Volume 36, Number 1, February 2018
|Page(s)||91 - 95|
|Published online||18 May 2018|
Initial Fatigue Quality Assessment for Aircraft Wing Panel Fastener Hole
An effective initial fatigue quality assessment method is presented in order to verify aircraft wing panel fastener hole whether to satisfy the design requirements. Firstly, after finishing fatigue test of bolted specimens and fatigue fracture interpretation, the time to crack initiation distributions under 3 stress levels are obtained and then a general equivalent initial flaw size distribution is established. Secondly, a method of fatigue life prediction with 95% reliability is proposed. Finally, the initial fatigue quality of aircraft wing panel fastener hole is evaluated based on the economic life criterion and double 95% EIFS value. The results show that the initial fatigue quality of the given aircraft wing panel fastener hole satisfies the design requirements.
Key words: design of experiments / fastener hole / initial fatigue quality / time to crack initiation / equivalent initial flaw size / economical life
关键字 : 试验设计 / 紧固孔 / 原始疲劳质量 / 裂纹萌生时间 / 当量初始缺陷尺寸 / 经济寿命
© 2018 Journal of Northwestern Polytechnical University. All rights reserved.
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