直升机结构响应自适应控制的频域双LMS法

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。本文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。

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

As to traditional active control of structural responses for helicopter, control output is obtained according to deterministic optimal principle, the computation amount of which is large. The output is sensitive to external disturbances especially at the beginning of control. Based on the Least Mean Square (LMS) which is small computation amount and less adjustment parameters, a new modified method—Dual LMS is proposed, by which frequency response matrix of control path and the amplitude of external excitation response are identified. Simulation is conducted based on true flight measured data and measured frequency responses of control path for a typical helicopter. Result shows 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, which possesses more robustness.