作　　者： ; ; ; ;

机构地区： 南京航空航天大学能源与动力学院

出　　处： 《南京航空航天大学学报》 2009年第2期181-186,共6页

摘　　要： 采用细观力学方法研究了纤维泊松收缩对陶瓷基复合材料迟滞回线的影响。采用库仑摩擦法则描述脱粘区界面剪应力分布,结合拉梅公式得到了界面脱粘区和粘结区的细观应力场。根据卸载与重新加载时纤维相对基体滑移机制,分析了加、卸载纤维轴向应力分布,假设纤维轴向应力在界面脱粘尖端连续得到了初载时界面脱粘长度ls、卸载时界面反向滑移长度y以及重新加载时界面滑移长度z′,讨论了纤维泊松比、纤维体积百分数和界面摩擦系数对加卸载界面滑移长度、迟滞回线的影响。由于考虑了纤维泊松收缩的影响,预测的迟滞回线面积及卸载残余应变大于Pryce-Smith模型预测值。 The effects of fiber Poisson contraction on fatigue hysteresis loops of ceramic matrix compos- ites are analyzed using a micromechanical approach. A Lame formulation incorporated with Coulomb friction law is adopted to solve the micro stress field in the interface de-bonding and bonding region. Based on the mechanisms of the fiber sliding relative to the matrix during unloading and reloading, the fiber axial stress distribution during unloading and reloading is analyzed. The interface de-bonding length ls during first loading, the interface counter-slip sliding length y during unloading and the inter-face sling length z′ during reloading are determined through fiber axial stress continuous at the interface de-bonding tip. The influence of fiber Poisson ratio, the fiber volume fraction and the interface friction coefficient on the fiber/matrix interface sliding and the stress/strain hysteresis loops is discussed. Considering the effect of fiber Poisson contraction, the hysteresis loop area and the unloading residual strain predicted by the present analysis are larger than those predicted by the Pryce-Smith model.

关 键 词： 陶瓷基复合材料 疲劳 迟滞回线 库仑摩擦 泊松收缩

领　　域： [一般工业技术] [航空宇航科学与技术] [航空宇航科学技术]