摘要
为了研究复合材料层合板在疲劳载荷下的分层扩展行为,本文基于内聚力本构模型提出一种改进的疲劳分层损伤速率计算模型;该模型只需要疲劳裂纹扩展速率Paris准则作为参数输入,无需进行裂纹尖端追踪或额外的参数拟合。基于所提出疲劳分层损伤算法,开发了复合材料疲劳分层VUMAT用户子程序植入ABAQUS/Explicit软件,并分别对复合材料单向层合板的Ⅰ型、Ⅱ型以及Ⅰ/Ⅱ混合型疲劳分层开裂过程开展了有限元数值模拟,结果表明该模型可以有效模拟疲劳载荷下复合材料层合板层间分层开裂。最后,对该模型进行了误差分析和网格敏感性分析,分析结果表明较长的疲劳内聚区长度可以明显提高该模型的计算精度。
In order to study the delamination behaviour of composite laminates subjected to fatigue loading,an improved fatigue damage rate strategy was proposed based on cohesive zone model(CZM).This strategy only re⁃quires the fatigue crack growth rate Paris law as the input parameters while no crack tip tracking or additional pa⁃rameter fitting is needed.The proposed fatigue damage rate strategy was implemented into the commercial software ABAQUS/Explicit via a user written subroutine VUMAT,and the fatigue damage processes of composite unidirec⁃tional laminates under modeⅠ,modeⅡandⅠ/Ⅱmixed-mode loading scenarios were simulated,and the results show that the improved model can effectively simulate the fatigue delamination of composite laminates.Finally,error analysis and mesh sensitivity analysis of the model were carried out,and it is shown that longer fatigue cohesive zone lengths can clearly improve the computational accuracy of the proposed model.
作者
项跟洋
冯电视
XIANG Genyang;FENG Dianshi(College of Civil Engineering,Taiyuan University of Technology,Taiyuan 030024,China)
出处
《复合材料科学与工程》
CAS
北大核心
2023年第8期19-25,91,共8页
Composites Science and Engineering
基金
山西省高等学校科技创新项目(2019L0203)。
