摘要
通过应变测量摸清某型飞机关键结构模拟件的疲劳危险部位及严重的受力状态 ,通过疲劳试验获得疲劳危险部位的裂纹扩展数据 。
The location of the fatigue critical and the serious load condition of the components simulating the key structure of a certain type aircraft were found out by strain gauging. The crack growth data with the load cycles within the fatigue critical location were obtained by fatigue tests. A engineering method defining the initial cracking life was put forward.
出处
《机械强度》
CAS
CSCD
北大核心
2004年第z1期222-225,共4页
Journal of Mechanical Strength
关键词
飞机结构
疲劳
裂纹扩展
裂纹起始寿命
Aircraft structure
Fatigue
Crack growth
Initial cracking life
