摘要
作为复合材料结构制造与使用过程中常见的缺陷损伤之一,分层会引起材料压缩强度的降低。在ABAQUS中建立含分层复合材料层板的有限元模型,编写了相关Umat子程序,将仿真结果与试验数据进行了对比,验证了模型的精度与有效性。同时对比了Hashin与Puck两种失效准则对仿真结果的影响,结果表明,使用Puck准则与试验结果吻合更好。利用已验证的有限元建模方法,研究了分层面积、厚度位置以及分层形状对剩余强度的影响。研究表明:分层面积越大、分层厚度位置越靠近中央,层合板的剩余强度越低;分层面积相同时,圆、正方形、椭圆(长短轴比为2:1)三种分层形状对剩余强度的影响没有显著差别。
As one of the common defects in the process of manufacturing and using of composite structures,delamination can cause the reduction of material compressive strength.In this paper,the finite element model of composite laminates with delamination is established in ABAQUS,and the related Umat subroutine is compiled.The simulation results are compared with the experimental data,and the accuracy and effectiveness of the model are verified.At the same time,the difference between the simulation results using Hashin criterion and Puck criterion is also compared.The results show that the Puck criterion is in better agreement with the experimental results.Finally,the effects of delamination area,thickness and shape on residual strength are also studied by using the validated finite element modeling method.The results show that:the larger the delamination area and the closer the delamination to the center of thickness,the lower the residual strength of the laminate;when the delamination area is the same,there is no significant difference in the influence of the three delamination shapes of circle,square and ellipse(the ratio of long axis to short axis is 2:1)on residual strength.
作者
童瑶
刘磊
朱书华
TONG Yao;LIU Lei;ZHU Shu-hua(Shanghai Aircraft Design and Research Institute,Shanghai 201000,China;Nanjing University of Aeronautics and Astronautics,Nanjing 211000,China)
出处
《航空计算技术》
2022年第1期110-114,共5页
Aeronautical Computing Technique
基金
中央高校基本科研业务费项目资助(NS2019008)。
关键词
复合材料
分层
剩余强度
失效准则
composite material
delamination
residual strength
failure criterion
