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颤振主动抑制(AFS,Active Flutter Suppression)是气动弹性综合研究的活跃分支,对飞行器设计具有重要意义.以带后缘控制面的二元机翼为对象,研究滑模控制(SMC,Sliding Mode Control)用于气动弹性AFS的可行性与机理.基于准定常气动力理论建立二元机翼气动弹性系统模型,设计SMC的滑模切换面及状态反馈控制切换函数,以实现受控对象AFS,从相空间状态轨线的角度,阐述SMC使闭环系统稳定的根源.此外,还对SMC的鲁棒性及延时效应做了分析与讨论.研究表明:该控制策略可用于AFS,在气动弹性主动控制方面具有应用前景.
Active Flutter Suppression (AFS) is an active branch of the research on aeroelasticity, which is of great significance to the design of aero-vehicle.For a dual wing with a trailing edge control surface, sliding mode control (SMC) Based on the quasi-constant aerodynamic theory, aeroelastic model of a binary wing is established, and the sliding-mode switching surface and the state feedback control switching function of SMC are designed to realize the controllable AFS, From the perspective of the trajectory of phase space, the source of SMC's stability in closed-loop system is described. In addition, the robustness and delay effect of SMC are analyzed and discussed.The results show that this control strategy can be used in AFS, Active control has application prospects.