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从飞机零件破坏的断口上观察的解理疲劳条纹表明:解理疲劳破坏断口上疲劳区的面积大于瞬时断裂区,断口边缘基本上没有剪切唇;在同一微区,解理疲劳裂纹扩展方向的不一致性比较明显,二次裂纹也较多;解理疲劳条纹的间距并非远大于延性疲劳条纹的间距;匹配断口的观察进一步表明解理疲劳裂纹及条纹基本上是凹凸对应的。最后,本文对传统的解理疲劳条纹形成机理提出了一些修正。
The cleavage fatigue fringes observed from the broken parts of aircraft parts show that the area of the fatigue zone on the cleavage fatigue failure fracture is larger than the instantaneous fracture zone and there is almost no shear lip on the fracture edge. In the same micro-zone, the fatigue crack propagation direction The inconsistency is more obvious, and there are more secondary cracks; the spacing of the cleavage fatigue stripes is not much larger than that of the ductile fatigue stripes; the observation of the matching fracture further shows that the cleavage fatigue cracks and stripes are basically corresponding to the bump. Finally, some amendments are proposed to the formation mechanism of traditional cleavage fatigue stripes.