摘要
研究了带有孔边裂纹的铆钉孔航空试验件的疲劳失效行为。使用航空载荷谱进行疲劳加载,分别采用有限元分析工具进行理论研究;借助数字图像相关技术对三种裂纹模型的试验件进行疲劳试验研究,对比模拟值和试验值之间的关系,并给出了裂纹扩展及破坏的主要模型。结果表明:裂纹尖端圆形区域网格数量为8,裂纹尖端环形区域网格数量为32的组合为试验件模型的最优拓扑划分;随着裂纹条数的增多,危险性逐渐增大,试验件破坏模式由相邻裂纹间连通演变为裂纹扩展至边界;裂纹扩展方向可能发生轻微改变,导致疲劳寿命模拟值小于试验值,共线裂纹的试验件先按I型扩展,再按混合型扩展,裂纹间的塑性区连通是共线裂纹失效的主要模型。
The fatigue failurebehavior of rivet holes and cracksamong aeromaterialspecimens.Aero fatigue spectrumtheoreticalanalyses were studied by finite element tool;fatigue test research of three crack models were studied by Digital Image Correlation;the relation between tested value and simulated value wascompared,the main model of cracks expand and failure wasgiven.The results shows that,gridnumber of cracks pointed endcircularregion 8 and gridnumber of cracks pointed endannularregion 32 were the best grid rule of the aeromaterialspecimens;with the increase of cracks number,danger of failureraised,the failure model of the aeromaterialspecimens developed by expanding boundary but not adjoin cracks connection;the direction of cracks maybe change a little,result in simulated value less than tested value,the same line cracks were expanded first by I model,and then by I and II model,the main model of cracks expand and failure was plastic region connection.
作者
王艾伦
曹玮
尚进
Wang Ailun;Cao Wei;Shang Jin(AECC Commercial Aircraft Engine Manufacture Co.,Ltd.,Shanghai 200000,China)
出处
《科学技术创新》
2022年第3期1-5,共5页
Scientific and Technological Innovation
