变后掠翼航弹最优弹道自适应滑模跟踪控制  

Adaptive sliding mode tracking control of optimal trajectory for cruise missiles with variable-swept wings

作　　者：李伟明[1,2] 孙瑞胜[1] 白宏阳[1] 刘鹏云[1] 

机构地区：[1]南京理工大学能源与动力工程学院,江苏南京210094 [2]山东航天电子技术研究所,山东烟台264003

出　　处：《系统工程与电子技术》2015年第2期372-378,共7页Systems Engineering and Electronics

基　　金：国家自然科学基金;中国物理研究院联合基金(11176012);国家航空科学基金(20110159001)资助课题

摘　　要：根据变后掠翼航弹在预定弹翼构型下对最优方案弹道跟踪的精确性和鲁棒性要求,设计了一种轨迹-姿态双回路自适应滑模控制器。外环轨迹跟踪回路以位置偏差为参考输入,得到方案攻角参考指令,同时基于Lyapunov稳定性理论给出外环滑模收敛的充分条件;内环姿态跟踪回路则设计了参数自适应律,抑制由后掠角引起的时变参数摄动,同时生成舵偏控制指令,以实现对姿态的跟踪控制。仿真对比结果表明,该自适应滑模控制器在有效消除参数不确定性影响的同时保证了变后掠翼航弹在弹翼预定作动时对最优方案弹道跟踪的稳定性,并且消除了常规滑模控制的抖振现象。In accordance with the requirements for robustness of the control system and accuracy of tracking optimal project trajectory in the scheduled wings＇ configuration schemes, an adaptive sliding-mode controller is proposed. The final controller is an inner/outer-loop structure, with trajectory tracking control being the outer loop and attitude tracking control being the inner loop. The outer loop uses position deviations as reference in- puts to obtain the reference angle-of-attack command. The sufficient condition of converging to a sliding mode area is obtained based on the Lyapunov stability theory. The inner loop is designed with the parametric adapta- tion law to restrain the time-varying parameter perturbations caused by the sweepback, and produce the rudder deflection commands in order to realize the attitude tracking control. Simulation results indicate that the pro- posed controller can eliminate the effect from time-varying parameter uncertainties and maintain the stability of tracking optimal project trajectory simultaneouslv, with no control chattering.

关 键 词：自适应滑模控制 双回路控制结构 变后掠翼 最优弹道 

分 类 号：TJ761.6[兵器科学与技术—武器系统与运用工程]