变结构滑模飞行控制

Variable Structure Sliding Mode Control for the Flight Control

飞机飞行的范围广泛、复杂 ,不可能得到精确的飞机数学模型 ,所以 ,常规的控制理论应用于飞行控制 ,效果不佳。模型跟踪变结构控制理论不依赖数学模型 ,而能对理想模型进行跟踪 ,使飞机具有良好的性能。本文研究了变结构滑模控制在飞行控制系统的应用 ,首先 ,对滑模进行极点配置 ,使滑模有良好的动态特性 ;设计了一个比例积分切换超平面 ,确保消除稳态误差 ;采用饱和控制技术 ,消除了抖振现象 ;对系统进行了数字仿真 ,表明系统不仅实现了无抖振模型跟踪 。

The flight envelope of aircraft is wide and complex, it is impossible to obtain an accurate aircraft mathematic mode, and the flight performance is not good by utilizing the conventional control theory. Since the aircraft is very complex, it is necessary that the flight control system possesses a strong robust stability. The sliding mode variable structure control just has the advantage of the strong robust stability, therefore, in this paper, the sliding mode control theory is used in designing the controller for the flight control system. First, the PI type mode is designed in order to reduce the error of stable state. Second, Pole assignment method is used to cope with the mode poles so that the mode has the good response. Third, the simple saturating control is adopted to eliminate the chattering phenomena. Finally, the controller for the flight control system is designed. The simulation results show that the whole control system has good a stability and performance.