直升机结构响应主动控制频域法的改进算法  

Modified Methods of Active Control of Structural Responses for Helicopter in Frequency-Domain

作　　者：赵灿峰[1] 顾仲权[1] 

机构地区：[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

出　　处：《振动．测试与诊断》2011年第5期631-636,667-668,共6页Journal of Vibration,Measurement & Diagnosis

摘　　要：传统的频域结构响应自适应控制都是基于确定性最优准则求控制量,该方法计算量大,且对外扰敏感,常常导致求得的电压有较大波动,尤其在控制开始时刻。为抑制发散及增加平稳性,在传统方法的基础上,提出了双归一化LMS法,对控制通道频响矩阵与外扰响应幅进行在线识别与最优控制量求取均采用NLM S法;在参数识别采用LM S法的基础上,进行Kalman二次滤波。仿真结果表明了两种改进方法的有效性。As to traditional active control of structural responses(ACSR) for helicopter in frequency-domain,the control output is obtained according to deterministic optimal principle,the computation cost of which is large.The output is sensitive to external disturbances especially at the beginning of control.Aiming at the targets that effectively restrain divergence and smooth control output,two new modified methods are proposed based on a traditional technique.One is dual normal least mean square(NLMS) method in which frequency response matrix of control path and the amplitude of external excitation response are identified.The other is L&K method that the needed variables are identified by Kalman filtering after primary identification of LMS method.Simulation results show the effectiveness of these two methods.

关 键 词：频域 结构响应主动控制 确定性最优原则 最小均方法 KALMAN滤波 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计] TB535[理学—物理]