基于复合材料Ⅰ型分层损伤机制的解耦内聚力方法  

Decoupling cohesion method based on Mode I delamination damage mechanism of composite materials

作　　者：张旭东 段青枫 曹东风 陈翀一 胡海晓 王继军 李书欣[1,2,3] ZHANG Xudong;DUAN Qingfeng;CAO Dongfeng;CHEN Chongyi;HU Haixiao;WANG Jijun;LI Shuxin(State Key Laboratory of Advanced Technology for Materials Synthesis and Processing,Wuhan University of Technology,Wuhan 430070,China;National Key Laboratory of Hydrogen Energy and Ammonia Hydrogen Fusion New Energy Technology,Foshan Xianhu Laboratory,Foshan 528200,China;Hubei Key Laboratory of Theory and Application of Advanced Materials Mechanics,Wuhan University of Technology,Wuhan 430070,China;China Gezhouba Group Road and Bridge Engineering CO.,LTD.,Yichang 443000,China)

机构地区：[1]武汉理工大学材料复合新技术国家重点实验室,武汉430070 [2]国家能源氢能及氨氢融合新能源技术重点实验室佛山仙湖实验室,佛山528200 [3]武汉理工大学新材料力学理论与应用湖北省重点实验室,武汉430070 [4]中国葛洲坝集团路桥工程有限公司,宜昌443000

出　　处：《复合材料学报》2024年第9期4942-4955,共14页Acta Materiae Compositae Sinica

基　　金：国家自然科学基金(52273080,12302481,12172265);2023年湖北省重大攻关项目(JD2023BAA028)。

摘　　要：分层损伤是航空航天复合材料结构分层的主要损伤模式之一。Ⅰ型分层具有起始断裂韧性值低,损伤模式复杂的特征,深入分析裂纹尖端损伤区多种损伤机制之间的相互关系及纤维桥接损伤演化过程,对研究Ⅰ型分层损伤起关键作用。本文针对性采用3种不同层间铺层(0//0、0//45、0//90)设计T700级碳纤维/环氧复合材料层合板并开展Ⅰ型分层测试。通过观测分层起始及损伤演化过程,总结标准双悬臂梁(DCB)试验结果载荷位移曲线及R曲线规律,并根据试样断口形貌、SEM等多种表征方法分析,揭示了裂纹尖端的损伤机制。在此基础上提出了一种分层损伤机制解耦的新方法。该方法基于3个双线性内聚力本构叠加,通过建立内聚力单元模型来解耦不同损伤尺度的分层损伤机制,独立表征了不同损伤机制在分层扩展过程中所作的贡献。仿真模拟所需参数均可从试验获得,计算得到的仿真结果与试验结果具有良好的一致性。Delamination damage is one of the primary damage modes in aerospace composite structures.Mode I delamination exhibits characteristics of low initial fracture toughness and complex damage patterns.Analyzing the interrelationships among three damage mechanisms at the crack tip region and bridging fiber damage evolution plays a crucial role in studying Mode I delamination.This paper specifically designs T700 level carbon fiber/epoxy composite laminates with three different interlayer configurations(0//0,0//45,0//90)and conducts Mode I delamination tests.By observing the initiation and evolution of delamination,summarizing double cantilever beam(DCB)experimental results in load-displacement curves and R-curves,and employing various characterization methods like SEM analysis based on specimen fracture surfaces,it reveals the damage mechanisms at the crack tip.Subsequently,a new approach to decoupling layered damage mechanisms is proposed,based on three bilinear cohesive constitutive laws.This method establishes a cohesive element model to decouple layered damage mechanisms at different damage scales,independently characterizing the contributions of different damage mechanisms during layered propagation.Parameters required for simulation are obtained from experiments,and the simulated results exhibit good consistency with experimental data.

关 键 词：复合材料层合板 分层 纤维桥接 损伤机制 DCB 内聚力模型 

分 类 号：TB332[一般工业技术—材料科学与工程]