Novel destructive method is implemented for quantitative assessment of fatigue damage accumulation in the stress concentration zone near the cold-expanded hole, which is characterized by residual stress influence. Damage accumulation is reached by preliminary push–pull loading of plane specimens with cold-expanded holes. Artificially introduced narrow notches, emanating from the hole edge at different stages of low-cycle fatigue, serve to manifest a damage level. Deformation response to local material removing is measured by electronic speckle pattern interferometry (ESPI) in terms of in-plane displacement components. Notches are inserted under constant external load to increase the measurement accuracy by reaching optimal fringe density. Normalized values of the notch mouth open displacement (NMOD), in-plane displacement component acting in the notch direction (U), the stress intensity factor (SIF), the T-stress and the biaxiality ratio are used as current damage indicator. Numerical integration of curves, describing an evolution of each fracture mechanics parameter, produces the damage accumulation function in an explicit form. It is established that all five fracture mechanics parameters give very close results. Developed approach is the essential link in predictable joints design to reach maximal beneficial effect of cold hole expansion on the fatigue life improvement of advanced aerospace structures.

采用新型破坏性方法对冷扩孔附近应力集中区疲劳损伤累积进行定量评估，该区域受残余应力影响。损伤累积是通过对带有冷扩孔的平面试样进行初步推拉加载来实现的。在低周疲劳的不同阶段，从孔边缘发出的人为引入的窄槽口用于显示损坏程度。对局部材料去除的变形响应是通过电子散斑图案干涉法 (ESPI) 根据面内位移分量测量的。在恒定外部负载下插入凹槽，以通过达到最佳条纹密度来提高测量精度。槽口张开位移（NMOD）的归一化值，作用在缺口方向 (U) 上的面内位移分量、应力强度因子 (SIF)、T 应力和双轴度比用作电流损伤指标。曲线的数值积分，描述每个断裂力学参数的演变，以明确的形式产生损伤累积函数。已确定所有五个断裂力学参数都给出了非常接近的结果。开发方法是可预测的接头设计中必不可少的环节，以达到冷扩孔对先进航空航天结构疲劳寿命提高的最大有益效果。以显式形式产生损伤累积函数。已确定所有五个断裂力学参数都给出了非常接近的结果。开发方法是可预测的接头设计中必不可少的环节，以达到冷扩孔对先进航空航天结构疲劳寿命提高的最大有益效果。以显式形式产生损伤累积函数。已确定所有五个断裂力学参数都给出了非常接近的结果。开发方法是可预测的接头设计中必不可少的环节，以达到冷扩孔对先进航空航天结构疲劳寿命提高的最大有益效果。