纤维桥联作用下的复合材料Ⅰ型疲劳分层扩展

doi:10.7527/S1000-6893.2024.29919

固体力学与飞行器总体设计

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纤维桥联作用下的复合材料Ⅰ型疲劳分层扩展

姚辽军¹^,²(), 魏景超², 陈向明², 啜明月¹, 李含月¹, 果立成¹

^1.哈尔滨工业大学航天学院航天科学与力学系，哈尔滨 150001
^2.中国飞机强度研究所强度与结构完整性全国重点实验室，西安 710065

收稿日期:2023-11-27 修回日期:2024-02-21 接受日期:2024-05-23 出版日期:2024-09-25 发布日期:2024-05-30
通讯作者: 姚辽军 E-mail:L.Yao@hit.edu.cn
基金资助:
强度与结构完整性全国重点实验室开放基金(ASSIKFJJ202302003);国家自然科学基金(12272110);航空科学基金(2022Z055077004)

Critical discussions on mode I fatigue delamination with large⁃scale fibre bridging in composite laminates

Liaojun YAO¹^,²(), Jingchao WEI², Xiangming CHEN², Mingyue CHUAI¹, Hanyue LI¹, Licheng GUO¹

^1.Department of Astronautics Science and Mechanics，School of Astronautics，Harbin Institute of Technology，Harbin 150001，China
^2.National Key Laboratory of Strength and Structural Integrity，Aircraft Strength Research Institute of China，Xi’an 710065，China

Received:2023-11-27 Revised:2024-02-21 Accepted:2024-05-23 Online:2024-09-25 Published:2024-05-30
Contact: Liaojun YAO E-mail:L.Yao@hit.edu.cn
Supported by:
National Key Laboratory of Strength and Structural Integrity Science Foundation(ASSIKFJJ202302003);National Natural Science Foundation of China(12272110);Aeronautical Science Foundation of China(2022Z055077004)

摘要/Abstract

摘要：

先进复合材料以其优异的力学性能及在结构减重方面的巨大潜力已经广泛应用于航空航天领域，其用量多少已经成为衡量一个国家高端装备技术发展水平的重要标志之一。疲劳分层是导致航空航天复合材料结构失效的重要原因，纤维桥联对疲劳分层扩展存在显著影响。同时，不同断裂模式下，复合材料抵抗Ⅰ型疲劳分层扩展的能力最低。因此，针对纤维桥联作用下的复合材料Ⅰ型疲劳分层扩展问题开展研究，具有十分重要的意义。本文对作者课题组近年来开展的相关研究工作进行了系统总结和介绍，重点对以下问题进行了分析讨论：纤维桥联对疲劳分层扩展的影响规律及机理；纤维桥联作用下的疲劳分层扩展模型和分析方法；疲劳分层扩展分析模型的应用和验证。研究表明，纤维桥联对疲劳分层扩展存在显著的抑制作用，将导致疲劳分层扩展速率随分层扩展长度的增加而显著下降；纤维桥联在疲劳分层扩展中的作用机理与静态分层扩展存在不同，疲劳分层扩展主要的能量耗散集中于分层前缘附近，桥联纤维中的能量耗散相对有限；并且纤维桥联强弱对疲劳分层前缘的损伤失效机制无显著影响。因此，采用作用于分层前缘处的应变能释放率作为疲劳裂纹扩展相似性参数，能够对纤维桥联作用下的复合材料Ⅰ型疲劳分层扩展进行有效的分析和表征，满足疲劳裂纹扩展相似性假设的基本要求；以此为基础，采用双参数形式的疲劳分层扩展准则，能够有效考虑应力比的影响，实现不同载荷工况下复合材料Ⅰ型疲劳分层扩展行为的有效分析和表征。

关键词: 疲劳分层, 纤维桥联, 相似性原理, 疲劳分层扩展准则, 复合材料

Abstract:

Advanced carbon fibre reinforced polymer composites have been widely used in aerospace industry， because of their excellent mechanical properties and great weight-saving potential. Fatigue delamination has been demonstrated the main reason for the failure of composite structures in their long-term operations. Fiber bridging， as an important and unique shielding mechanism， has significant effects on fatigue delamination behavior. And it has been demonstrated that composite laminates have even lower mode I fatigue delamination resistance. As a result， it is really important to have thorough investigations on mode I fatigue delamination with large-scale fibre bridging in composite laminates， to guarantee the integrity of composite structures. This paper therefore provides critical reviews and discussions on the research work carried out by the author’s research group in this field in the past several years. And the main contents of this paper can be organized as following aspects： the effects of fibre bridging on fatigue delamination behavior， and bridging mechanism in fatigue delamination； the similarity for fatigue delamination with large-scale fibre bridging， and Paris type correlations for fibre-bridged mode I fatigue delamination characterization； the application and verification of the proposed Paris type correlations in fibre-bridged fatigue delamination interpretations. The results clearly demonstrated that the presence of fiber bridging has significant retardation effects on mode I fatigue delamination behavior. Particularly， fatigue delamination growth can decrease significantly with the development of fibre bridging， using the basic Paris law in fatigue data reduction. The mechanism of fiber bridging in fatigue delamination is different from that in static delamination in the perspective of energy dissipation. Particularly， fibre bridging has negligible contribution to permanent energy dissipation in fatigue delamination， unless there is failure in them. Bridging fibres in most cases only periodically store and release strain energy under cyclic loading， making the most energy dissipation still concentrate around the crack front （regardless of fibre bridging） in fatigue delamination. And the fractographic examinations on fatigue fracture surfaces indicate that the presence of fibre bridging indeed has little influence on the damage mechanism in mode I fatigue delamination. According to the energy dissipation and fractographic examinations， it is therefore reasonable to use the strain energy release rate that applied around the crack front as the similitude parameter to appropriately represent fatigue delamination behavior with significant fibre bridging at a given stress ratio， which can well obey the similitude principles. A two-parameter Paris type correlation was proposed to account for stress ratio. And the results clearly indicated that the use of this two-parameter model can appropriately determine fibre-bridged fatigue delamination behavior at different stress ratios and temperatures.

Key words: fatigue delamination, fiber bridging, similarity principles, fatigue delamination laws, composite laminates

中图分类号:

V258

姚辽军, 魏景超, 陈向明, 啜明月, 李含月, 果立成. 纤维桥联作用下的复合材料Ⅰ型疲劳分层扩展[J]. 航空学报, 2024, 45(18): 229919.

Liaojun YAO, Jingchao WEI, Xiangming CHEN, Mingyue CHUAI, Hanyue LI, Licheng GUO. Critical discussions on mode I fatigue delamination with large⁃scale fibre bridging in composite laminates[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(18): 229919.

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纤维桥联作用下的复合材料Ⅰ型疲劳分层扩展

Critical discussions on mode I fatigue delamination with large⁃scale fibre bridging in composite laminates

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