自适应全程滑模变结构在轨迹跟踪上的应用  

Application of Adaptive Global Sliding Mode Control Method in Trajectory Tracking

作　　者：王子瑜 李君 王海涛 宋敬群 Wang Zi-yu;Li Jun;Wang Hai-tao;Song Jing-qun(Beijing Institute of Astronautical System Engineering, Beijing, 100076)

机构地区：[1]北京宇航系统工程研究所,北京100076

出　　处：《导弹与航天运载技术》2017年第4期59-62,94,共5页Missiles and Space Vehicles

摘　　要：针对高超声速飞行器(hypersonic reentry vehicle,HRV)轨迹跟踪问题,提出一种自适应全程滑模变结构轨迹跟踪方法。首先,基于最优化理论设计全程滑模面,使系统的轨线一开始便落在切换面上;其次,采用滑模变结构控制与自适应控制相结合的方法,根据辨识结果自动调整控制律,在保证稳定性的同时削弱抖振;最后,采用Lyapunov定理证明系统的稳定性,并在一定的干扰作用下,将所设计的跟踪算法进行数值仿真,通过与二次型调节器(linear quadratic regulator,LQR)跟踪算法进行比较,验证了控制器的有效性。A trajectory tracking guidance control law is proposed based on the theory of adaptive global sliding mode control,which can help solve the problem of trajectory tracking for HRV.Firstly,a global sliding mode surface is designed based on optimization theory,which guarantees the sliding mode motion of the system lie on the sliding surface at the beginning.Secondly,an adaptive reaching law is incorporated to estimate the system uncertainties,so that the chattering phenomenon is effectively relaxed.Finally,the robustness of the system is proofed by Lyapunov theory.Numerical simulations demonstrated the capability and effectiveness of the proposed method under the condition of aerodynamic data perturbations.

关 键 词：高超声速飞行器 全程滑模变结构控制 自适应控制 最优化理论 

分 类 号：V448.235[航空宇航科学与技术—飞行器设计]