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.%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.
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