摘要
为评估某型飞机中央翼下壁板萌生疲劳裂纹后的使用安全性 ,进行结构模拟件疲劳试验 ,并利用AFGROW软件对其疲劳裂纹的扩展寿命进行估算 ,与试验结果进行对比 ,初步确定出该部位裂纹扩展速率 。
Fatigue crack was found in the lap joint panel of the central wing lower structure in an aircraft. To assess the safety of the structure, simulated structure specimen was designed and fatigue test was performed under design fatigue load. Test results were reported,and analyzed crack growth cycles predicted by the AFGROW software package compared and agreed well with test results. It also gave suggestion for the repair of crack failure.
出处
《机械强度》
CAS
CSCD
北大核心
2004年第z1期234-236,共3页
Journal of Mechanical Strength
关键词
疲劳裂纹
裂纹扩展
寿命估算
Fatigue crack
Crack growth
Life prediction
