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陶瓷基复合材料(CMC)在航空航天领域应用广泛，其必要的机械连接结构最为薄弱。在常用的螺纹连接中，CMC螺栓因承受预紧力带来的拉伸载荷，最易失效。提出一种预测针刺C/SiC螺栓失效模式的细观力学方法。建立由0°/90°单向纤维层、网胎层和针刺纤维束组成的螺栓的细观几何模型；建立这些组分的本构模型、失效准则和退化模型，并在此基础上进行渐进损伤分析(PDA);预测螺栓的极限断裂载荷与损伤演变过程。失效单元的分布表明，C/SiC螺栓的宏观失效模式是螺纹牙断裂。在细观尺度上，单向层和针刺纤维束的剪切破坏引起了螺纹牙断裂。为验证建立的细观力学模型，对C/SiC螺栓进行拉伸试验，试验结果与预测结果一致。
Abstract：Ceramic matrix composites(CMC) are widely used in the aerospace field, where their necessary mechanical connection structures are particularly vulnerable. Among the commonly used threaded connections, CMC bolts are most prone to failure due to the tensile loads resulting from pre-tensioning. A micromechanical method is developed to predict the failure behavior of the needle-punched C/SiC bolt. A microscopic geometric model of the bolt is established which is composed of 0°/90° unidirectional fiber plies, fiber net plies and needle-punched fiber bundles. Constitutive models, failure criteria, and degradation models for these components are developed, followed by progressive damage analysis(PDA) based on these models. The ultimate fracture load of the bolt is predicted as well as the damage evolution process. The distribution of the failed elements reveals that the macroscopic failure mode of C/SiC bolts is the fracture of the thread. On the microscale, shear failure of the unidirectional plies and needled fiber bundles leads to thread tooth failure. To verify the established micromechanical model, tensile tests are performed on C/SiC bolts, showing consistent results with the predictions.
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基本信息:
DOI：10.19886/j.cnki.dhdz.2024.0332
中图分类号:TB332;TH131.3
引用信息:
[1]王通,张盛,高希光,等.拉伸载荷下针刺C/SiC螺栓连接失效模式的细观力学模拟[J].东华大学学报(自然科学版),2025,51(06):162-168.DOI:10.19886/j.cnki.dhdz.2024.0332.
基金信息:
国家自然科学基金(52202098)