限幅装置对直升机尾传动轴系统动力学行为的影响研究

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摘要直升机尾传动轴系统易超临界工作，采用一种新型的限幅装置对其进行跨临界减振研究。分别建立尾传动轴动力学方程组，限幅装置动力学方程组和弹性支承动力学方程组，并基于界面协调理论相互耦合，建立具有限幅装置的直升机尾传动轴系统耦合动力学方程组。通过数值算法求解系统方程组，分别研究了偏心量、预紧力、碰摩间隙、辅助支座与摩擦环间隙以及碰摩摩擦系数对系统幅频响应特性的影响规律。结果表明：尾传动轴和限幅装置之间的碰摩使系统产生了附加刚度，导致转轴在共振点处出现跳跃和滞后现象；同时，限幅装置可以有效的降低转轴过临界转速的振动幅值，但不同参数下的减振效果不同，在设计时需要考虑。本研究为直升机尾传动轴系统的减振设计提供理论指导。

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	朱海民1
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	陈蔚芳1
	朱如鹏1

关键词 ：限幅装置, 直升机尾传动轴, 耦合动力学, 碰摩, 减振

Abstract：The helicopter tail drive shaft system is accessible to operate in supercritical condition, so a new type of limiting device is employed to reduce its transcritical vibration. The dynamic equations of the tail drive shaft, the dynamic equations of the limiting device and the dynamic equations of the elastic support are established, respectively, and the coupling dynamic equations of helicopter tail transmission shaft system with limiting device are proposed based on the interface coordination theory. The system equations are solved by a numerical algorithm, and the effects of eccentricity, preload, rubbing clearance, clearance between auxiliary support and friction ring and rubbing friction coefficient on the amplitude-frequency response characteristics of the system are investigated, respectively. The results show that the limiting device can effectively reduce the over-critical amplitude of the system, and the damping effect is varied under different parameters, which needs to be considered in the design. The study provides theoretical guidance for the vibration reduction design of helicopter tail drive shaft system.

Key words： limiting device helicopter tail drive shaft coupling dynamics rub-impact vibration reduction

收稿日期: 2020-10-26 出版日期: 2022-04-15

引用本文:

朱海民1,2，陈蔚芳1，朱如鹏1. 限幅装置对直升机尾传动轴系统动力学行为的影响研究[J]. 振动与冲击, 2022, 41(7): 97-105.
ZHU Haimin1,2, CHEN Weifang1, ZHU Rupeng1. Effects of amplitude limit device on dynamic behavior of helicopter tail drive shaft system. JOURNAL OF VIBRATION AND SHOCK, 2022, 41(7): 97-105.

链接本文:

http://jvs.sjtu.edu.cn/CN/ 或 http://jvs.sjtu.edu.cn/CN/Y2022/V41/I7/97

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