含多裂纹连接结构损伤容限试验研究

EXPERIMENTAL INVESTIGATION FOR DAMAGE TOLERANCE OF FASTENER JOINT IN PRESENCE OF MULTIPLE SITE DAMAGE

针对机翼典型对接结构，进行了平板空孔试样和螺栓搭接件在等幅谱及飞－续－飞谱下的多裂纹损伤容限试验，通过该试验开展多裂纹开裂模式及多裂纹扩展规律的试验研究，为多裂纹断裂力学理论分析、多裂纹结构剩余强度准则提供试验依据。

The fatigue experimental studies of some multiple holed and cracked plates and fastener joints exposed to constant amplitude as well as flight by flight loading spectra have been carried out for the damage tolerance evaluation of typical aircraft wing structural components. The experimental results have shown some major features and models of multiple crack initiation and growth, which provide the experimental evidence served for the study of multiple site fracture theory and residual strength criterion in multiple cracked structures.