摘要
对飞机机翼构件在不同载荷谱下的宏、微观断裂特征进行了观察与分析 ,并结合载荷谱中的应力变化特点 ,对A飞机和 B飞机机翼构件在不同载荷谱下的裂纹扩展寿命进行了反推。结果表明 ,载荷谱中不同的应力变化在失效构件断口上反映出不同的宏、微观断裂特征 ,采用断口定量分析技术可反推构件的疲劳寿命 。
The macro and micro fracture characteristics of wing structures on two load spectra were observed Crack spread life on different load spectra for wing structures on A and B airplane was retroestimated on account of stress distribution respectively The results show that different macro and micro fracture characteristics on fatigue spread zone are formed with the variety of stress distribution in a load spectrum The fatigue life of engineering structure can be retroestimated by means of fracture quantity analysis Also, the crack formation sequence can be obtained
出处
《材料工程》
EI
CAS
CSCD
北大核心
2002年第5期42-45,共4页
Journal of Materials Engineering
关键词
载荷谱
断口定量分析
寿命反推
疲劳弧线
load spectrum
fracture quantity analysis
fatigue life retroestimation
fatigue line
