复合材料大开孔层合板压缩损伤分析与试验  

Compressive Damage Analysis and Experiment of Large Opening Composite Laminate

作　　者：张芸倩 段世慧[1] 张国凡[1] 聂小华[1] ZHANG Yun-qian;DUAN Shi-hui;ZHANG Guo-fan;NIE Xiao-hua(Aircraft Strength Research Institute of China,Xi′an 710000,China)

机构地区：[1]中国飞机强度研究所,陕西西安710000

出　　处：《航空计算技术》2022年第1期65-69,共5页Aeronautical Computing Technique

基　　金：航空科学基金项目资助(20183723009);国家工信部民用飞机专项科研项目资助(MJ-2017-F-24)。

摘　　要：为提升复合材料大开孔层合板损伤分析计算精度,采用三维渐进损伤分析模型研究了开孔复合材料层合板在压缩载荷作用下的损伤机理,模型考虑了损伤演化、破坏准则以及刚度退化等因素。其中,采用带剪切非线性修正的Hashin准则作为单元失效的判断依据,引入瞬时退化模型对失效单元进行材料退化仿真。在ABAQUS中通过编写用户自定义材料子程序,实现复合材料大开孔层合板压缩渐进损伤分析。通过大开孔层合板压缩强度试验对得到的仿真结果进行验证,对比结果表明仿真计算与真实试验结果误差仅为4%,且仿真分析计算得出的失效位置与失效模式和试验吻合较好,验证了模型的有效性与准确性。In order to improve simulation accuracy of large opening composite laminate,a three dimensional finite element model based on progressive failure analysis method is established in this paper to study the damage mechanism of composite laminates with large opening under compression load,considering damage evolution,rigidity degeneration,and failure criterion.In the constructed model,a modified nonlinear Hashin criterion is employed for the judgement of element failure.Simultaneously,instantaneous degradation model is introduced for material performance degradation simulation of the failure element.Finally,the compressive progressive damage analysis for large opening composite laminate is realized in ABAQUS software via user defined material subroutine.Finally,the simulation results are verified by experiments.The result of simulation and experiment indicates that the simulation error is only about 4%.Moreover,the failure position and mode of simulation result is similar with those of experimental result,which demonstrates the effectiveness and accuracy of the paper.

关 键 词：复合材料层合板 用户自定义材料子程序 有限元 渐进损伤 破坏准则 

分 类 号：TB332[一般工业技术—材料科学与工程]