推力调节飞行距离最优自适应滑模控制

Optimal Adaptive Sliding Mode Control of Flight Distance on Thrust Regulation

为了准确控制巡航导弹在指定时间到达指定位置,提出了一种基于飞行距离和地速反馈的推力调节最优自适应滑模控制方法。基于包含发动机推力动态特性的巡航状态附近小扰动方程,采用反馈线性化方法设计指数趋近滑模变结构控制律和状态反馈系数自适应律,构造李雅普诺夫函数,证明了自适应滑模控制系统的稳定性;根据控制律和滑模函数推导出飞行距离跟踪误差传递方程,并用线性二次型调节器最优控制方法设计跟踪误差动态特性。对某型巡航导弹进行仿真,结果表明,在外界阵风干扰和空气动力系数摄动情况下,该控制方法能精确地跟踪以时间为自变量的参考地速和飞行距离信号,具有较好的抑制系统参数摄动和抗干扰能力。

In order to make cruise missile arrive at specified location in the given time accurately, an optimal adaptive sliding-mode-control method of thrust adjustment was proposed based on ground speed and flight-distance feedback. The perturbation equation of cruise-state was written considering the dynamic characteristics of engine thrust. Index reaching sliding-mode-control law and adaptive law were designed by using feedback linearization, and the Lyapunov function was constructed to prove the stability of system. The error transfer equation was deduced according to the control law and the sliding mode function,and the dynamic characteristics of error were designed by solving the optimal linear quadratic regulator problem. Simulation results of cruise missile show that,under the conditions of wind disturbance and aerodynamic-coefficient perturbation, the reference signals of speed and distance can be tracked accurately by using this control-method, and the method can suppress system parameter perturbation and has good anti-interference ability.