南京航空航天大学学报2011，Vol.43Issue(3)：308-311,4.
旋翼系统模态阻尼数值计算方法
Numerical Method for Computing Modal Damping of Rotor System
王华明 1王安武 1何瑞恒 1王浩文2
作者信息
- 1. 南京航空航天大学直升机旋翼动力学重点实验室,南京,210016
- 2. 清华大学航天航空学院,北京,100084
- 折叠
摘要
Abstract
A dynamics model of the rotor system based on Hamilton principle is established to compute vibration frequency and modes. The excitation at the frequency of a certain mode is applied to blades with the rotor in a stable hover state, and withdrawed when the rotor arrives at a new stable state. The response of the blade in the free decay progress is recorded. Modal damping is calculated by using the moving-block method. This method can compute any modal damping of the rotor system under different working conditions. Moreover, excitation can be applied to each degree of freedom of the blade according to the mode with the same phase, so that the blade vibrates according to this mode. The method breaks through the limitation of excitation location, frequency and phase in the rotor dynamics test to obtain comprehensive dynamic characteristics of rotor systems.关键词
数值模拟/移动矩形窗法/模态阻尼Key words
numerical simulation/ moving-block method/ modal damping分类
航空航天引用本文复制引用
王华明,王安武,何瑞恒,王浩文..旋翼系统模态阻尼数值计算方法[J].南京航空航天大学学报,2011,43(3):308-311,4.
