摘要
为探究薄板的屈曲破坏性能,以飞机机身设计中最常用的铝合金薄板结构为研究对象,利用金属材料塑性修正系数分析矩形薄板的屈曲失效,得到在均布压力和不同约束条件下矩形薄板的临界屈曲应力。数值仿真算例及其有限元计算结果对比,验证该方法的正确性。
To study the buckling failure behavior of thin plate,the aluminum alloy thin plate structure which is most commonly used in aircraft fuselage design is selected as the object,and the analysis of buckling failure of rectangular thin plate is carried out by using plastic correction coefficient of metal material.The critical buckling stresses of rectangular thin plate under uniform pressure and different constraints are obtained.The numerical results of a simulation case are compared with its finite element results,and it shows that the method is accurate.
作者
童杰
李娟
张冰珂
苏江
侯鹏飞
TONG Jie;LI Juan;ZHANG Bingke;SU Jiang;HOU Pengfei(College of Mechanical and Automobile,Guangdong Polytechnic of Science and Technology,Zhuhai 519090,Guangdong,China;Department of Engineering Mechanics,Hunan University,Changsha 410082,China)
出处
《计算机辅助工程》
2020年第2期1-4,27,共5页
Computer Aided Engineering
基金
广州市科技计划项目(201904010204,201707010171,201707010172)
广东省教育厅特色创新项目(2018GKTSCX107,2017GKTSCX015,2017GKTSCX016)
广东省教育厅应用研究重大项目(2017GKZDXM003)
广东科学技术职业学院校级基金培育项目(XJPY2018001)。
关键词
塑性修正
薄板
屈曲应力
失效
plastic modification
thin plate
buckling stress
failure
