基于μ综合的导弹自动驾驶仪设计  

Design of Missile Autopilot Based on μ-Synthesis

作　　者：王鹏举[1] 贾晓洪[1] 周桃品[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《四川兵工学报》2011年第3期32-34,37,共4页Journal of Sichuan Ordnance

摘　　要：为了满足高机动性要求,空空导弹常采用大攻角飞行;然而导弹大攻角飞行时存在通道间耦合严重、气动力系数摄动范围大等问题,使设计模型与实际对象误差严重,传统方法设计的自动驾驶仪很难满足鲁棒性要求。考虑导弹自动驾驶仪设计中存在的未建模误差和气动力系数摄动等不确定性因素,采用μ综合设计方法,以某型导弹为例对其俯仰通道驾驶仪进行了设计,仿真结果表明,与传统设计方法相比,所设计的控制系统不仅动态性能满足设计要求,且具有良好的鲁棒性能。Aimed at the uncertainty such as modeling error and disturbances existing in the designing of the Missile autopilot,the paper proposed a design framework constructed by μ-synthesis.In the paper,it took a certain type of missile as an example,according to the system performance requirements,and the autopilot was designed with applicable weighting functions,and made comparison with the conventional design method.The simulation results show that the μ-synthesis＇s controller is insensitive to the parameters perturbation,and has well dynamic and robust performance.

关 键 词：自动驾驶仪 鲁棒性 Μ综合 不确定性 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]