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针对机翼系统的颤振问题,采用一种积分和反演相结合的准滑模控制方法对机翼的浮沉和俯仰自由度进行控制。首先对带前后副翼的机翼气动弹性系统进行建模,基于建立的模型设计了积分和反演相结合的准滑模控制器,并利用Lyapunov稳定性理论对机翼控制系统的稳定性进行分析。最后,基于Matlab对该机翼气动弹性反演准滑模控制系统进行仿真,并与传统滑模控制的系统进行了分析和比较。仿真结果表明,所设计的反演准滑模控制器能在保证系统稳定运行的同时实现期望状态的快速稳定跟踪,同时能削弱滑模控制的抖振,取得了良好的控制效果。
Aiming at the flutter problem of the wing system, a method of quasi-sliding mode control combined with integral and inversion is adopted to control the wing sway and pitch degrees of freedom. Firstly, the aeroelastic system with anterior and posterior ailerons is modeled. Based on the established model, a quasi-sliding mode controller integrating the integral with the inversion is designed. The stability of the wing control system is studied by Lyapunov stability theory analysis. Finally, the simulation of aero-elastic inversion quasi-sliding-mode control system based on Matlab is carried out and compared with the traditional sliding mode control system. The simulation results show that the designed quasi-sliding mode controller can achieve the stable and stable tracking of the desired state while maintaining the stable operation of the system, and can weaken the chattering of the sliding mode control and achieve good control effects.