摘要
对整体加肋板进行了疲劳裂纹扩展试验，分析了结构疲劳裂纹扩展的基本特性及规律，讨论了应力强度因子工程计算方法，为整体加肋板的损伤容限评定及设计提供了依据。
Fatigue crack growth of panel and rib integral structures has been investigated. Based on the experimental data, the basic characteristics and regularities of the fatigue crack growth of the integral structures are analyzed and an engineering computational method of stress intensity factors for the integral structures is discussed. The conclusions drawn in this paper can be used for damage tolerance assessment and design of the panel and rib integhral structures.
出处
《机械科学与技术》
CSCD
北大核心
1999年第6期983-984,共2页
Mechanical Science and Technology for Aerospace Engineering
关键词
整体加肋板
疲劳裂纹扩展
应力强度因子
飞机
Panel and rib integral structure, Fatigue crack growth, Stress intensity factor
