飞机紧固孔周疲劳裂纹扩展微观分析  

Microscopic Analysis of Fatigue Crack Propagation around Connection Holes of Aircraft Fasteners

作　　者：王锡芝 张剑伟 刘贞言 帅馨禹 WANG Xi-zhi;ZHANG Jian-wei;LIU Zhen-yan;SHUAI Xin-yu(School of Mechanical Engineering,Liaoning Shihua University,Fushun Liaoning,110179;School of Safety Engineering,Shenyang Aerospace University,Shenyang Liaoning,1101361;School of Intelligence and Engineering,Shenyang City University,Shenyang Liaoning,110112)

机构地区：[1]辽宁石油化工大学机械工程学院,辽宁抚顺110179 [2]沈阳航空航天大学安全工程学院,辽宁沈阳1101361 [3]沈阳城市学院智能与工程学院,辽宁沈阳110112

出　　处：《山西大同大学学报（自然科学版）》2023年第5期22-26,共5页Journal of Shanxi Datong University(Natural Science Edition)

基　　金：辽宁省教育厅系列项目[LJKZ0168]。

摘　　要：为揭示飞机紧固孔周疲劳微裂纹起裂和扩展的行为过程,运用分子动力学软件LAMMPS对飞机紧固件连接孔周疲劳裂纹扩展进行微观尺度数值模拟研究。分析了预制裂纹长度、环境温度、纳米板材料和裂纹扩展方向上的晶向对裂纹起裂和扩展行为的影响。采用微观方法对宏观裂纹进行分析,丰富了人们对纳米级尺寸裂纹的认识与理解。In this paper,to reveal the initiation and propagation process of fatigue microcracks around aircraft fastener holes,molecular dynamics software LAMMPS was used to conduct microscale numerical simulation research on fatigue crack propagation around aircraft fastener connection holes.The effects of prefabricated crack length,ambient temperature,nano-plate material and crystal direction of crack propagation on crack initiation and propagation behavior were analyzed.The macroscopic crack is analyzed by the microscopic method,which enriches the knowledge and understanding of the nanoscale crack.

关 键 词：紧固孔 疲劳裂纹 扩展 微观尺度 

分 类 号：V11[航空宇航科学与技术—人机与环境工程]