高超声速飞行器的动态滑模飞行控制器设计  

Dynamic Sliding Mode Control of a Hypersonic Flight Vehicle

作　　者：耿洁[1] 刘向东[1] 王亮[1] 

机构地区：[1]北京理工大学自动化学院,北京100081

出　　处：《兵工学报》2012年第3期307-312,共6页Acta Armamentarii

基　　金：国家自然科学基金项目(10872030)

摘　　要：基于高超声速航空飞行器的纵向动力学,提出了一种基于动态滑模原理的飞行控制器。在将模型进行输入/输出线性化的基础上,构造辅助的滑模变量,求取了滑模控制量,实现了动态滑模控制的两阶段收敛。证明了传统滑模面以及辅助滑模面有限时间内的收敛特性,并给出了控制器参数所满足的条件。该方法对不连续的控制量输出加以积分作用,有效地降低了普通滑模控制器的抖振现象。在33 528 m高度和马赫数15的平稳巡航条件下的仿真研究表明:与普通滑模控制器相比,动态滑模有效降低了抖振,并且对参数不确定模型具有更好的鲁棒性。A kind of sliding mode flight controller based on dynamic sliding mode principle is proposed for the longitudinal dynamics of a hypersonic flight vehicle.For its input/output linearized model,an auxiliary sliding mode variable is constructed.The dynamic sliding mode control law is introduced and the dual-phase convergent process is implemented.The auxiliary sliding mode and conventional sliding mode are both proved to be convergent in finite time and the condition of controller parameters to be satisfied is given.Using this method,the discontinuous controll output is integrated,and the chattering is effectively reduced.Simulation studies are conducted for a stable cruise condition at the height of 33 528 m and the speed of Mach 15.The simulation results demonstrate that the proposed dynamic sliding mode controller reduces the sliding chattering,and has better robustness when there are parameter uncertainties.

关 键 词：飞行器控制、导航技术 高超声速飞行器 动态滑模 飞行控制 鲁棒性 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]