基于超声电机作动器的翼段颤振主动抑制

Active flutter suppression of an airfoil model using ultrasonic motor

研究采用超声电机作为作动器来实现含控制面的翼段颤振主动抑制。首先,通过实验获得超声电机的频率响应,经过非线性最小二乘法进行物理参数识别,建立了超声电机作动器的传递函数模型。然后,设计了具有控制面的翼段颤振实验模型,建立了机翼-控制面的三自由度气动弹性方程,设计了输出反馈的次最优控制律。数值仿真和风洞试验结果表明,以超声电机作为控制面作动器可以有效地抑制机翼颤振,并将颤振临界速度提高了13.4%。

This paper presents the use of the ultrasonic motor, which features high torque at low speed, small size and low weight, as an actuator in the flutter control of a two-dimensional airfoil section with control surface. The paper starts with the design of a two-dimensional airfoil model with a control surface driven by an ultrasonic motor. Then, it gives the experimental modelling of the servo. Afterwards, the paper establishes the dynamic equation of the aeroservoelastic system based on Theodoson＇s aerodynamic load, and presents the numerical simulations for the sub-optimal control of flutter. Finally, the paper outlines the experimental study of the flutter control of the airfoil section in a wind tunnel test, where the critical flutter speed of the controlled system is increased by 13.4%, and the flutter is effectively suppressed when the flow velocity exceeded the critical flutter velocity of the uncontrolled system.