论文:2018,Vol:36,Issue(1):91-95
引用本文:
周俊杰, 王生楠. 飞机机翼壁板紧固孔细节原始疲劳质量评估[J]. 西北工业大学学报
Zhou Junjie, Wang Shengnan. Initial Fatigue Quality Assessment for Aircraft Wing Panel Fastener Hole[J]. Northwestern polytechnical university

飞机机翼壁板紧固孔细节原始疲劳质量评估
周俊杰, 王生楠
西北工业大学 航空学院, 陕西 西安 710072
摘要:
为验证某飞机机翼下壁板紧固孔细节原始疲劳质量是否满足设计要求,建立了评估其原始疲劳质量的有效方法。首先完成了螺栓连接试验件的疲劳试验及疲劳断口判读,建立了3种不同应力水平下的裂纹萌生时间分布,并在此基础上获得通用当量初始缺陷尺寸分布;提出一种可靠度为95%的细节疲劳寿命预测方法,基于经济寿命准则,实现对紧固孔细节的原始疲劳质量评估;最后使用此方法与基于满足双95%要求的EIFS值对飞机机翼下壁板紧固孔原始疲劳质量进行了评估,结果表明,该飞机机翼下壁板紧固孔细节原始疲劳质量满足设计要求。
关键词:    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   
Initial Fatigue Quality Assessment for Aircraft Wing Panel Fastener Hole
Zhou Junjie, Wang Shengnan
School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
Abstract:
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   
收稿日期: 2017-05-20     修回日期:
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作者简介: 周俊杰(1992-),西北工业大学博士研究生,主要从事结构疲劳、耐久性研究。
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