缝合复合材料可用性——含孔层合板的疲劳性能  

Properties of Stitched Composite Laminates—Fatigue Performance of Composite Laminates with an Open-hole

作　　者：程小全[1] 邹健[1] 张纪奎[1] 郦正能[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《航空学报》2009年第5期867-871,共5页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(10672009);航空基础科学基金(05B51044);北京航空航天大学凡舟科研基金(20060501)

摘　　要：对含孔缝合复合材料层合板的疲劳性能进行了试验研究,考察了缝合及其方向对复合材料孔板拉伸疲劳损伤扩展规律的影响。通过有限元法分析了有、无缝合复合材料含孔板的应力分布状态,对缝合复合材料孔板的拉伸疲劳损伤及其扩展机理进行了分析。研究表明,缝合改变了复合材料含孔板的拉伸疲劳损伤起始与扩展的机理,缝合方向对含孔层合板的拉伸疲劳损伤的发生与扩展有比较明显的影响。层间剪切应力对45°缝合孔板内的损伤发生与扩展起着重要作用,而且45°缝合孔板可能会出现孔边损伤以外的其他主要损伤区。Experimental study was carried out on the fatigue performance of stitched composite laminates with an open-hole, in which the effect of stitching and its direction on the tensile fatigue damage propagation rule of the composite laminates with a hole was studied. The stress distribution of non-stitched and stitched laminates with a hole was calculated through finite element method （FEM）. Based on this, the mechanism of tensile fatigue damage origination and propagation of stitched laminates with a hole was analyzed. The results show that the mechanism for the tensile fatigue damage origination and propagation of laminates with a hole has been changed by stitching. Stitching direction has an obvious effect on tensile fatigue damage propagation. The interlaminar shear stress plays an important role in damage origination and propagation for 45° stitched laminates with a hole. It is likely that certain other main damage areas will arise with 45° stitched laminates with a hole in addition to the damage at the hole edge.

关 键 词：复合材料层合板 缝合 疲劳 刚度 损伤扩展 

分 类 号：V215.4[航空宇航科学与技术—航空宇航推进理论与工程] TB330.1[一般工业技术—材料科学与工程]