摘要
基于三维有限元分析结果,提出了机身对接修理构型的疲劳与裂纹扩展寿命快速评估方法。考虑摩擦及铆钉预紧力,建立了不同修理构型三维有限元模型。基于计算结果得到了铆钉钉载随孔边裂纹长度变化的函数表达式。基于权函数法提出了对接构型孔边裂纹应力强度因子快速分析方法,并建立了相应的裂纹扩展寿命分析方法。对4种不同对接修理构型进行疲劳和裂纹扩展寿命分析,结果表明:危险位置均位于蒙皮头排铆钉,不同修理构型的头排铆钉钉载差异较大;增加铆钉排数和阶梯状布置加强板可降低头排铆钉钉载;减小头排铆钉钉载可显著提高疲劳寿命,但对裂纹扩展寿命改善效果较小。
A rapid analysis method of fatigue life and crack propagation life for repaired butt-joint is proposed based on three-dimensional finite element analysis.Considering the friction and rivet clamping force,the three-dimensional finite element models of different repaired configurations are established.An approximate model is constructed to represent the variation of pin load with the increase of crack length based on the analysis result.A rapid analysis method for calculation of the stress intensity factor for cracks in butt-joint is proposed based on weight function method,from which a predictive method for the crack propagation life is then developed.The fatigue life and crack propagation life of 4 repaired configurations are analyzed,Results shown that the dangerous positions are all located at the first rivet row in skin,and the pin load of different configurations is quite different.In addition,increasing the number of rivet rows and adopting stepped patch can reduce the pin load of the first rivet row.The fatigue life can be significantly enhanced by reducing the pin load of the first rivet row,while the improvement for crack propagation life is less significant.
作者
邹君
柴崇博
董登科
常文魁
冯振宇
ZOU Jun;CHAI Chongbo;DONG Dengke;CHANG Wenkui;FENG Zhenyu(College of Safety Science and Engineering,Civil Aviation University of China,300300 Tianjin,China;Key Laboratory of Civil Aircraft Airworthiness Technology,CAAC,300300 Tianjin,China;Aircraft Strength Research Institute of China,710065 Xi'an,China)
出处
《应用力学学报》
CAS
CSCD
北大核心
2023年第6期1257-1262,共6页
Chinese Journal of Applied Mechanics
基金
航空科学基金资助项目(No.2017ZD67002)
科研启动金资助项目(No.2017QD10S)。
关键词
对接构型
疲劳寿命
裂纹扩展寿命
铆接修理
快速评估
butt-joints
fatigue life
crack propagation life
riveted repair
rapid assessment method
