摘要
为探究CFRP/TC4叠层结构不同叠层顺序下的材料去除过程、两相材料及界面损伤形成机理,建立CFRP/TC4叠层结构钻削的有限元模型,并通过实验获得的轴向力、缺陷类型验证了模型的正确性。研究结果表明,当钻削顺序为CFRP→TC4时,CFRP入口处产生以撕裂型为主的入口分层,CFRP出口处未产生明显的推出分层,但在钻头的持续旋转作用下形成界面分层;当钻削顺序为TC4→CFRP时,当钛合金待切削层厚度较低时,轴向推力超过CFRP层间界面结合强度时产生界面相失效,TC4→CFRP的界面损伤比CFRP→TC4更加严重;TC4→CFRP主要形成以张开型、滑开型裂纹扩展为主的推出分层。
In this paper,the finite element model of drilling CFRP/TC4 stack structure was established to explore the material removal process,two-phase material and interface damage formation mechanism under different stacking sequences of CFRP/TC4 stack structure.The correctness of the model was verified by thrust force and defect type obtained from CFRP/TC4 stack drilling experiment.The results show that when the drilling sequence is CFRP→TC4,the entrance delamination dominated by tear occurs at the entrance of CFRP.There is no obvious push out delamination at the CFRP exit,but the interface delamination is formed under the continuous rotation of the drill.When the drilling sequence is TC4→CFRP,if the thickness of titanium alloy to be cut is low and the thrust force exceeds the interfacial bonding strength between CFRP layers,the interfacial phase failure occurs.The interface damage of TC4→CFRP is more serious than that of CFRP→TC4.TC4→CFRP mainly forms push out delamination with open and sliding crack propagation.
作者
李云义
李树健
李鹏南
王春浩
赵永锋
LI Yunyi;LI Shujian;LI Pengnan;WANG Chunhao;ZHAO Yongfeng(Department of Mechanical and Electrical Engineering,Hunan Jiuyi Technical College,Yongzhou 425000;School of Mechanical Engineering,Hunan University of Science and Technology,Xiangtan 411201)
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2023年第6期32-39,共8页
Aerospace Materials & Technology
基金
国家自然科学基金(51975208、51775184、51905169)。
