含面芯界面缺陷的蜂窝夹芯板侧向压缩破坏模式  

End compression failure of honeycomb sandwich panels containing interfacial debonding

作　　者：泮世东[1] 吴林志[1] 孙雨果[1] 

机构地区：[1]哈尔滨工业大学复合材料与结构研究所,哈尔滨150080

出　　处：《复合材料学报》2007年第6期121-127,共7页Acta Materiae Compositae Sinica

基　　金：国家重点基础研究发展计划(973计划)(2006CB601206)

摘　　要：为了对含面芯层间脱胶缺陷的蜂窝夹芯板在侧向压缩载荷作用下的典型破坏模式进行数值预报,建立了基于蔡-希尔破坏准则和粘结模型的计算模型。该计算模型是建立在对蜂窝夹芯板的双悬臂梁(DCB)和单臂梁(SLB)试验中所发现的一种新的破坏模式的分析基础之上的。对蜂窝夹芯板的侧向压缩破坏行为的数值预报中,发现一种新的破坏模式:位于脱胶区域的面板首先发生局部屈曲失稳,随后面板内部靠近芯子的45°/0°层间出现分层,与此同时最靠近芯子的45°铺层发生断裂,伴随着45°/0°层间分层的扩展,面板发展成为对称性整体屈曲失稳。与侧向压缩试验测试结果对比发现,计算模型模拟中所预报的破坏模式在实验测试中也得到了很好的验证。Based on the Tsai - Hill failure criterion and the cohesive zone model, a computational model was proposed to predict a typical damaged mode for honeycomb sandwich panels containing interfacial debonding under end compressive loading. The proposed model was built up based on a new failure mode, which is observed in the double cantilever beam （DCB） and the single leg bending （SLB） tests for honeycomb sandwich panels. The prediction results show that the end compressive failure occurs according to the following procedure： starting with local buckling of the debonding facesheet, followed by the initiation of interlaminar delamination between 45° ply and 0° ply, and meanwhile, the fracture of 45° ply, then the rapid propagation of interlaminar delamination between 45° ply and 0° ply, and finally, ending in the symmetrical global buckling of facesheets. Compared with the results of the end compressive test, the new failure mode predicted in the simulation is validated well in the experiment.

关 键 词：界面脱胶 蜂窝夹芯 蔡一希尔破坏准则 粘结模型 层间分层 

分 类 号：TB333[一般工业技术—材料科学与工程]