摘要
基于复合材料层合板静强度的"平均应力准则"和经典的指数函数疲劳预测理论以及所提出应力修正因子β,建立了一种带孔的复合材料层合板疲劳预测模型。针对复合材料T300/KH304进行了带孔层合板在不同应力水平下的疲劳试验研究及模型验证,模型预测结果满足工程要求,为含圆孔层合板S-N曲线的预测提供了简单、快捷、实用的方法。
T300/KH304, which is recently studied in aviation, is a high capability composite material. To predicate the fatigue life of an aero-engine structure mode by this composite, the notched laminates were mainly investigated. Based on the fatigue model laminates and average stress criterion of static strength for the composite material laminates with a circular hole, a new fatigue model of composite material laminates was presented. According to the experiment data of static strength and fatigue of notched laminates, the stress correct factor β was presented. The fatigue analysis and tests were carried under the difference stress levels. In the future this method could be used for the predication of S-N curve of other composite materials plate with a circular hole.
出处
《材料工程》
EI
CAS
CSCD
北大核心
2004年第3期18-20,共3页
Journal of Materials Engineering
基金
航空发动机结构强度"九.五"项目预研课题(2 4. 8. 1 . 2 6 )
