工程科学学报.第43卷.第3期：442-450.2021年3月 Chinese Journal of Engineering,Vol.43,No.3:442-450,March 2021 https://doi.org/10.13374/j.issn2095-9389.2020.01.13.005;http://cje.ustb.edu.cn 飞机机翼缘条紧固孔细节原始疲劳质量评估方法 高志刚四，何宇廷，马斌麟，张天宇 空军工程大学航空工程学院，西安710038 ☒通信作者.E-mail:gaozhigang666@126.com 摘要为了对飞机机翼缘条紧固孔细节原始疲劳质量进行评估，本文首先对飞机机翼缘条结构中常用的BXXX铝合金紧 固孔试件分别开展了高、中、低3种应力水平下的疲劳试验，通过断口判读和反推得到3组关于裂纹长度a和疲劳寿命1的 (α-)数据，在此基础上应用当量初始缺陷尺寸(EFS)控制方程对每个试件的EIFS值进行计算并初步评估，验证了在不同应 力水平下紧固孔结构细节的EFS无显著性差异：得到了紧固孔结构细节的裂纹萌生时间(TTCI)分布，在指定应力水平下对 紧固孔结构细节95%置信水平下的经济寿命进行预测，并与设计寿命进行对比，提出了一种不同超越概率P下的结构细节 当量初始缺陷尺寸模型，基于给定5%的裂纹超越概率，对结构细节的通用EFS分布进行评估.通过以上对飞机机翼缘条紧 固孔细节原始疲劳质量的三重评估，得到综合评估结果：飞机机翼缘条紧固孔细节原始疲劳质量满足要求. 关键词机翼缘条；紧固孔：原始疲劳质量：当量初始缺陷尺寸：裂纹超越概率：质量评估 分类号V215.5 Evaluation method of initial fatigue quality of aircraft wing flange fastener holes GAO Zhi-gang,HE Yu-ting,MA Bin-lin,ZHANG Tian-yu Aeronautics Engineering College,Air Force Engineering University,Xi'an 710038,China Corresponding author,E-mail:gaozhigang666@126.com ABSTRACT On analyzing the details of kinetic links of parts and structures of aircrafts,one can find few bad links.But fastener hole is the weakest link where abnormal stress is produced and initiation of crack occurs.The initial fatigue quality of aircraft wing flange fastener is the key parameter,which affects the durability of aircraft structure.The initial fatigue quality of structural details is usually characterized by the equivalent initial defect size (EIFS)and the time to crack initiation (TTCI).To evaluate the initial fatigue quality of aircraft wing flange fastener hole details,this paper first carried out fatigue tests at high-,medium-and low-stress levels on the BXXX aluminum alloy fastener hole specimens generally used in aircraft wing flange structures,and obtained three groups of()datasets about crack length a and fatigue life tthrough fracture interpretation and back stepping.On this basis,the EIFS governing equation was used to evaluate the EIFS value of each specimen,and it is found out that there is no significant difference in equivalent initial flaw size under different stress levels;TTCI distribution of structural details is obtained,and the economic life of specified stress level under 95% confidence level of fastener hole structural details was predicted,and compared with the design life;a structural detail equivalent to initial flaw size model under different exceedance probability P was proposed.Based on the given 5%crack exceedance probability,the general EIFS distribution of structural details was evaluated.The comprehensive evaluation results were obtained through the above triple evaluation of the initial fatigue quality of the fastener hole details:the general EIFS distribution and the EIFS value of each test piece are less than the allowable value,and the economic life is greater than the allowable value,so the original fatigue quality of the details of the fastening holes of the aircraft flange meets the stringent requirements. 