基于特征区间的滑翔弹姿态控制系统设计  

Design of Gliding Missile Attitude Control System Based on Interval Feature Theory

作　　者：孙旭[1] 庞红[1] 时满红[1] 彭理群[1] 

机构地区：[1]空军预警学院,武汉430019

出　　处：《现代雷达》2013年第1期80-83,共4页Modern Radar

摘　　要：根据无动力滑翔弹在不同飞行时段的运动特点,文中将其弹道分为若干时段,基于区间PID控制理论,结合风干扰模型,设计了无动力滑翔弹的俯仰通道姿态控制系统。给定航弹的初始投抛条件,对纵向通道的时变过程进行仿真,结果表明该滑翔弹控制系统具有一定的稳定性和精度。文中的方法对设计具有滑翔段的飞行器姿态控制系统有一定的参考价值和工程实用价值。According to flight charalteristics at time-verying ballistic trajectory of unpower gliding missile is divided into several parts. Based on the control theory of interval PID and wind disturbance model, attitude control system at pitch channel for unpower gliding missile is designed. The pitch channel parameters are calculated and simulated under certain initial dropping conditions. The results show that the missile control system is stable and precise. The method possesses reference values and practical engi- neering values in design of attitude control system for unpowered vehicle.

关 键 词：无动力滑翔弹 特征区间 姿态控制 风场 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]