TC4钛合金飞机结构件开缝衬套冷挤压技术的探索  

Exploration of Cold Extrusion Technology for Slotted Bushing of TC4 TitaniumAlloyAircraft Structural Parts

作　　者：周瑜 刘康伟 周宝 ZHOU Yu;Liu Kangwei;ZHOU Bao(Chengdu Aeronautic Polytechnic,Chengdu 610100,China)

机构地区：[1]成都航空职业技术学院,成都610100

出　　处：《成都航空职业技术学院学报》2024年第1期51-55,共5页Journal of Chengdu Aeronautic Polytechnic

摘　　要：现代飞机机体上有百万颗连接件,连接件之间所对应的连接孔在运行过程中会产生疲劳。大量试验数据显示,飞机机体损伤中,绝大部分都来自机械连接处。开缝衬套冷挤压增强钻孔工艺主要应用于飞机制造、维修等行业,主要用于改善航空结构孔的疲劳寿命。通过仿真分析,研究开缝衬套冷挤压增强孔残余应力分布情况和疲劳寿命。采用有限元模型、分析、测试,确定开缝衬套冷挤压增强工艺中的TC4钛合金相对挤压率为6%和8%左右,疲劳寿命增益效应显著。There are millions of connections in the modern airplane fuselage,and every connection hole is a potential source of fatigue.A large amount of experimental data shows that most of the damage to the aircraft fuselage comes from the mechanical connections.The cold-extrusion enhanced drilling process for open-seam bushings is mainly used in the aircraft manufacturing and maintenance industries,and it is mainly used to improve the fatigue life of holes in aerospace structures.Through simulation analysis,the residual stress distribution and fatigue life of the cold-extruded reinforced holes of open-seam bushings are investigated.Using finite element modeling,analysis,and testing,it is determined that the relative extrusion rate of TC4 titanium alloy in the open seam bushing cold extrusion enhancement process is about 6%and 8%,and the fatigue life gain effect is significant.

关 键 词：疲劳 冷挤压 疲劳寿命 

分 类 号：TG376.3[金属学及工艺—金属压力加工]