论文部分内容阅读
针对飞机结构中过盈配合对无载孔疲劳寿命的影响开展了研究,通过试验对比分析了普通铆接试验件和过盈量1%铆接试验件。结合有限元分析,采用多轴疲劳理论对不同过盈量的铆接紧固孔在疲劳载荷下的损伤参量进行研究,确定过盈量对疲劳损伤的影响规律。实验结果表明:过盈量为1%铆接紧固件可提高紧固孔的疲劳寿命15%左右;通过有限元分析,适当的过盈量可降低紧固孔的应力幅和应变幅,进而降低疲劳损伤参量。
Aiming at the influence of the interference fit in the aircraft structure on the fatigue life of the no-load hole, the common riveted test pieces and 1% riveting test pieces of the interference are analyzed and contrasted by experiments. Combined with the finite element analysis, the multi-axial fatigue theory was used to study the damage parameters of the interference fasteners with different interferences under fatigue load, and the influence rules of the interference on the fatigue damage were determined. The experimental results show that the interference of fasteners can improve the fatigue life of the fastening hole by about 1%. The finite element analysis shows that proper interference can reduce the stress amplitude and strain amplitude of the fastening hole, Fatigue damage parameters.