摘要
介绍了当前国内外机械连接干涉配合强化技术的理论和实验研究的状况。简要说明了干涉配合和冷胀孔(I-E)综合强化方法产生的重大技术效益。对比分析了强化孔和非强化孔试件,在变载荷作用下疲劳裂纹的行为。指出强化孔试件厚向和α向裂纹扩展速率的明显差异现象(dc/dN<da/dN),和相应的裂纹扩展模型对构件疲劳寿命的影响。
Theoretical and experimental investigation is introduced for the recent development of interference-fit strengthen technique. This paper will probe into the strengthen theory, in which the analysis of stress-strain field around the hole is put first, and point out the achievement obtained in the experimental investigation of strengthen effects and mechanism. The most significant benefit caused by the combined strengthen method of interference-fit and cold expanding (I-E) is briefly illustrated.The fatigue crack growth behaviour characters under cyclic load of samples with and without strengthening are compared and analysed. The clear difference of the crack propagation rate between the direction of thickness and the direction of (a) in the strengthened samples (dc/dN<da/dN) is pointed out and briefly explained, and the corresponding crack propagation models are set up as well. Some enlightenments are finally introduced.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1990年第12期B515-B522,共8页
Acta Aeronautica et Astronautica Sinica
关键词
干涉配合
强化技术
冷胀孔
航空器
intetference-fit strengthening, cold expanding of hole, cold-working fatigue.
