复合材料板拉/压-剪复合载荷屈曲相关方程

1. 1. 中国飞机强度研究所, 西安 710065;
2. 南京航空航天大学 航空学院, 南京 210016;
3. 中国航空研究院, 北京 100029
• 收稿日期:2021-02-25 修回日期:2021-03-16 发布日期:2021-05-10
• 通讯作者: 陈向明 E-mail:asrichenxm@avic.com
• 基金资助:
民机科研项目（MJ-2015-F-038，MJ-2016-F-01）

Buckling interaction formulae of composite plates under combined axial compression/tension and shear loads

CHEN Xiangming1, CHEN Puhui2, SUN Xiasheng3, WANG Binwen1, WANG Zhe1, ZHANG Hui1, CHAI Yanan1

1. 1. Aircraft Strength Research Institute of China, Xi'an 710065, China;
2. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
3. Chinese Aeronautical Establishment, Beijing 100029, China
• Received:2021-02-25 Revised:2021-03-16 Published:2021-05-10
• Supported by:
Civil Aircraft Scientific Research Project (MJ-2015-F-038,MJ-2016-F-01)

Abstract: An interaction function is constructed using axial tension/compression and in-plane shear loads, and further expanded into a quadratic polynomial by power series. Based on mathematical principles and reasonable hypotheses, the polynomial coefficients are determined using the buckling load of the composite plate measured by a uniaxial test. The buckling interaction formulae of composite plates under combined axial tension/compression and shear loads are then established. The problem that the traditional buckling interaction formulae are not suitable for composite plates (particularly for unbalanced laminates) is thereby solved mathematically and rationally. The buckling interaction curves of four different unbalanced ply composite plates under axial tension/compression and shear loads are predicted with the interaction formulae proposed in this paper, and compared with the simulation results of the finite element eigenvalue method. The comparison shows a good agreement. For the traditional interaction formulae, the prediction error increases with the increasing unbalanced degree of composite laminates. Finally, the validity of the proposed interaction formulae is verified by the compression shear tests of composite stiffened panels with balanced laminates.