摘要
以歼教五机翼主梁疲劳断裂分析为例 ,介绍了用断口金相和Zheng -Hirt公式估算疲劳裂纹扩展寿命的方法 ,为研究老龄飞机的使用寿命问题 。
As an examole of analysing the fatigue crack of wing spar in type 5 Fighter-Trainer, The methods of crack propagation life prediction by means of fractography and Zheng-Hirt formula are ntrodued in this paper. Some useful study was carried out for predetermined service life of old fighters.
出处
《空军工程大学学报（自然科学版）》
CSCD
2001年第2期4-7,共4页
Journal of Air Force Engineering University(Natural Science Edition)
