摘要
为了分析复合材料层板疲劳分层扩展行为,基于Abaqus有限元分析平台,建立分层扩展复合材料层板有限元分析模型。选用基于能量释放率的分层扩展判据,结合剩余强度模型弱化材料性能,引入VUMAT用户子程序实现模型疲劳损伤失效的判断及材料刚度性能的折减,模拟含分层复合材料层板在疲劳压缩载荷作用下的分层扩展行为。结果表明:分层长度随着疲劳载荷地施加不断增大,但扩展速率逐渐减小,最终分层长度达到稳定值,与实验结果吻合良好。
A finite element model of composite laminates with delamination damage is established to analyze the fatigue delamination propagation behavior of composite laminates, and B-K standard based on the energy release rate as the criterion of delamination growth is taken. The residual strength model is adopted and VUMAT user subroutine is introduced to judge the failure of model and reduce the stiffness performance of material. Based on the Abaqus simulation analysis software, the delamination growth mechanism of composite laminates with initial delamination damage under fatigue compression load is simulated. The results indicate that with the fatigue load applying, the delamination length is increased and reached a stable value. Finally, with the delamination growth rate being reduced, a good agreement is obtained between FEA analysis and the experimental results.
出处
《航空工程进展》
2014年第1期46-52,58,共8页
Advances in Aeronautical Science and Engineering
基金
国家自然科学基金(11102082)
江苏高校优势学科建设工程资助
