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采用台架试验装置对某型飞机平尾轴进行了疲劳试验,通过断口的观察分析、断口部位的金相分析、硬度检测、有限元结构应力分析,确定了平尾轴的失效模式,并对其断裂失效原因进行了分析。结果表明:平尾轴的断裂性质为疲劳断裂,裂纹源均起源于大轴筒体内壁加工刀痕形成的沟槽处,变截面圆弧造成的结构应力集中和粗糙加工刀痕形成的附加应力集中是造成大轴疲劳断裂的主要原因。
The fatigue test was carried out on the flat-tail shaft of a certain type of aircraft by a bench test device. Through the observation and analysis of the fracture, the metallographic analysis of the fracture site, the hardness detection and the stress analysis of the finite element structure, the failure mode of the horizontal tail shaft was confirmed and the fracture Failure causes were analyzed. The results show that the fracture of the flat-tail shaft is a kind of fatigue fracture. The sources of cracks originate from the grooves formed by the machining marks on the inner wall of the large-diameter cylinder. The stress concentration in the structure caused by the arc of the variable cross-section and the additional stress concentration in the formation of the rough machining marks Is the main cause of fatigue fracture shaft.