中文摘要：

在交变载荷作用下,小孔构件易产生疲劳裂纹,零件的使用寿命因此降低。为了研究制孔工艺对激光冲击强化前后小孔疲劳寿命的影响,文中选用材料为铝合金7050-T7451的双联试样进行激光强化试验,并使用不同的制孔工艺开孔,随后进行拉伸试验,试验后观察断口的疲劳源位置、孔壁质量,并测量孔壁粗糙度。试验研究表明,对于未进行激光冲击强化的试件,不同的制孔工艺对小孔件寿命无明显影响;对于激光冲击强化后的试件,使用不同的制孔工艺对小孔件寿命差异较大;因此在激光强化前后,制孔工艺对小孔件的疲劳寿命影响是不同的。

英文摘要：

Hole components can easily produce fatigue cracks thus reducing hole fatigue life in the role of alter- nating load. The paper studies the effect of the drilling technology on the hole fatigue life with aluminum alloy double samples of 7050-T7451, which are subjected to tensile test to observe the fracture fatigue source location, the hole- wall quality and roughness. Experiments show that different hole drilling technologies has little effect on the samples for non-laser shock peening, but it has great impact after laser shock peening.