北京航空航天大学学报 ›› 2019, Vol. 45 ›› Issue (3): 446-453.doi: 10.13700/j.bh.1001-5965.2018.0414

• 论文 • 上一篇    下一篇

激光焊接带口盖加筋壁板剪切性能分析

回丽1,2, 陈晓伟1, 周松1,2, 杨文军1,2, 王磊1,2   

  1. 1. 沈阳航空航天大学 机电工程学院, 沈阳 110136;
    2. 沈阳航空航天大学 航空制造工艺数字化国防重点学科实验室, 沈阳 110136
  • 收稿日期:2018-07-09 出版日期:2019-03-20 发布日期:2019-04-04
  • 通讯作者: 周松,E-mail:zhousong23@163.com E-mail:zhousong23@163.com
  • 作者简介:回丽,女,博士,教授。主要研究方向:航空材料与结构强度;周松,男,博士,讲师。主要研究方向:航空材料与结构强度。
  • 基金资助:
    辽宁省教育厅高等学校科学研究项目(L201633);沈阳航空航天大学航空制造工艺数字化国防重点学科实验室开放基金(SHSYS2017006);沈阳航空航天大学青年博士科研启动基金(18YB05)

Shear property analysis of laser welding stiffened panel with cover

HUI Li1,2, CHEN Xiaowei1, ZHOU Song1,2, YANG Wenjun1,2, WANG Lei1,2   

  1. 1. School of Mechatronics Engineering, Shenyang Aerospace University, Shenyang 110136, China;
    2. Key Laboratory of Fundamental Science for National Defence of Aeronautical Digital Manufacturing Process, Shenyang Aerospace University, Shenyang 110136, China
  • Received:2018-07-09 Online:2019-03-20 Published:2019-04-04

摘要: 针对双光束激光焊接带口盖加筋壁板开展了剪切稳定性试验,分析了带口盖加筋壁板在受剪状态下的屈曲载荷、屈曲形式、后屈曲承载能力及破坏形式。建立了壁板与剪切夹具的有限元模型,对壁板的剪切失稳形式及后屈曲承载能力进行仿真计算,并探究了口盖对加筋壁板的承载能力、应力变化及面外变形的影响。结果表明:带口盖加筋壁板在剪切状态下,当屈曲比达到1.95时,加筋壁板进入后屈曲,最终破坏载荷约为屈曲载荷的2.98倍。仿真与试验得到的载荷-位移曲线较为吻合,有限元法得到的屈曲载荷和破坏载荷与试验平均值误差分别为8.7%、1.02%。开口壁板的承载能力及刚度均下降,螺栓紧固口盖对加筋壁板的应力与面外变形影响较大。

关键词: 加筋壁板, 口盖, 剪切载荷, 有限元, 屈曲性能

Abstract: Shear stability test was carried out on the dual beam laser welding stiffened panel with cover. The buckling load, buckling form, post-buckling carrying capacity and failure modes of the stiffened panel with cover under shear loading were analyzed. A finite element method was utilized to model the stiffened panel and shear fixture. Simulation calculation of shear instability modes and post-buckling carrying capacity of stiffened panel. Meanwhile, the effects of cover on the carrying capacity, stress distribution and deformation of cutout stiffened panels were investigated. The results show that, in the sheared state of the stiffened panel with cover, when the buckling ratio reaches 1.95, the stiffened panel enters into post-buckling and the final failure load is approximately 2.98 times the buckling load. The load-displacement curves obtained from simulation and test are in good agreement, and the errors for the buckling loads and failure loads obtained from the numerical calculations compared with the test average value are 8.7% and 1.02%, respectively. The rigidity and load-carrying capacity of open stiffened panel reduce, and the bolt fastening cover has a great influence on the stress and out-of-plane deformation.

Key words: stiffened panel, cover, shear loading, finite elements, buckling property

中图分类号: 


版权所有 © 《北京航空航天大学学报》编辑部
通讯地址:北京市海淀区学院路37号 北京航空航天大学学报编辑部 邮编:100191 E-mail:jbuaa@buaa.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发