摘要
为探究激光增材修复技术修复弹体结构裂纹的可行性和有效性,针对某型导弹舱段裂纹,借助有限元仿真手段对裂纹部位进行应力仿真,仿真结果为激光增材修复提供标准;用扩展有限元法(XFEM)对裂纹扩展进行模拟,再现裂纹产生过程;制备工艺试样,并对试样进行金相分析和拉伸测试,验证优化激光增材修复工艺,在保证舱段使用强度及要求前提下,借助激光增材修复技术完成舱段裂纹修复。结果表明:XFEM可准确模拟弹体裂纹的扩展过程;激光增材修复后的舱段满足导弹使用要求。
In order to explore the feasibility and effectiveness of laser additive repair technology to repair missile structural cracks,the finite element simulation method was used to simulate the stress of the cracked part for a certain type of missile’s cabin. The simulation results provided the repair standard for laser additive repair. The process of crack generation was reproduced by using the extended finite element method(XFEM)to simulate the crack propagation. The laser additive repair process was optimized by the preparation of the process sample and the metallographic and tensile tests of the sample. Under the premise of ensuring the strength of the cabin and the requirements for the use of the cabin,the crack repair of the cabin was completed by means of laser additive repair technology. The results show that XFEM can accurately simulate the expansion process of the projectile crack,and the cabin after laser additive repair can meet the using requirements of missile.
作者
王思明
朱红章
陈道斌
莫洋
谢君宇
WANG Siming;ZHU Hongzhang;CHEN Daobin;MO Yang;XIE Junyu(Factory of 5718 of the People's Liberation Army of China,Guilin 541003,China)
出处
《兵器材料科学与工程》
CAS
CSCD
北大核心
2020年第3期133-136,共4页
Ordnance Material Science and Engineering
作者简介
第一作者:王思明,男,硕士,主要研究方向为金属失效分析。E-mail:tlwsmlf@163.com。
