针对临近空间高超声速巡航飞行器动力系数变化大、攻角要求精确控制的特点,设计了一种自适应滑模变结构攻角控制律。该控制律采用内外环结构,内环通过俯仰角速率反馈提高系统的阻尼、改善动态过程品质,外环控制飞行攻角,用自适应算法调节滑模控制器的控制参数来逼近时变系统参数的上界同时消除外界干扰。仿真研究表明,所设计的攻角控制律响应快、稳态误差小,具有良好的跟踪性能和鲁棒性能。

Due to various dynamics, an angle of attack control law for hypersonic cruise vehicle in near space was designed based on adaptive sliding mode control. The control law adopted an inner-outer loop control configuration, inner loop through introducing pitch rate feedback to improve the system damp and the dynamic performance, outer loop control angle of attack based on adaptive sliding mode control, the parameters of the sliding mode controller were adjusted by the adaptive law to approximate the upper bound of model perturbation and external disturbances. The simulation results show that the control method has properties of quick response and nice steady accuracy; it also has high tracking performance and robustness.