基于动柔度法的二元机翼颤振主动控制试验研究

Experimental Study on Active Flutter Suppression for Two-dimensional Wing Based on Receptance Method

为了实现机翼的振动主动控制,以带后缘控制面的NACA0018型二元机翼为研究对象,研究了动柔度法在振动主动控制中的应用。基于准定常气动力理论建立二元机翼的开环和闭环动柔度模型,采用PD控制器实现系统的极点配置目标。介绍了风洞振动试验的系统组成及试验装置。试验结果表明,基于动柔度法的极点配置理论在无需确实系统的质量、阻尼和刚度特性的前提下能够有效地实现二元机翼系统的振动主动控制,获得期望的动态特征,且系统具有良好的鲁棒性。

In order to suppress flutter for aircraft wing effectively, research on the application of recep-tance method was conducted on a two-dimensional wing with a tailing-edge control surface. The open and closed-loop receptance model was established based on quasi-steady aerodynamics force;The pole as-signment was achieved by using PD controller. In addition, the experimental rig was introduced detailed-ly before carrying out the wind tunnel test. The result of the experiment indicates that there being no re-quirement at all for the mass, stiffness and damping matrices, the active flutter suppression was success-fully achieved by using measured receptance, and the dynamic characteristics and strong robustness of system were expressed by processing the test.