弹性飞行器气动伺服弹性稳定性分析与控制

The stability analysis of aeroservoelasticity and longitudinal attitude control for flexible flight vehicles

轻质结构大长细比弹性飞行器开环闭环颤振及控制系统设计是气动伺服弹性稳定性校核与分析的核心问题。本文利用振动模态试验数据修正了弹性飞行器结构有限元模型;使用涡格法进行非定常气动力计算,并利用最小状态法获得了弹性飞行器刚弹耦合频时域状态空间方程。绘制系统状态矩阵特征值随动压变化绘制的根轨迹图对该弹性飞行器开环颤振进行了分析。最后使用线性二次型方法设计了弹性飞行器主动颤振抑制控制律和纵向姿态控制器。仿真结果表明,系统在短的上升时间内实现了对指令的跟随,超调量合理,无静态误差。本文所采用的方法能够满足工程设计需求。

In the design of flexible flight vehicle with lightweight structure and large slenderness ratio, open-loop and close-loop flutter analysis are important. The finite element model of the flexible flight vehicle is modeled by compared with the modal experimental data. The vortex lattice method is employed to compute the unsteady aerodynamic forces. The frequency-domain aeroelastic model is translated into time-domain model by using the mini-state method. The flutter speed and flutter modal are identified by the root locus of eigenvalue. Finally, an LQR active flutter suppression control law and longitudinal attitude controller are designed. Simulation results obtained indicate that the proposed method is suitable for engineering application in aeroservoelatic analysis and design.