带口盖加筋复合材料壁板剪切性能

郭俊; 关志东; 黎增山; 卓越

doi:10.13801/j.cnki.fhclxb.20150624.001

带口盖加筋复合材料壁板剪切性能

北京航空航天大学航空科学与工程学院, 北京 100083

详细信息

通讯作者:
关志东, 博士, 教授, 博士生导师, 研究方向为复合材料结构设计、复合材料力学。E-mail: D5062010@163.com

中图分类号: TB330.1
计量
- 文章访问数: 898
- HTML全文浏览量: 110
- PDF下载量: 428
出版历程
- 收稿日期: 2015-03-09
- 修回日期: 2015-06-08
- 刊出日期: 2016-02-14

Shear properties of composite stiffened panel with cover

School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China

摘要

摘要: 采用试验和有限元方法研究了带口盖加筋复合材料壁板的剪切性能。在带口盖加筋复合材料壁板有限元模型的基础上, 去掉口盖, 对不带口盖的大开口加筋复合材料壁板进行了有限元模拟分析, 以此研究口盖对带口盖加筋复合材料壁板的影响。试验和数值计算结果表明: 当达到屈曲载荷时, 带口盖加筋复合材料壁板各个区域同步发生屈曲, 最终破坏位置位于加强筋条以外的复合材料壁板区域; 去掉口盖后, 结构的刚度以及承载能力降低, 结构的应力集中点以及损伤起始位置均发生变化, 破坏时失稳形式无明显变化, 均为局部失稳。
- 口盖 /
- 加筋 /
- 复合材料 /
- 剪切试验 /
- 有限元分析
Abstract: The shear properties of composite stiffened panel with cover were investigated through tests and finite element methods. Based on the finite element model of composite stiffened panel with cover and by removing cover, the finite element simulation analysis was conducted on large opening composite stiffened panel without cover to investigate the effects of cover on composite stiffened panel with cover. Test and numerical calculation results reflect that different regions of composite stiffened panel with cover buckles simultaneously and the final failure position is at the composite panel area outside the stiffeners. When the cover is removed, the rigidity and load-carrying capacity of structure get reduced, and the stress concentration point and location of the initial damage of structure both get shifted. The failure modes show no obvious change when failure, both are local buckling.
- cover /
- stiffener /
- composites /
- shear test /
- finite element analysis

HTML全文

参考文献(0)

施引文献(2)

期刊类型引用(2)

1.	田童，李建乐，邓德双，曾旭，林奎旭，董珊珊，杨雷，徐浩，杨正岩，武湛君. 飞行器结构健康监测技术研究进展. 航空制造技术. 2024(13): 41-67+98 . 百度学术
2.	曾旭，邓德双，杨红娟，杨正岩，马书义，杨雷，武湛君. 航空结构低速冲击监测技术研究进展. 航空学报. 2024(23): 100-127 . 百度学术