考虑输入饱和的高超声速飞行器姿态控制

Attitude Control of Hypersonic Vehicle Considering Input Saturation

针对高超声速飞行器姿态控制,利用滑模干扰观测器观测系统复合扰动并予以补偿,采用动态面控制方法处理非线性控制系统设计问题,同时考虑输入饱和问题,区别于直接对舵偏进行限幅,将控制输入扩张成一个新的变量进行控制器设计,在设计过程中采用双曲正切函数近似饱和函数。仿真结果显示,基于滑模观测器的动态面控制方法相比于单纯动态逆控制方法具有较强的鲁棒性,但两者的控制输入都是对舵偏强制限幅,这并不有利于系统的稳定性,而考虑输入饱和问题的飞行器的姿态控制不仅保证对姿态的精确跟踪,同时可保证控制输入更平滑且尖峰值相对更小。

Aiming at the design of attitude control of hypersonic vehicles, the sliding mode disturbance observer is used to compensate the composite disturbance, meanwhile the dynamic surface control method is used to deal with the design of the nonlinear control system. Considering the input saturation problem, the control input is expanded into a new variable to design the controller, which is different from the direct limit of the rudder deviation. The simulation results show that the dynamic surface control method based on sliding mode observer has stronger robustness than the simple dynamic inversion control method, but the control inputs of both methods are forced to limit the rudder bias, which is bad for the stability of the system. The attitude control of aircraft considering input saturation not only ensures the accurate tracking of attitude, but also ensures the smoother control input and relatively smaller peak value.