作　　者： ; ; ; ;

机构地区： 南京航空航天大学能源与动力学院

出　　处： 《航空动力学报》 2010年第3期597-602,共6页

摘　　要： 采用细观力学方法研究了界面层参数对陶瓷基复合材料单轴拉伸行为的影响.在剪滞模型基础上提出了考虑界面相与界面层效应的力学简化模型,结合临界基体应变能准则、最大剪应力准则、临界纤维应变能准则确定基体裂纹间距、界面脱黏长度和纤维失效百分数,对考虑界面层影响的陶瓷基复合材料拉伸应力-应变曲线进行了模拟,讨论了界面层体积分数、弹性模量及泊松比对拉伸行为的影响,并与试验结果进行了对比,发现考虑界面层及界面相的影响时,界面脱黏和纤维失效段应力-应变曲线与试验数据更接近,预测效果更好. The effect of interface layer parameters on the uniaxial tensile stress-strain behavior of ceramic matrix composites has been investigated using micro-mechanic approaeh. The simplified micro mechanic model, whieh considered the effects of the interfaee layer on the mechanical proper ties of fiber reinforced ceramic composites, was proposed based on the classic shear-lag model. The critical matrix strain energy criterion, maximum interface shear stress criterion and the critical fiber strain energy criterion were used to determine the matrix crack space, interface debonding length and the fiber failure fraction. The stres-strain curve was modeled with consideration of the effeets of interface layer. And the influenees of interfaee layer volume fraction, elastic modulus and Poisson ratio on the stres-strain curve were also discussed. The stress-strain curve predicted by the present analysis with compared the experimental data,and it was found that the interface debonding and fiber failure part of the tensile stree-strain curve agree well with the experimental data on consideration of the effect of interface layer or interface phase.

关 键 词： 陶瓷基复合材料 界面层 基体开裂 界面脱黏 纤维失效 应力 应变曲线 剪滞模型

领　　域： [航空宇航科学与技术] [航空宇航科学技术]