北京航空航天大学学报 ›› 2016, Vol. 42 ›› Issue (5): 1032-1038.doi: 10.13700/j.bh.1001-5965.2015.0335

• 论文 • 上一篇    下一篇

不同工艺成型复合材料加筋板轴压破坏机理分析

徐荣章, 关志东, 王仁宇, 蒋思远   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100083
  • 收稿日期:2015-05-25 出版日期:2016-05-20 发布日期:2015-10-09
  • 通讯作者: 关志东,Tel.:010-82338873 E-mail:D5062010@163.com E-mail:D5062010@163.com
  • 作者简介:徐荣章 男,硕士研究生。主要研究方向:复合材料结构设计。Tel.:010-82338873 E-mail:buaa_xrz@163.com;关志东 男,博士,教授,博士生导师。主要研究方向:飞机结构设计,复合材料力学和损伤容限。Tel.:010-82338873 E-mail:D5062010@126.com

Failure mechanism analysis of different types of manufacture for composite stiffened panels under axial compression load

XU Rongzhang, GUAN Zhidong, WANG Renyu, JIANG Siyuan   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2015-05-25 Online:2016-05-20 Published:2015-10-09

摘要: 对受到边界约束的不同工艺成型复合材料加筋板进行了轴压试验和数值模拟,研究二次胶接和共固化工艺成型加筋板轴向压缩破坏机理。轴压试验中,通过应变计实时监测试验件局部屈曲,及时记录试验件初始声响载荷,通过断面观测分析结构破坏机理。基于ABAQUS软件建立有限元模型模拟结构后屈曲损伤渐进直至破坏过程。计算结果和试验结果相吻合,研究表明工艺对结构稳定性及承载能力没有显著影响,而加筋板构型影响较大。聚甲基丙烯酰亚胺(Polymethacrylimide,PMI)泡沫不影响结构失稳载荷及破坏载荷,但能延缓结构初始损伤的发生。二次胶接成型加筋板界面临近破坏才出现损伤,而共固化成型加筋板界面损伤出现较早且扩展缓慢,表现出更好的损伤阻抗特性。

关键词: 复合材料加筋板, 破坏机理, 后屈曲, 断面分析, 损伤渐进

Abstract: In order to research the failure mechanism of secondary bonding and co-curing stiffened panels under axial compression load, test and numerical calculation were conducted for different types of manufacture of composite stiffened panels with edge constraint. In the test, strain gage was pasted to timely monitor the local buckling, while the load corresponding to initial acoustic emission was detected and fracture cross-section was observed to investigate the fracture mechanism. Based on the ABAQUS software, a finite element was observed to simulate the post-buckling-progress and damage progress. The calculated results are coordinated with the tested results very well. The results indicate that manufacture has no impact on the stability and load capacity, while the structure types have significant influence. Polymethacrylimide (PMI) foam can delay the occurrence of initial damage, even though it cannot increase the buckling load and ultimate load of panels. Initial damage of interface of secondary bonding panels occurs at a time close to fracture, while that of co-curing panels occurs early and extends slowly, so co-curing panels show better behavior of damage resistance.

Key words: composite stiffened panel, fracture mechanism, post-buckling, fracture cross-section analysis, damage progress

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