采用分布式压电驱动器的翼面热颤振主动抑制

Active Flutter Suppression for Wings Using Distributed Piezoelectric Actuators under Thermal Circumstances

高超声速气动加热会严重影响飞行器结构的颤振特性,本文开展了采用分布式压电驱动器的热颤振主动抑制方法研究。以某飞行器小展弦比翼面为研究对象,进行了常温和热载荷边界条件下的结构振动和颤振分析。在此基础上,对频域非定常气动力进行有理函数拟合,建立包含压电驱动器的翼面耦合结构系统状态空间形式的运动方程;对典型热载荷边界条件下的被控对象设计颤振主动抑制控制律,分别设计出LQG及PID控制器;对比分析了系统开、闭环颤振特性。结果表明,通过主动控制律的实施,达到了热颤振主动抑制的目的,验证了这种颤振主动抑制方法的有效性。

Flutter characteristics of hypersonic flight vehicles can be severely affected by aerodynamic heating,and an investigation of active flutter suppression for wings using distributed piezoelectric actuators is performed in this paper under thermal circumstances.A finite element model of a low aspect-ratio wing is built and its flutter characteristics as well as natural dynamics characteristics are analyzed under both normal temperature circumstance and thermal circumstance.Rational function approximation of unsteady aerodynamics is executed in order to establish state-space equations of the model of wing coupled with piezoelectric actuators.LQG and PID control laws are designed for active flutter suppression under typical thermal circumstance.Analytical results of close-loop system indicate that flutter characteristics of the wing is improved prominently.The solution scheme of the active flutter suppression is proved valid.