导弹的直接参数化姿态控制器设计  

Design of Direct Parametric Attitude Controller for Missile

作　　者：薛梦琪 刘珊中 邱耀龙 秦陆明 XUE Mengqi;LIU Shanzhong;QIU Yaolong;QIN Luming(School of Information Engineering,Henan University of Science and Technology,Luoyang 471023,China)

机构地区：[1]河南科技大学信息工程学院,河南洛阳471023

出　　处：《火力与指挥控制》2022年第9期43-47,共5页Fire Control & Command Control

基　　金：国家自然科学基金资助项目(61976081)。

摘　　要：针对拦截导弹末制导段弹体飞行姿态控制问题,建立了耦合状态下拦截导弹三通道姿态数学模型,以此模型为对象,采用直接参数化方法设计姿态稳定控制器,仿真结果显示该控制器能使系统迅速镇定且具有良好的鲁棒性;在前述姿态稳定控制的基础上,设计了滑模跟踪控制器,并与PD跟踪控制对比,仿真结果表明,直接参数化稳定控制结合滑模跟踪控制导弹姿态控制系统,能使导弹姿态更迅速地跟踪期望指令信号,且具有良好的动态性能和抗干扰性能。Aiming at the flight attitude control problem of interceptor missile in terminal guidance phase,a three-channel attitude mathematical model of interceptor missile under coupling state is established.On this basis,the attitude stabilization controller is designed by direct parameterization method.The simulation shows that the controller can stabilize the system quickly and has good robustness.Based on the above attitude stabilization control,a sliding mode tracking controller is designed,and compared with PD tracking controller.The simulation shows that the missile attitude control system based on the combination of direct parametric stability control and sliding mode variable structure tracking control can make the missile attitude track the desired command signal more quickly,and has good dynamic performance and an-ti-jamming performance.

关 键 词：拦截导弹 姿态控制 直接参数化设计 滑模控制 鲁棒性 

分 类 号：TJ761[兵器科学与技术—武器系统与运用工程] V249.122[航空宇航科学与技术—飞行器设计] TP273[自动化与计算机技术—检测技术与自动化装置]