含孔碳纤维复合材料拉伸渐进损伤失效多尺度分析
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1.北京信息科技大学 机电工程学院 高端装备智能运维与控制北京市重点实验室北京100192; 2.高端装备智能感知与控制北京市国际科技合作基地北京100192;3.现代测控技术教育部 重点实验室北京100192;4. 北京航天动力研究所北京100076

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TB332;TN06

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北京市自然科学基金(L258043,IS24076)、航空航天结构力学及控制国家重点实验室重点开放课题(MCMS-E-0423K01)资助项目


Multi-scale analysis of tensile progressive damage failure of Open-hole carbon fiber composites
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1.Beijing Key Laboratory of Intelligent Operation and Maintenance and Control of High-end Equipment,School of Mechanical and Electrical Engineering, Beijing Information Science & Technology University, Beijing 100192, China;2.High-end Equipment Intelligent Perception and Control Beijing International Science & Technology Cooperation Base,Beijing 100192, China; 3.Key Laboratory of Modern Measurement & Control Technology, Ministry of Education,Beijing 100192, China; 4.Beijing Aerospace Propulsion Institute, Beijing 100076,China

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    摘要:

    碳纤维增强复合材料(carbon fiber reinforced polymer,CFRP)广泛应用于航空航天等领域。但装配钻孔易引发应力集中,导致局部损伤扩展与承载能力下降。亟需研究碳纤维复合材料板材局部损伤的产生扩展的机理并对其失效预测。提出了一种碳纤维复合材料拉伸渐进损伤多尺度分析方法,实现了CFRP板材微观宏观力学性能和拉伸损伤的全流程数值仿真预测。首先,建立微观代表性体积单元(representative volume element,RVE),设定周期性边界条件,获得材料力学性能参数。然后,建立CFRP板材的有限元模型,采用应变形式Hashin损伤判据和基于断裂能的线性损伤演化建立了渐进损伤多尺度预测模型。对含孔层合板进行了拉伸仿真模拟,建立的渐进损伤模型能够较准确地预测层合板的载荷位移曲线,最大载荷和试验结果误差仅在9.3%以内。最后研究了不同孔深对开孔层合板拉伸极限载荷和损伤行为的影响。实验结果表明,随着孔深增加,层合板极限承载能力显著下降。损伤起始于孔边90°铺层的基体开裂,并逐步向开孔区域内的0°铺层扩展;随着载荷增大,损伤进一步向未被钻穿的内部完整0°主承力铺层传递,导致承载能力持续退化。孔深的增大不仅减少了有效承载面积,更改变了0°铺层中纤维损伤的起始位置与演化路径,削弱了层间载荷再分配能力,加速结构失效。

    Abstract:

    Carbon fiber reinforced polymer (CFRP) is widely used in aerospace and other fields. However, assembly drilling is easy to cause stress concentration, resulting in local damage expansion and bearing capacity reduction. It is urgent to study the mechanism of local damage generation and expansion of carbon fiber composite plates and predict their failure. A multi-scale analysis method for tensile progressive damage of carbon fiber composites is proposed, and the whole process numerical simulation prediction of micro-macro mechanical properties and tensile damage of CFRP laminates are realized. Firstly, the representative volume element (RVE) is established, and the periodic boundary conditions are set to obtain the mechanical properties of the material. Then, the finite element model of CFRP laminates is established, and the progressive damage multi-scale prediction model is established by using the stress form Hashin damage criterion and the linear damage evolution based on fracture energy. The tensile simulation of laminates with holes was carried out. The established progressive damage model can accurately predict the load-displacement curve of laminates, and the error between the maximum load and the test result is only within 9.3%. Finally, the effects of different hole depths on the tensile ultimate load and damage behavior of perforated laminates were studied. The results show that the ultimate bearing capacity of laminates decreases significantly with the increase of hole depth. The damage starts from the matrix cracking of the 90°plies at the edge of the hole, and gradually expands to the 0 °plies in the hole area. As the load increases, the damage is further transmitted to the internally intact 0 °main bearing layer that has not been drilled, resulting in continuous degradation of the bearing capacity. The increase of the hole depth not only reduces the effective bearing area, but also changes the initial position and evolution path of fiber damage in the 0 °plies, weakens the inter-layer load redistribution ability and accelerates the structural failure.

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石豫星,王红军,金志磊,韩凤霞.含孔碳纤维复合材料拉伸渐进损伤失效多尺度分析[J].电子测量与仪器学报,2026,40(8):197-206

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