摘要
本文提出了一种新的工程-解析方法,导出了飞机平尾大轴孔边角裂纹应力强度因子的封闭解。这种能量释放率方法非常节省机时,可以获得大量系统的新结果。
Corner cracks often appear in the shaft of aeroplane all-moving stabilizer near a hole. It's an urgent need to know the stress intensity factors of this kind of cracks in damage tolerance design. This problem is more complicated than the case of flat plates with corner cracks emanating from a hole. It's very inconvienent even using finite element method.In this paper, a new analytical-engineering method of a closed form solution about stress intensity factors for the shaft of aeroplane all-moving stabilizer (circular tube) with corner cracks near a hole is derived by means of energy release rate method. This method is very time-saving. Since a complete series of useful results of stress intensity factors can be obtained. The solution can be used in damage tolerance design.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1990年第9期A424-A432,共9页
Acta Aeronautica et Astronautica Sinica
关键词
应力强度因子
飞机平尾大轴
孔边角裂纹
能量释放率
stress intensity factor
shaft of aeroplane all-moving stabilizer
corner cracks emanating from a hole
energy release rate
