复合材料层合板低速冲击后剩余压缩强度研究  

Effectively Calculating Residual Compressive Strength of Composite Laminate after Impact(CAI)

作　　者：姚振华[1] 李亚智[1] 刘向东[1] 李彪[1] 李玺[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《西北工业大学学报》2012年第4期518-523,共6页Journal of Northwestern Polytechnical University

摘　　要：应用有限元显式算法计算层合板冲击后压缩强度(CAI值)。建立实体单元与cohesive界面单元相结合的层合板有限元分析模型。首先进行层合板受离面低速冲击中损伤过程的数值模拟,再以该步分析结果(损伤状态)作为初始损伤,进行面内压缩下层合板破坏过程数值模拟。从而实现了层合板从冲击损伤到冲击后压缩破坏的全过程分析。模型应用面内和层间损伤逐渐累积的算法。通过不同加载速率下的分析,考察了显式算法在准静态CAI计算中的可用性。冲击损伤特征、冲击后压缩破坏特征及CAI的计算值与试验结果有良好的一致性,表明文中所采用的模型、算法与损伤处理方法是合理的。The explicit finite element model was established using the solid elements and interfacial cohesive ele- ments. A two-step calculation procedure was established. Sections 1 through 3 of the full paper explain our method of calculation mentioned in the title, which we believe is effective and whose core consists of： （1） the out of plane low-velocity impact process was simulated first; the results of the first step, namely the state of the damages and de- formation, were taken as the input for the second step to simulate the in-plane compression, until the collapse of the laminate; the strength criterion and a stiffness degradation scheme were utilized to characterize various types of the in-plane damages; the initiation and propagation of the delamination damage was estimated with the cohesive ele- ments according to the failure criteria and critical energy release rate criterion respectively; （2） the usefulness of the explicit solution algorithm in dealing with the quasi-static procedure of the in-plane compression was investigated Tables 3 through 5, and their analysis show preliminarily that they are indeed in fairly good agreement with the ex- perimental ones.

关 键 词：复合材料 计算机模拟 分层 有限元法 冲击阻抗 冲击后压缩 低速冲击 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程] O347.3[理学—固体力学]