Liu Yuesen, Xie Jiuming, Chen Xin, Zhang Jiawen, Wan Meiqing, Sun Zengxi, Yang Chunlin
School of Mechanical Engineering, Tianjin Sino-German University of Applied Sciences, Tianjin, 300350, China.
Tianjin Aerospace Reliability Technology Co., Ltd., Tianjin, 300450, China.
Sci Rep. 2025 Apr 21;15(1):13791. doi: 10.1038/s41598-025-98774-7.
The progressive damage behavior and failure mechanism of molded carbon fiber reinforced composite laminates under tensile and three-point bending loads were studied. The mechanical properties and failure mechanism of composite laminates were studied by theoretical analysis, numerical simulation and experimental characterization. The results show that the tensile failure mode of molded carbon fiber reinforced composite laminates presents the phenomenon of resin matrix cross-section fracture, fiber fracture and fiber pull-out. Under three-point bending load, the main failure modes of molded carbon fiber reinforced composite laminates are matrix crack, interlayer separation and fiber fracture. Based on the progressive energy dissipation theory and the incremental method, the FEA-VUMAT model is established, which can accurately predict the tensile, three-point bending response and failure mechanism. The predicted load-displacement curves and load disturbance curves of the model are in good agreement with the experimental results. The prediction accuracy of the maximum tensile load, flexural modulus and flexural strength is 97%, 96% and 93%, respectively, which verifies the validity of the model.
研究了模压碳纤维增强复合材料层合板在拉伸和三点弯曲载荷作用下的渐进损伤行为及失效机理。通过理论分析、数值模拟和实验表征研究了复合材料层合板的力学性能和失效机理。结果表明，模压碳纤维增强复合材料层合板的拉伸失效模式呈现出树脂基体横截面断裂、纤维断裂和纤维拔出的现象。在三点弯曲载荷作用下，模压碳纤维增强复合材料层合板的主要失效模式为基体裂纹、层间分离和纤维断裂。基于渐进能量耗散理论和增量法，建立了FEA-VUMAT模型，该模型能够准确预测拉伸、三点弯曲响应及失效机理。模型预测的载荷-位移曲线和载荷扰动曲线与实验结果吻合良好。最大拉伸载荷、弯曲模量和弯曲强度的预测精度分别为97%、96%和93%，验证了模型的有效性。
