超音速飞行器机翼颤振的时滞反馈控制

Tim e-Delayed Feedback Control of Flutter for Supersonic Airfoils

采用时滞反馈主动控制方法对超音速飞行器机翼颤振进行控制,以提高飞行器机翼系统的颤振临界速度.首先根据二元机翼的力学模型,制定时滞反馈控制策略并建立时滞反馈控制系统的数学模型;分别对无控、零时滞反馈控制和有时滞反馈控制系统进行稳定性分析,获得时滞反馈控制系统的颤振稳定性边界.利用MATLAB/SIMULINK进行时域数值模拟,验证理论稳定性分析结果的正确性.结果表明:通过调节时滞量,可有效提高飞行器机翼的颤振临界速度,且控制策略简单,效果较好.

An active delayed feedback control technique was proposed to control the flutter of supersonic airfoils. It＇s intended to increase the critical flowvelocity. Firstly,the delayed feedback control strategy was designed to suppress the flutter of the 2D airfoil,in turn the delayed differential equations（DDEs）were formulated for the controlled system under consideration. Then,the stability of the uncontrolled system,the non-delay feedback controlled system and the time-delayed feedback controlled system were analytically determined,respectively,and the flutter stability boundary of the delayed feedback controlled system as a function of the time delay was predicted. Finally,numerical simulation in time domain with the MATLAB / SIMU LINK software was made to demonstrate the effectiveness of the present theoretical analysis results. The results showthat,the critical flowvelocity is significantly increased through regulation of the time delay magnitude,and the proposed delayed feedback control strategy for flutter control of supersonic airfoils is not only valid but also easily applicable to engineering structures.