Hybrid carbon fiber reinforced polymer (CFRP)/titanium alloy (Ti) stacks are the key load-bearing components in the aircraft structure. However, CFRP/Ti stack has poor machinability and defects are easily caused in the drilling process, resulting in the reduction of fatigue performance for aircraft structural parts. In this paper, the effects of drilling strategies on static mechanical property and fatigue behavior of open-hole CFRP laminates were studied by quasi-static tensile tests and fatigue tests. When drilling CFRP/Ti stacks from CFRP side, due to the hole defects of CFRP caused by Ti6Al4V chips, the ultimate tensile strength and fatigue life of open-hole CFRP laminates decrease by 12.5 % and 75.8 %, respectively. When drilling CFRP/Ti stacks from Ti6Al4V side, due to the drilling defects of CFRP caused by the high drilling temperature and delamination, the ultimate tensile strength and fatigue life of open-hole CFRP laminates decrease by 5.8 % and 26.5 %, respectively.

混合碳纤维增强聚合物（CFRP）/钛合金（Ti）堆是飞机结构中的关键承重组件。然而，CFRP / Ti叠层的可加工性差，并且在钻孔过程中容易引起缺陷，从而降低了飞机结构部件的疲劳性能。本文通过准静态拉伸试验和疲劳试验研究了钻孔策略对开孔CFRP层压板静态力学性能和疲劳行为的影响。从CFRP侧钻CFRP / Ti叠层时，由于Ti6Al4V切屑引起的CFRP孔缺陷，开孔CFRP层压板的极限抗拉强度和疲劳寿命分别降低了12.5％和75.8％。从Ti6Al4V侧钻CFRP / Ti叠层时，