收稿日期：2020-01-13 基金项目：国家自然科学基金资助项目(51805538)：陕西省自然科学基础研究计划资助项目(2020JQ-476):装备预研领域基金资助项目 (61409220202)飞机机翼缘条紧固孔细节原始疲劳质量评估方法 高志刚苣，何宇廷，马斌麟，张天宇 空军工程大学航空工程学院，西安 710038 苣通信作者，E-mail：gaozhigang666@126.com 摘    要    为了对飞机机翼缘条紧固孔细节原始疲劳质量进行评估，本文首先对飞机机翼缘条结构中常用的 BXXX 铝合金紧 固孔试件分别开展了高、中、低 3 种应力水平下的疲劳试验，通过断口判读和反推得到 3 组关于裂纹长度 a 和疲劳寿命 t 的 （a−t）数据，在此基础上应用当量初始缺陷尺寸（EIFS）控制方程对每个试件的 EIFS 值进行计算并初步评估，验证了在不同应 力水平下紧固孔结构细节的 EIFS 无显著性差异；得到了紧固孔结构细节的裂纹萌生时间（TTCI）分布，在指定应力水平下对 紧固孔结构细节 95% 置信水平下的经济寿命进行预测，并与设计寿命进行对比，提出了一种不同超越概率 P 下的结构细节 当量初始缺陷尺寸模型，基于给定 5% 的裂纹超越概率，对结构细节的通用 EIFS 分布进行评估. 通过以上对飞机机翼缘条紧 固孔细节原始疲劳质量的三重评估，得到综合评估结果：飞机机翼缘条紧固孔细节原始疲劳质量满足要求. 关键词    机翼缘条；紧固孔；原始疲劳质量；当量初始缺陷尺寸；裂纹超越概率；质量评估 分类号    V215.5 Evaluation method of initial fatigue quality of aircraft wing flange fastener holes GAO Zhi-gang苣 ，HE Yu-ting，MA Bin-lin，ZHANG Tian-yu Aeronautics Engineering College, Air Force Engineering University, Xi'an 710038, China 苣 Corresponding author, E-mail: gaozhigang666@126.com ABSTRACT    On analyzing the details of kinetic links of parts and structures of aircrafts, one can find few bad links. But fastener hole is the weakest link where abnormal stress is produced and initiation of crack occurs. The initial fatigue quality of aircraft wing flange fastener is the key parameter, which affects the durability of aircraft structure. The initial fatigue quality of structural details is usually characterized by the equivalent initial defect size (EIFS) and the time to crack initiation (TTCI). To evaluate the initial fatigue quality of aircraft wing flange fastener hole details, this paper first carried out fatigue tests at high-, medium- and low-stress levels on the BXXX aluminum alloy fastener hole specimens generally used in aircraft wing flange structures, and obtained three groups of (a−t) datasets about crack length a and fatigue life t through fracture interpretation and back stepping. On this basis, the EIFS governing equation was used to evaluate the EIFS value of each specimen, and it is found out that there is no significant difference in equivalent initial flaw size under different stress levels; TTCI distribution of structural details is obtained, and the economic life of specified stress level under 95% confidence level of fastener hole structural details was predicted, and compared with the design life; a structural detail equivalent to initial flaw size model under different exceedance probability P was proposed. Based on the given 5% crack exceedance probability, the general EIFS distribution of structural details was evaluated. The comprehensive evaluation results were obtained through the above triple evaluation of the initial fatigue quality of the fastener hole details: the general EIFS distribution and the EIFS value of each test piece are less than the allowable value, and the economic life is greater than the allowable value, so the original fatigue quality of the details of the fastening holes of the aircraft flange meets the stringent requirements. 收稿日期: 2020−01−13 基金项目: 国家自然科学基金资助项目（51805538）；陕西省自然科学基础研究计划资助项目（2020JQ-476）；装备预研领域基金资助项目 （61409220202） 工程科学学报，第 43 卷，第 3 期：442−450，2021 年 3 月 Chinese Journal of Engineering, Vol. 43, No. 3: 442−450, March 2021 https://doi.org/10.13374/j.issn2095-9389.2020.01.13.005; http://cje.ustb.edu.cn