Han Liu, Song Yao, Qi Hui, Yang Jin-Shui, Li Shuang, Liu Ping-An
College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin 150001, China.
AVIC Harbin Aircraft Industry Croup Co., Ltd., Harbin 150066, China.
Polymers (Basel). 2023 Nov 20;15(22):4468. doi: 10.3390/polym15224468.
In this paper, the damage initiation/propagation mechanisms and failure modes of open-hole carbon fiber-reinforced thermoplastic composites and thermosetting composites with tension, compression, and bearing loads are investigated, respectively, by experiments and finite element simulations. The experimental evaluations are performed on the specimens using the Combined Loading Compression (CLC) test method, the tensile test method, and the single-shear test method. The differences in macroscopic damage initiation, evolution mode, and damage characteristics between thermoplastic composite materials and thermosetting composite material open-hole structures are obtained and analyzed under compressive load. Based on scanning electron microscope SEM images, a comparative analysis is conducted on the micro-failure modes of fibers, matrices, and fiber/matrix interfaces in the open-hole structures of thermoplastic and thermosetting composites under compressive load. The differences between thermoplastic and thermosetting composites were analyzed from the micro-failure mechanism. Finally, based on continuum damage mechanics (CDM), a damage model is also developed for predicting the initiation and propagation of damage in thermoplastic composites. The model, which can capture fiber breakage and matrix crack, as well as the nonlinear response, is used to conduct virtual compression tests, tensile test, and single-shear test, respectively. Numerical simulation results are compared with the extracted experimental results. The displacement-load curve and failure modes match the experimental result, which indicates that the finite element model has good reliability.
本文分别通过实验和有限元模拟，研究了开孔碳纤维增强热塑性复合材料和热固性复合材料在拉伸、压缩和承载载荷作用下的损伤起始/扩展机制及失效模式。使用组合加载压缩（CLC）试验方法、拉伸试验方法和单剪试验方法对试样进行实验评估。获得并分析了热塑性复合材料和热固性复合材料开孔结构在压缩载荷下宏观损伤起始、演化模式和损伤特征的差异。基于扫描电子显微镜（SEM）图像，对热塑性和热固性复合材料开孔结构在压缩载荷下纤维、基体和纤维/基体界面的微观失效模式进行了对比分析。从微观失效机制方面分析了热塑性和热固性复合材料之间的差异。最后，基于连续损伤力学（CDM），建立了一个损伤模型来预测热塑性复合材料中损伤的起始和扩展。该模型能够捕捉纤维断裂、基体裂纹以及非线性响应，分别用于进行虚拟压缩试验、拉伸试验和单剪试验。将数值模拟结果与提取的实验结果进行比较。位移-载荷曲线和失效模式与实验结果相符，表明有限元模型具有良好的可靠性。
