缝纫泡沫夹芯复合材料板的稳定性分析

马元春; 俸翔; 卢子兴; 卢文书; 王伯平

缝纫泡沫夹芯复合材料板的稳定性分析

1.
北京航空航天大学航空科学与工程学院, 北京 100191;
2.
沈阳飞机设计研究所, 沈阳 110035;
3.
空军航空大学航空理论系, 长春 130022

基金项目: 国家自然科学基金(10932001, 11072015)

详细信息

通讯作者:
卢子兴, 教授, 博士生导师, 研究方向为泡沫材料力学及复合材料结构强度 E-mail: luzixing@buaa.edu.cn

中图分类号: TB332; TB330.1
计量
- 文章访问数: 1803
- PDF下载量: 844
- 被引次数: 0
出版历程
- 收稿日期: 2010-03-08
- 修回日期: 2010-07-06
- 刊出日期: 2011-04-15

Stability analysis of stitched foam-core composite sandwich plates

1.
School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China;
2.
Shenyang Aircraft Design and Research Institute, Shenyang 110035, China;
3.
Department of Flight Theory, Aviation University of Air Force, Changchun 130022, China

摘要

摘要: 整体屈曲是缝纫复合材料夹芯板的一种重要失效模式。考虑到缝纫夹芯复合材料板一般较厚且面板与芯层厚度相差较大, 缝纫工艺对夹芯板刚度影响较大的特点, 基于高阶剪切理论, 编制了缝纫泡沫夹芯复合材料板稳定性分析的有限元程序。利用该程序对多个算例进行了计算, 所得临界屈曲应力与文献及试验结果吻合很好。同时, 讨论了不同边界条件下缝纫泡沫夹芯复合材料板稳定性随缝纫参数(包括针距、行距和缝纫针半径)以及结构参数(包括面板铺层角、芯层厚度和缝纫夹芯板边长)的变化规律。
- 缝纫 /
- 复合材料 /
- 泡沫夹芯板 /
- 屈曲 /
- 高阶剪切
Abstract: The global buckling is one of the important failure modes of stitched foam-core composite sandwich plates. Considering the characters that the thicknesses of stitched foam-core composite sandwich are always relatively large and the thicknesses of face panel and core are obviously different, in addition that the stitching process influences the property evidently, the finite element program for stability analysis of stitched foam-core composite sandwich plates was written based on higher-order shear deformation theory. The calculation results revealed the consistency with the results in references and experiments. The relationship between the stability of stitched foam-core composite sandwich plates and stitching parameters (including step, space and radius of needle) and structural parameters (including stacking angles in face panel, thickness of the core and length of the sandwich) was discussed.
- stitched /
- composite /
- foam-core sandwich /
- buckling /
- higher-order shear