直升机结构响应自适应控制的频域双LMS法  

Dual-LMS method in frequency domain for active control of structural responses of a helicopter

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：《振动与冲击》2010年第5期195-198,共4页Journal of Vibration and Shock

摘　　要：传统的频域结构响应自适应控制都是根据确定性最优准则求得控制量,这种方法计算量大,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。提出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的双LMS法。对某型直升机空测数据与其控制通道频响函数实测数据进行仿真,结果表明改进方法在保证控制效果和识别结果与原方法基本不变的同时,不仅能大大降低计算量,减少调整参数,而且能有效地缓和控制量的波动,具有更好的鲁棒性。For traditional active control of structural responses of a helicopter,control output is obtained according to deterministic optimal principles,its computation amount is large.The output is sensitive to external disturbances,especially,at the beginning of control.Based on the Least Mean Square(LMS) with small computation amount and less adjustment parameters,a new modified method-Dual LMS was proposed,using it the frequency response matrix of the control path and the amplitude of response to external excitation could be identified.Simulations were conducted based on true flight data measured and frequency responses measured of control path of a typical helicopter.Result showed that the modified method not only can guarantee the effects of control and identification,but also can greatly reduce computation amount and adjustment parameters,and effectively smooth control output,it possesses more robustness.

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 直升机 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计]