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

作　　者：王新年 赵伟[2] 吴师[2] 谢宗蕻[2] 

机构地区：[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

出　　处：《南京航空航天大学学报》2017年第6期812-819,共8页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：针对某型支线客机复合材料平尾加筋壁板结构选型需求,采用p型有限元分析手段考察了不同筋条与蒙皮剖面面积比例对复合材料平尾加筋壁板承受面内剪切性能的影响,并采用试验测试对有限元预测结果进行验证。研究表明:p型有限元分析方法可以高效的完成复合材料平尾加筋壁板剪切稳定性分析,预测的结果较为准确,采用的分析方法可行、分析模型准确有效;复合材料平尾加筋壁板在剪切载荷作用下的典型破坏模式为蒙皮剪切失稳所导致的蒙皮和筋条界面分离;在筋条剖面面积/蒙皮剖面面积近似相同情况下,复合材料平尾加筋壁板的蒙皮截面积决定其承受剪切载荷的性能,但对其屈曲模态几乎没有影响。In order to determine cross-section size parameters of the tail panel of a certain aircraft and validate the reliability and accuracy of the p-version finite element method, the buckling behavior of stiffened 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 obtained, 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 approximately 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 

分 类 号：TB332[一般工业技术—材料科学与工程]