复合材料多墙盒段的设计与后屈曲性能

王春寿; 陈普会; 隋晓东; 王进; 柴亚南; 李新祥

复合材料多墙盒段的设计与后屈曲性能

1.
南京航空航天大学航空宇航学院, 南京 210016;
2.
沈阳飞机设计研究所, 沈阳 110035;
3.
中国飞机强度研究所, 西安 710065

详细信息

中图分类号: TB330.1
计量
- 文章访问数: 989
- HTML全文浏览量: 90
- PDF下载量: 906
出版历程
- 收稿日期: 2012-10-08
- 修回日期: 2013-01-15
- 刊出日期: 2013-10-14

Multi-spar composite box design and its post-buckling analysis

1.
School of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2.
Shenyang Aircraft Design Research Institute, Shenyang 110035, China;
3.
Aircraft Strength Research Institute of China, Xi'an 710065

More Information

Corresponding author:
CHEN Puhui: 陈普会, 教授, 博士生导师, 研究方向为复合材料结构设计与分析 E-mail: phchen@nuaa.edu.cn

摘要

摘要: 采用商业有限元软件ABAQUS对盒段的后屈曲承载能力进行了分析,重点研究了在弯扭载荷条件下后屈曲诱发的盒段蒙皮/缘条界面的失效问题。在此基础上,采用缝线对墙缘条与蒙皮的界面进行增强,应用粘接元模拟缝线,研究缝线对复合材料多墙盒段的破坏模式和承载能力的影响,并对缝线增强后的盒段的承载能力进行了试验研究。有限元分析表明,复合材料多墙盒段具有较长的后屈曲历程,采用缝线增强技术能够明显改善盒段的后屈曲承载能力,预测结果与试验值吻合良好,而且预测的失效模式也与试验结果一致。
- 复合材料 /
- 多墙盒段 /
- 试验 /
- 后屈曲 /
- 缝线 /
- 承载能力
Abstract: The post-buckling loading capability of the box was analyzed with the commercial software ABAQUS, focusing on the failure of skin/flange interface induced by post-buckling under bend-twist loading. Based on the FEM results, the skin/flange interface was enhanced by stitch which was simulated by using cohesive element, and the impact of stitch on failure mode and loading capability of the box was discussed. Moreover, the loading capability of reinforced box was studied by testing. The FEM results show that the multi-spar composite box has a long post-buckling period, and the post-buckling loading capability of the box reinforced by stitching technique could be improved significantly. The predicted results coincide well with experimental data, and the failure mode is also consistent with test results.
- composite /
- multi-spar box /
- testing /
- post-buckling /
- stitch /
- loading capability