一种高超声速飞行器固定时间滑模控制方法  

A Fixed-time Sliding-mode Control Method for Hypersonic Vehicle

作　　者：许玉龙 鄂斌 王小刚[1] 崔乃刚[1] XU Yulong;E Bin;WANG Xiaogang;CUI Naigang(School of Astronautics,Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]哈尔滨工业大学航天学院,哈尔滨150001

出　　处：《宇航学报》2024年第4期560-570,共11页Journal of Astronautics

摘　　要：针对高超声速飞行器再入滑翔段的姿态控制问题,提出了一种存在外部扰动、模型不确定和输入饱和约束情况下的固定时间收敛终端滑模控制器。首先,针对固定时间收敛的超螺旋二阶滑模扰动观测器,给出了一个更加精确的固定收敛时间上界。随后,构造了一种改进的变指数系数快速非奇异多变量终端滑模面。进而,基于固定时间观测器和改进的滑模面,提出了一种可以使高超声速飞行器模型在受到外部扰动、模型存在不确定参数和输入饱和约束的情况下,能够实现固定时间收敛的再入滑翔段姿态控制终端滑模控制器,并证明了其在观测器收敛前后的固定时间稳定性。该方法能够在不引入额外测量的前提下,有效避免输入饱和。最后,通过数值仿真验证了所提出的控制方法的有效性。A fixed-time terminal sliding mode controller for the attitude control problem of hypersonic vehicle in the reentry gliding phase is proposed,in the presence of external disturbances,model uncertainty,and input saturation constraints.Firstly,a more accurate fixed convergence time upper bound is proposed for the fixed-time super-twisting second-order sliding-mode disturbance observer.Then,an improved variable exponential coefficient fast non-singular multivariable terminal sliding-mode surface is constructed.Furthermore,based on the fixed-time observer and the improved sliding-mode surface,a non-singular terminal sliding-mode controller is proposed to enable the hypersonic vehicle model to achieve attitude control in fixed-time under external disturbances,uncertain model parameters,and input saturation constraints.Its fixed-time stability before and after observer convergence is demonstrated.The proposed method can effectively avoid input saturation without introducing additional measurements.Finally,the effectiveness of the proposed control method is verified by numerical simulation.

关 键 词：高超声速飞行器 滑翔再入 姿态控制 固定时间控制 滑模控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]