计及层内和层间的L形层合板失效的数值研究

doi:10.19936/j.cnki.2096-8000.20240328.006

复合材料科学与工程 ›› 2024, Vol. 0 ›› Issue (3): 43-53.DOI: 10.19936/j.cnki.2096-8000.20240328.006

计及层内和层间的L形层合板失效的数值研究

王宇轩¹, 曹东风^2,3,4*, 胡海晓^1,2,4, 李书欣^1,2,3,4

1.武汉理工大学理学院,武汉 430070;
2.先进能源科学与技术广东省实验室佛山分中心(佛山仙湖实验室),佛山 528000;
3.武汉理工大学材料复合材料新技术国家重点实验室,武汉 430070;
4.武汉理工大学先进材料制作装备与技术研究院,武汉 430070

收稿日期:2023-04-06 出版日期:2024-03-28 发布日期:2024-04-22
通讯作者: 曹东风(1980—),男,副研究员,硕士生导师,主要从事先进复合材料力学与数值仿真技术方面的研究,cao_dongf@whut.edu.cn。
作者简介:王宇轩(1998—),男,硕士,研究方向为复合材料力学。
基金资助:
国家自然科学基金(52273080)

Computational study on failure behavior of L-shaped laminates considering both intra-laminar matrix cracking and inter-laminar delamination

WANG Yuxuan¹, CAO Dongfeng^2,3,4*, HU Haixiao^1,2,4, Li Shuxin^1,2,3,4

1. School of Science, Wuhan University of Technology, Wuhan 430070, China;
2. Foshan Xianhu Laboratory of the Advanced Energy Science and Technology Guangdong Laboratory, Foshan 528000, China;
3. State Key Laboratory of Materials Synthesis and Processing, Wuhan University of Technology, Wuhan 430070, China;
4. Institute of Advanced Materials and Manufacturing Technology, Wuhan University of Technology, Wuhan 430070, China

Received:2023-04-06 Online:2024-03-28 Published:2024-04-22

摘要/Abstract

摘要： 民用复合材料飞机中,L形层合板是最常见也是最关键的元件,研究其失效机制对飞机结构安全至关重要。层内基体裂纹扩展和层间分层失效是L形复合材料层合板最关键的两种失效机制,这两种失效机制可能同时发生并且存在耦合作用。本文提出两套数值分析模型,用于描述L形复合材料层合板的失效过程。模型Ⅰ在L形板的弧形区域层间布置零厚度内聚力单元用于模拟分层,同时在90°层内铺设径向零厚度内聚力单元用于模拟基体裂纹。模型Ⅱ采用XFEM方法模拟基体裂纹的萌生和扩展,采用内聚力行为方法模拟分层。通过与试验进行对比,验证了本文方法的可行性。同时,对两套模型在失效模式和关键载荷预测等方面的能力和优缺点进行评价。结果表明,两套模型都能描述基体裂纹和分层的扩展及二者的耦合作用。模拟分析所得到的失效模式与试验结果一致,同时预测的初始失效载荷和最大失效载荷也与试验结果吻合良好。

关键词: L形层合板, 层内裂纹, 分层, 扩展有限元, 内聚力单元, 复合材料

Abstract: L-shaped laminates are the most common and critical composite components in commercial aircraft, and the study of their failure mechanism is very important for the safety of aircraft structures. The crack propagation in matrix and the delamination failure between plies are the two most important failure mechanisms of L-shaped composite laminates. These two failure mechanisms may occur simultaneously and have coupling effects. In this paper, two sets of numerical analysis models are presented to describe the failure process of L-shaped composite laminates. In Model Ⅰ, zero-thickness cohesive elements are inserted between plies in the curved region of L-shaped laminates to simulate delamination and radial-pattern zero-thickness cohesive elements are inserted in the 90° layer to simulate matrix cracks. In Model Ⅱ, the XFEM method was used to simulate the initiation and propagation of matrix cracks and the cohesive behavior method was used to simulate the delamination. In comparison with the experimental results, the feasibility of the proposed methods is validated. Furthermore, the capability as well as the advantages and disadvantages of the two models in terms of failure modes and critical load predictions are evaluated. The results show that both models can describe the propagation of matrix crack and delamination as well as possible coupling effects. The failure modes predicted by numerical analysis agree well with the experimental results, and the predicted initial failure loads and maximum failure loads are also in good agreement with the experimental results.

Key words: L-shaped laminate, intra-laminar cracking, delamination, XFEM, cohesive elements, composite

中图分类号:

TB332

王宇轩, 曹东风, 胡海晓, 李书欣. 计及层内和层间的L形层合板失效的数值研究[J]. 复合材料科学与工程, 2024, 0(3): 43-53.

WANG Yuxuan, CAO Dongfeng, HU Haixiao, Li Shuxin. Computational study on failure behavior of L-shaped laminates considering both intra-laminar matrix cracking and inter-laminar delamination[J]. COMPOSITES SCIENCE AND ENGINEERING, 2024, 0(3): 43-53.

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计及层内和层间的L形层合板失效的数值研究

Computational study on failure behavior of L-shaped laminates considering both intra-laminar matrix cracking and inter-laminar delamination

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