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在各轴扭转运动方程的基础上,用振型叠加原理求得中间减速器及尾减速器的传动比不等于1时尾传动系统扭转振动的解,并分析了中间减速器及尾减速器的传动比对直升机尾传动系统扭转振动的影响。其结果表明:与中间减速器及尾减速器的传动比等于1的尾传动系统相比,中间减速器或尾减速器的传动比接近且大于1时,水平传动轴和尾斜轴的扭转频响函数的最大幅值增大,尾传动系统的第2阶扭转固有频率增大,第3阶扭转固有频率变化不大,大于第3阶的扭转固有频率近似不变。
Based on the equations of torsional motion of each shaft, the solution of the torsional vibration of the tail-drive system with the transmission ratio of the intermediate reducer and the final reducer is not equal to 1, and the influences of the intermediate reducer and the final reducer Effect of Transmission Ratio on Torsional Vibration of Helicopter Tail Drive System. The results show that the torsional frequency of the horizontal drive shaft and the trailing shaft is higher than that of the rear drive system with the gear ratio of the intermediate reducer and the final reducer being equal to 1 when the gear ratio of the intermediate reducer or the final reducer is close to and greater than 1 The maximum amplitude of the loud function increases, the natural frequency of the second order torsion of the tail drive system increases, and the natural frequency of the third order torsion does not change much. The natural frequency of torsion greater than the third order is approximately the same.