直升机尾传动系扭转振动的分析

Torsional Vibration Analysis for a Helicopter Tail Drive System

在简化直升机尾传动系结构的基础上,根据轴段的扭转动力学方程,用分离变量法获得轴段的扭转主振型。再根据轴段、支点的扭转动力学方程和边界条件,用振型叠加原理求得尾传动系扭转振动的精确解,并进行了扭转振动分析。提出直升机的尾传动系是多个轴段和圆盘的串联系统。给出了尾传动系扭转频响函数的变化幅值的测试方法。

Based on simplifing a structural of a helicopter tail drive system, from the torsional dynamic equations of shaft segment, the modes of vibration are derived by the variable separation method. According to the boundary conditions and the torsional dynamic equations of shaft segment and disks, the exact solution of torsional vibration of a tail drive system is obtained by the superposition principle of modes of vibration. The torsional vibration is analyzed. It is presented that a helicopter tail drive system is a series of systems with shaft segment and disks. A measure method of variable amplitude of torsional frequency response function for a tail drive systern is given.