复合材料板拉/压-剪复合载荷屈曲相关方程

doi:10.7527/S1000-6893.2021.25417

固体力学与飞行器总体设计

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复合材料板拉/压-剪复合载荷屈曲相关方程

陈向明¹, 陈普会², 孙侠生³, 王彬文¹, 王喆¹, 张辉¹, 柴亚南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. 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)

摘要/Abstract

摘要： 利用轴向拉伸/压缩和面内剪切载荷构建了一个相互作用函数，并将其通过幂级数展开成二次多项式，利用单轴试验测试的复合材料板屈曲载荷，基于数学原理和合理的假设，推导确定了多项式的各项待定系数，构建了轴向拉伸/压缩和剪切复合载荷下的复合材料板屈曲相关方程，从数学上理性地解决了传统屈曲相关方程不适用于复合材料板（尤其是非均衡铺层板）的问题。利用提出的相关方程预测了4种不同的非均衡铺层复合材料板在轴向拉伸/压缩和剪切载荷作用下的屈曲相关曲线，并与有限元特征值法的模拟结果进行了对比，两者具有很好的一致性，而对于传统相关方程，其铺层的非均衡性越大则预测误差越大。最后通过均衡铺层的复合材料加筋壁板的压剪复合试验进一步证明了提出的相关方程的有效性。

关键词: 复合材料, 非均衡, 复合载荷, 屈曲, 相关方程

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.

Key words: composites, unbalanced, combined loads, buckling, interaction formulae

中图分类号:

陈向明, 陈普会, 孙侠生, 王彬文, 王喆, 张辉, 柴亚南. 复合材料板拉/压-剪复合载荷屈曲相关方程[J]. 航空学报, 2021, 42(12): 225417-225417.

CHEN Xiangming, CHEN Puhui, SUN Xiasheng, WANG Binwen, WANG Zhe, ZHANG Hui, CHAI Yanan. Buckling interaction formulae of composite plates under combined axial compression/tension and shear loads[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(12): 225417-225417.

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复合材料板拉/压-剪复合载荷屈曲相关方程

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

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