considering the residual strength is corrected on the basis of the Hashin hypothesis and in combination with the Miner damage accumulation theory, the fatigue life predicted by the method is more effective, and the implementation process is simpler and more convenient.

Description

technical field [0001] The invention relates to the technical field of fatigue performance research of aeronautical structural materials, in particular to a method for predicting fatigue life of fiber metal laminates under complex loads. Background technique [0002] Since the middle of the 20th century, in order to meet the needs of the rapid development of the aerospace industry, it has become a general trend to continuously improve the performance of structural materials in all aspects. Many countries are more and more urgent to develop and apply new materials, and put the research and development and application of materials at the top of scientific research work. So far, the new materials that have received more and more attention are composite materials, and various advanced composite materials account for a considerable proportion of new materials. These composite materials can not only meet the weight reduction requirements of structural design, but also have some u...

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Application Information

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IPC IPC(8): G01N3/08
CPCG01N3/08G01N2203/0003G01N2203/0017G01N2203/0019G01N2203/0073G01N2203/0075G01N2203/0676G01N2203/0682
Inventor 孟维迎李宇鹏张啸尘
Owner SHENYANG JIANZHU UNIVERSITY
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