### 面内弯曲载荷作用下两边简支两边固支复合材料层合板的屈曲

1. 中国商飞上海飞机设计研究院, 上海 201210
• 收稿日期:2013-08-26 修回日期:2013-11-08 出版日期:2014-04-25 发布日期:2013-11-16
• 通讯作者: 陈保兴，Tel.：021-31225909 E-mail：chenbaoxing@comac.cc E-mail:chenbaoxing@comac.cc
• 作者简介:袁坚锋男，硕士研究生。主要研究方向：复合材料结构设计与分析。Tel：021-31225916 E-mail：yuanjianfeng0220@163.com；尼早男，博士，高工。主要研究方向：复合材料结构设计与分析。Tel：021-31225918 E-mail：nizao@comac.cc；陈保兴男，研究员。主要研究方向：飞机结构强度，复合材料力学与制造。Tel：021-31225909 E-mail：chenbaoxing@comac.cc

### Buckling of SSCC Composite Laminates Under In-plane Bending Load

YUAN Jianfeng, NI Zao, CHEN Baoxing

1. Shanghai Aircraft Design and Research Institute of COMAC, Shanghai 201210, China
• Received:2013-08-26 Revised:2013-11-08 Online:2014-04-25 Published:2013-11-16

Abstract:

In order to provide a stability analysis method of composite airframe structures, this paper presents a numerical solution method for the buckling of SSCC composite laminates (laminates having two parallel edges simply supported and the remaining parallel edges clamped) based on the Levy form series and finite-difference method. First, the deflection function is transformed to a discrete form by the finite-difference method; then, the system of equations is supplemented by the boundary conditions; finally, the critical buckling load is obtained through solving a generalized eigenvalue problem. Numerical examples are utilized to verify the present method on both isotropic and composite plates. The comparison of the present method and a finite element method (FEM) is conducted as well. The result shows that the present method has high accuracy and provides a new way for the buckling analysis of composite plates.