基于加权最小二乘法辨识的后缘襟翼智能旋翼振动载荷闭环控制仿真研究

Closed-loop vibration control simulation of a helicopter active rotor with trailing-edge flaps based on the weighted-least-squares-error identification method

智能旋翼是一种行之有效的直升机旋翼振动主动控制技术,针对后缘襟翼式智能旋翼振动闭环控制问题,建立了带后缘襟翼旋翼气弹耦合动力学模型,并对后缘襟翼进行了开环控制仿真。通过对后缘襟翼扫幅、扫频和扫相分析,研究了后缘襟翼偏转运动的幅值、频率与相位对旋翼振动载荷的影响,采用高阶谐波控制算法,结合加权最小二乘法辨识系统传递矩阵,并考虑驱动器饱和现象,进行了后缘襟翼智能旋翼闭环控制仿真。仿真结果表明旋翼通过频率垂向振动载荷降幅最高达到87%,取得了良好的控制效果,为后缘襟翼智能旋翼闭环控制系统工程实现提供参考。

An active rotor is effective active vibration control for helicopters.Focusing on closed-loop vibration control of an active rotor with active controlled flap(ACF),a coupled aero-elastic model with ACF was developed.Open-loop control simulation for the ACF was conducted through amplitude sweep,frequency sweep,and phase sweep,and their influence on rotor vibratory loads was studied.The higher harmonic control algorithm was employed in the closed-loop control simulation,while the weighted-least-squares-error(WLSE)method was used to identify the transfer matrix of the active rotor system.Actuator saturation was also taken into account using the auto-weighting method.The controller demonstrates satisfying control performance,and the vertical vibratory load of passing frequency is reduced by up to 87%.The simulation results will be useful to direct the engineering implementation of the closed-loop control system for the active rotor.