摘要
钛合金蜂窝夹层结构在制备或使用过程中可能会产生面板裂纹损伤。采用试验和有限元结合的方法研究了单侧面板裂纹损伤对钛合金蜂窝夹层结构弯曲性能的影响。结果显示:单侧面板裂纹损伤会明显降低钛合金蜂窝夹层结构面板弯曲强度,弯曲强度近似随裂纹长度的增加而线性降低;有限元模型能够准确预测结构的破坏模式和破坏强度,预测得到的面板弯曲强度与试验结果最大偏差仅为6%。采用的有限元方法可用于含面板裂纹损伤的钛合金蜂窝壁板结构弯曲性能的工程预估。
During the manufacturing process and service period,the crack damage may occur in the facesheet of titanium honeycomb sandwich structure.The influence of one side facesheet crack damage on flexural properties of titanium honeycomb sandwich structures was studied experimentally and numerically.The research results show that the flexural strength of titanium honeycomb sandwich structure with one side facesheet crack damage is obviously lower than that of the structure without crack damage,and the flexural strength decreases linearly with the increase of the crack length;the finite element models can accurately predict the failure mode and fracture strength of the structures,and the maximum deviation between the predicted results and the test result is only 6%.The finite element analysis method can be used to predict the flexural strength of titanium honeycomb sandwich structure with facesheet crack damage in the engineering estimate.
作者
岳喜山
闫群
赵伟
谢宗蕻
YUE Xishan;YAN Qun;ZHAO Wei;XIE Zonghong(School of Astronautics,Northwestern Polytechnical University,Xi'an 710072,China;Aeronautical Key Laboratory for Welding and Joining Technologies,AVIC Manufacturing Technology Institute,Beijing 100024,China;Structure Department,Shenyang Aircraft Design and Research Institute,Shenyang 110035,China;School of Aeronautics and Astronautics,Sun Yat-Sen University,Guangzhou 510275,China)
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2020年第11期2018-2025,共8页
Journal of Beijing University of Aeronautics and Astronautics
关键词
钛合金蜂窝夹层结构
面板裂纹
三点弯曲试验
弯曲强度
有限元
titanium honeycomb sandwich structure
facesheet crack
three-point bending test
flexural strength
finite element
