Prediction of Fatigue Cracks Using Gamma Function

Q4 Engineering

Fatigue of Aircraft Structures Pub Date : 2023-04-20 DOI:10.2478/fas-2022-0004

Abdelfetah Moussouni, M. Benachour, N. Benachour

引用次数: 0

Abstract

Abstract In the present study it has been endeavored to estimate the fatigue crack propagation in V-notch Charpy specimens of 2024 T351 Al-alloy. For this purpose, a new application of fatigue crack growth (FCG) is developed based on the “Gamma function.” Experimental fatigue tests are conducted for stress ratios from 0.1 to 0.5 under constant amplitude loading. The empiric model depends principally on physical parameters and materials’ properties in non-dimensional form. Deviation percentage, prediction ratio, and band error are used for validation of the performance of the fatigue life. The results determined from Gamma application are in good agreement with experimental FCG rates and those obtained from using Paris law.

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利用伽玛函数预测疲劳裂纹

摘要本研究试图估算2024 T351铝合金V型缺口夏比试样的疲劳裂纹扩展。为此，基于“伽玛函数”开发了疲劳裂纹扩展（FCG）的新应用。在恒定振幅载荷下，对0.1至0.5的应力比进行了实验疲劳试验。经验模型主要取决于无量纲形式的物理参数和材料特性。偏差百分比、预测率和带误差用于验证疲劳寿命的性能。Gamma应用的结果与实验FCG速率和使用Paris定律获得的结果非常一致。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

Fatigue of Aircraft Structures Engineering-Safety, Risk, Reliability and Quality

CiteScore

0.40

自引率

0.00%

发文量

期刊介绍： The publication focuses on problems of aeronautical fatigue and structural integrity. The preferred topics include: full-scale fatigue testing of aircraft and aircraft structural components, fatigue of materials and structures, advanced materials and innovative structural concepts, damage tolerant design of aircraft structure, life extension and management of ageing fleets, structural health monitoring and loads, fatigue crack growth and life prediction methods, NDT inspections, airworthiness considerations.