含缺口碳/碳复合材料损伤行为试验与数值研究

doi:10.3901/JME.2025.12.060

摘要/Abstract

摘要： 碳/碳(C/C)复合材料是航空、航天和核能等领域不可或缺的战略性材料。为满足装配和功能需求，C/C复合材料不可避免地会存在各种形式的缺口，在服役过程中，其缺口边缘处极易产生不同类型损伤，进而影响材料的失效载荷，因此设计C/C复合材料构件时必须考虑缺口参数对其力学性能的影响。为提升含缺口构件的设计水平，采用试验测试和数值计算相结合的C/C复合材料损伤行为研究方法，通过不同缺口尺寸试样的拉伸试验获得材料承载能力和失效形貌，根据各类损伤的特征，分别采用Hashin、Puck和二次应力准则定义碳纤维、热解碳基体和层间界面损伤的起始，并通过基于能量的损伤演化方法描述相应的刚度退化行为。数值预测的极限载荷和损伤分布与试验结果吻合，证明了所建有限元模型的有效性。研究表明，缺口尺寸和位置均对C/C复合材料的承载能力有较大影响，当缺口尺寸从1.0 mm增大至2.2 mm时，极限载荷下降38.5%；而当缺口间距离从0 mm增大至12.8 mm时，纤维损伤的起始位移减小16.1%，极限载荷下降17%。此外，研究还揭示了缺口C/C复合材料的损伤演化规律：在加载过程中，层间界面损伤、基体损伤和纤维损伤依次出现并不断演化直至材料完全失效。研究成果有望为含缺口C/C复合材料构件设计提供参考。

关键词: 缺口碳/碳复合材料, 损伤行为, 承载能力, 数值计算, 试验测试

Abstract: Carbon/Carbon (C/C) composites are indispensable strategic materials for aviation, aerospace, and nuclear energy. Various notches are inevitably introduced in C/C composites to meet the assembly and functional requirements. During loading, various damages affecting the failure load are prone to occur at the edges of the notches. Thus, the effect of the notches on the effective mechanical properties must be considered when designing C/C composite parts. A strategy combining experimental test and numerical calculation is used to helps understand the design of high-performance notched C/C composite parts. Load-bearing capacity and failure morphology of C/C composites are obtained by experiments with various notch sizes. Based on the characteristics of various damages, Hashin, Puck, and quadratic stress criterion are individually adopted to define the damage initiation of carbon fiber, pyrocarbon matrix, and the interlaminar interface. The damage evolution is defined by the energy-based method. The validity of the proposed finite element model is verified by the good agreements between the experimental and numerical ultimate loads and damage distributions. It is found that the load-bearing capacity of C/C composites is significantly affected by the size and distribution of the notches. The ultimate load of C/C composites decreases by 38.5% as the size of notches increases from 1.0 mm to 2.2 mm. The damage initiation displacement of fibers decreases by 16.1% and the ultimate load drops by 17% with the increase of distance between the notches from 0 mm to 12.8 mm. Finally, the research reveals the damage evolution mechanism of the notched C/C composites, which suggests that the composites fail completely as the interlaminar interface damage, matrix damage, and fiber damage appear sequentially during the loading. The design of notched C/C composite parts can be guided by the research results in the future.

Key words: notched C/C composite, damage behavior, load-bearing capacity, numerical calculation, experimental test

中图分类号:

TB332

李伟琪, 齐乐华, 晁许江, 葛健, 田文龙, 李贺军. 含缺口碳/碳复合材料损伤行为试验与数值研究[J]. 机械工程学报, 2025, 61(12): 60-72.

LI Weiqi, QI Lehua, CHAO Xujiang, GE Jian, TIAN Wenlong, LI Hejun. Experiment and Numerical Calculation Study on Damage Behaviors of Notched C/C Composites[J]. Journal of Mechanical Engineering, 2025, 61(12): 60-72.

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