摘要
用扫描电镜观察了某型飞机机翼主梁的疲劳断口 ,用疲劳条带估算了裂纹扩展寿命 ,并用 Zheng- Hirt公式估算出裂纹尖端应力强度因子范围 ,估算结果与实验测定值十分接近 ,从而为研究老龄飞机的使用寿命 。
The fatigue fracture of wing spar in type X finhter is observed with scanning electron microscope Both the crack propagation life and the amplitude of stress intersity factor are estimated with fatigue strition and Zheng Hirt formula The estimation is very close to the results of experiment It is a useful attempt to study the service life of old fighters
出处
《材料工程》
EI
CAS
CSCD
北大核心
2001年第10期42-44,共3页
Journal of Materials Engineering
