直升机结构响应主动控制试验研究  

Experimental Study on Active Control of Structural Response for Helicopters

作　　者：胡俊[1] 顾仲权[1] 马扣根[1] 

机构地区：[1]南京航空航天大学航空宇航学院

出　　处：《振动工程学报》2002年第2期125-129,共5页Journal of Vibration Engineering

摘　　要：直升机飞行中机体的振动水平是所有飞行器中最为严重的 ,必须采取振动控制措施 ,而结构响应主动控制是目前被公认为能大幅度降低机体振动水平的、具有实用价值的减振新技术。本文综述在直升机结构响应主动控制实验室内试验研究中的几项主要工作 ,包括作动器形式的选取与伺服液压式惯性型作动器的研制、多通道控制中收敛因子的确定 ,以及多通道控制的试验研究 ,研究结果证实作者研制的作动器与测控系统能实现有效的减振。The vibration levels of helicopter fuselage during flight are most serious, comparing to all other type of aircrafts. It is necessary to develop the means of vibration control. Nowadays active control of structural responses (ACSR) is considered as most practical technique for reducing vibration levels. Some of the key experimental studies in laboratory for active control of structural responses are summarized in this paper, including the selection of the types for active inertial actuators and its fabrication, the determination of convergence factor in multi channel control, the test of multi input/multi output control for structural vibration of the helicopter. The results show that the active inertial actuator,the measurement and control system can be effectively served for the purpose.

关 键 词：直升机 结构响应 主动控制 试验研究 动态试验 

分 类 号：V214[航空宇航科学与技术—航空宇航推进理论与工程]