直升机结构响应主动控制飞行试验  

Flight test of active control of structure response for helicopter

作　　者：陆洋[1] 顾仲权[1] 凌爱民[2] 李明强[2] 

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,江苏南京210016 [2]中国直升机设计研究所,江西景德镇333001

出　　处：《振动工程学报》2012年第1期24-29,共6页Journal of Vibration Engineering

摘　　要：为验证结构响应主动控制方法在直升机振动控制中的有效性,以某轻型直升机为验证机,基于具有在线识别功能的时域自适应控制算法,进行了直升机结构响应主动控制飞行试验研究。给出了飞行试验方法、试验系统组成、试验内容及其过程。通过对飞行试验数据的处理分析,对减振效果进行了评估。试飞结果表明:ACSR(Active Control of Structure Response)系统对各测点的垂向振动均有减振效果,各速度状态下的全机垂向减振效率在30%～66%之间,巡航速度状态下具有最佳的减振效率;此外,各测点的侧向振动水平也有一定程度的减小。In order to verify the validity for the method of active control of structural response（ACSR） in helicopter vibration reduction,the flight tests are carried out on a lighter helicopter based on the adaptive control algorithm with online identification in time domain.Details about the ACSR system composing and the scheme of the flight tests are brought forward.Then,summary and analysis of the flight test data are given.The results of flight tests show that when the ACSR system is working,the vertical vibration level of every evaluation points can be reduced,and the reduction efficiency of total helicopter is between 30% and 66% at different flight speeds;best efficiency can be acquired at cruise speed.At the same time,to some extent,vibration reduction in lateral direction can be observed as well.

关 键 词：直升机 结构响应主动控制 飞行试验 减振 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程] V417