基于H_∞控制和μ控制的二元机翼颤振主动抑制分析

Flutter active suppression of two-dimensional airfoil based on H_∞ controller and μ controller

针对二元机翼颤振主动抑制问题,对二元翼段颤振控制律的设计以及风洞实验验证展开了深入研究。首先,基于Theodorsen非定常气动力理论建立了该翼段模型的运动状态方程。其次,基于鲁棒控制理论设计了H_∞控制器和μ控制器,分别与二元翼段气动弹性系统共同组成了机翼颤振主动控制系统。最后,采用数值仿真和风洞实验相结合的方式,对H_∞控制器和μ控制器的颤振控制效果进行了验证。研究结果表明:H_∞控制器和μ控制器都能有效抑制颤振的发生,可将机翼颤振临界速度由15.45 m/s提高到27 m/s以上。且μ控制器在颤振主动抑制中的颤振抑制收敛时间更短,颤振抑制风速上限更高,具有更好的鲁棒稳定性和鲁棒性能。

Aiming at the flutter active suppression of two-dimensional airfoil, the control law of flutter active suppression and the wind tunnel experimental verification were researched. First, the airfoil＇s equation of motion state was established based on Theodorsen unsteady aerodynamic theory. Then, the H∞ controller and the μ controller were designed based on the robust control theory and constituted the airfoil flutter active control system with pneumatic elastic system of two-dimensional airfoil. Finally, the control effect of H∞ controller and μ controller was verified by numerical simulations and wind tunnel experiments. The results indicate that both H∞ controller and μ controller can make the flutter speed of two-dimensional airfoil increase from 15.45 m/s to 27 m/s. Besides, the μ controller has shorter flutter active suppression convergence time and higher flutter active suppression wind speed, so the μ controller has better robust stability and robust performance.