导弹自动驾驶仪控制算法鲁棒性研究  

Research on Robustness of Missile Autopilot Control Alogorithm

作　　者：屈秀敏 刘珊中[1] 刘永斌[1] QU Xiu-min;LIU Shan-zhong;LIU Yong-bin(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》2017年第8期52-55,60,共5页Fire Control & Command Control

基　　金：国家自然科学基金(61203047);河南省教育厅自然科学基金资助项目(12A120004)

摘　　要：以某型轴对称导弹为研究对象,在解耦和线性化的情况下,得到简化的数学模型。通过求解线性矩阵不等式(LMI)设计了状态反馈H∞控制导弹自动驾驶仪,采用模糊和变论域理论设计了变论域模糊PID控制自动驾驶仪。考虑飞行过程中的干扰、气动参数摄动,对两种自动驾驶仪的控制性能进行对比研究,仿真结果表明,二者皆能实现对导弹制导指令的有效跟踪,其中状态反馈H∞控制设计的自动驾驶仪在指令跟踪的快速性、准确性和抗干扰性上具有明显的优越性。Taking a certain type of axis symmetrical missile as the research object,a simplifiedmathematical model is obtained in the case of decoupling and linearization.The state feedback H肄control missile autopilot is designed by solving linear matrix inequality(LMI),and the variableuniverse fuzzy PID control autopilot is designed by using fuzzy and variable universe theory.Considering the disturbance and the perturbation of aerodynamic parameters during flight,acomparative study is carried out on the control performance of the both autopilots.The simulationresults show that both of them can achieve tracking of the missile guidance command effectively,especially the state feedback H∞control missile autopilot has obvious advantages in rapidity andaccuracy of the command tracking and anti-interference.

关 键 词：线性矩阵不等式 变论域 模糊控制 自动驾驶仪 鲁棒性 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]