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直升机行星齿轮保持架(简称行星架)是传动系统的重要部件,其可靠性对于直升机的飞行安全至关重要。行星架疲劳裂纹故障的发生、发展受多种因素影响,其故障诊断和寿命预测都有难度。为准确预测行星架疲劳裂纹寿命,研究了其裂纹故障发生、发展规律,提出了基于对数线性的方法,将裂纹扩展过程离散化处理,采用Paris公式,定量描述裂纹扩展速率,结合Miner准则,累积其疲劳损伤过程,最终得到随裂纹长度变化的行星架剩余使用寿命数值。利用有限元软件ANSYS Workbench的疲劳寿命模块对计算得到的数值结果进行了仿真对比,验证了方法的精确性和有效性。
Helicopter planetary gear cage (referred to as the planet carrier) is an important component of the transmission system, its reliability is essential for the helicopter flight safety. The occurrence and development of the fatigue crack fault of the planet carrier are affected by many factors, and its fault diagnosis and life prediction have difficulty. In order to accurately predict the fatigue crack life of the planet carrier, the occurrence and development of the crack fault were studied. Based on the logarithm linear method, the crack propagation process was discretized. The Paris formula was used to describe the crack propagation rate quantitatively. Combined with the Miner criterion, Accumulate its fatigue damage process, and finally obtain the remaining service life of the planet carrier with the change of the crack length. The finite element software ANSYS Workbench’s fatigue life module is used to simulate the calculated numerical results to verify the accuracy and effectiveness of the method.