基于H_∞控制理论的防空导弹自动驾驶仪设计  

Design of Antiaircraft Missile Autopilot Based on H_∞ Control Theory

作　　者：徐欣中[1] 雷虎民[1] 

机构地区：[1]空军工程大学导弹学院,陕西三原713800

出　　处：《现代防御技术》2010年第5期28-31,共4页Modern Defence Technology

摘　　要：针对防空导弹的飞行控制问题,提出了一种基于H_∞控制理论的导弹自动驾驶仪设计方法。该方法在设计过程中保留了通道间的全部耦合因素,从而提高了系统的稳定性,增强了系统的适应性和鲁棒性。给出了应用该方法的具体实现步骤,结合导弹飞行的全弹道典型特征参数,通过仿真实验说明了设计方法的有效性。Aimed at the antiaircraft missile flight control problem, a design method of missile autopilot base on H∞ control theory is put forward. All the coupling between three channels is reserved in the process of design. Hence, the stability of the system is improved and the adaptability and the robustness are enhanced. The implement process of this method is presented. Based on the representative parameters of the entire missile flight trajectory, the control effect is analyzed by simulation, and the simulation result has demonstrated the method is valid.

关 键 词：H∞控制 防空导弹 自动驾驶仪 鲁棒性 

分 类 号：TJ761.13[兵器科学与技术—武器系统与运用工程] TJ765