直接力导弹的模型参考自适应滑模控制器设计  

Side Jet Missile Control Design Based on Adaptive Sliding Mode Control with Reference Model

作　　者：董朝阳[1] 吴振辉[2] 陈宇[1] 王枫[1] 

机构地区：[1]北京航空航天大学自动化科学与电气工程学院,北京100083 [2]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《系统仿真学报》2008年第13期3500-3503,共4页Journal of System Simulation

基　　金：航天创新基金与航天支撑基金资助项目

摘　　要：针对导弹直接力/气动力复合控制的特点,提出了一种基于参考模型的自适应滑模控制方案。该设计方法针对系统所存在的不确定性,在滑模控制中引入了自适应参数调节律和模糊控制规则,采用自适应律逼近模型摄动和外界干扰的上界,采用模糊调节律有效减弱了一般变结构控制系统的抖颤问题,既进一步增强了系统的鲁棒性,又提高了自适应参数收敛过程中的跟踪精度。仿真结果表明,所提出的控制方案对机动指令具有较好的跟踪效果,适用于直接力/气动力复合控制导弹的控制系统设计。An adaptive sliding mode control scheme based on reference model was proposed to design the autopilot of reaction-jet and aerodynamic compound control missile. Due to the uncertainties of system, an adaptive parameter adjuster and fuzzy control rules were introduced into sliding mode control. The adaptive law was used to approximate the upper bound of model perturbation and external disturbances. The fuzzy adjusting law was used to attenuate the chattering phenomenon which was common in general sliding mode control systems. And the fuzzy inference system could not only improve the robustness of system further, but also improve the tracking precision in the progress of adaptive parameter convergence. Simulation results show that the proposed scheme can track the maneuver command with higher precision and faster response speed than traditional ones, and it is applicable to design the autopilot of reaction-jet and aerodynamic compound control missile.

关 键 词：直接力/气动力复合控制 滑模变结构控制 自适应控制 模糊逻辑 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]