Individual aircraft life monitoring： An engineering approach for fatigue damage evaluation

作     者：Rui JIAO Xiaofan HE Yuhai LI 

作者机构：School of Aeronautic Science and Engineering Beihang University Beijing 100083 China A viation Industry Corporation of China Beijng 100022 China 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2018年第31卷第4期

页      面：727-739页

核心收录：

学科分类：08[工学] 0802[工学-机械工程] 0825[工学-航空宇航科学与技术] 0814[工学-土木工程] 0801[工学-力学（可授工学、理学学位）] 082301[工学-道路与铁道工程] 0823[工学-交通运输工程] 

基　　金：support from National Natural Science Foundation of China (No. 11772027) National Key Research and Development Program of China (No. 2017YFB1104003) Aeronautical Science Foundation of China (No. 28163701002) 

主　　题：Fatigue damage Fatigue monitoring Fatigue test Scatter factor S-N curve 

摘      要：Individual aircraft life monitoring is required to ensure safety and economy of aircraft structure, and fatigue damage evaluation based on collected operational data of aircraft is an integral part of it. To improve the accuracy and facilitate the application, this paper proposes an engineering approach to evaluate fatigue damage and predict fatigue life for critical structures in fatigue monitoring. In this approach, traditional nominal stress method is applied to back calculate the S-N curve parameters of the realistic structure details based on full-scale fatigue test data. Then the S-N curve and Miner＇s rule are adopted in damage estimation and fatigue life analysis for critical locations under individual load spectra. The relationship between relative small crack length and fatigue life can also be predicted with this approach. Specimens of 7 B04-T74 aluminum alloy and TA15 M titanium alloy are fatigue tested under two types of load spectra, and there is a good agreement between the experimental results and analysis results. Furthermore, the issue concerning scatter factor in individual aircraft damage estimation is also discussed.