南京航空航天大学学报2017，Vol.49Issue(6)：812-819,8.DOI:10.16356/j.1005-2615.2017.06.009
复合材料平尾加筋壁板剪切稳定性
Buckling Behaviour of Stiffened Composite Tail Panel Subjected to Shear Loading
王新年 1赵伟 2吴师 2谢宗蕻2
作者信息
- 1. 中航西飞民用飞机有限责任公司工程技术中心 ,西安 ,710089
- 2. 西北工业大学航天学院 ,西安 ,710072
- 折叠
摘要
Abstract
In order to determine cross-section size parameters of the tail panel of a certain aircraft and val-idate the reliability and accuracy of the p-version finite element method ,the buckling behavior of stiff-ened composite tail panel subjected to shear loading is studied by finite element analysis and testing . Study results show that the good correlations between the numerical results and the test results are ob-tained ,which proves that the model can be effectively used in the engineering applications related to the buckling behavior of stiffened composite panel subjected to shear loading ;the typical failure mode of the specimens is debonding of the skin and stringers ;when the cross-section area of the stringers/skin is ap-proximately equal ,the cross-section of the skin is the major factor effecting the buckling load ,but has little influence on the buckling modes .关键词
复合材料/加筋壁板/剪切/屈曲载荷Key words
composites/stiffened panels/shear/buckling loads分类
通用工业技术引用本文复制引用
王新年,赵伟,吴师,谢宗蕻..复合材料平尾加筋壁板剪切稳定性[J].南京航空航天大学学报,2017,49(6):812-819,8.
