基于滑模趋近律的防空导弹垂直发射姿态控制研究  

Attitude Control Law Design of Vertical Launched Air-defense Missile Based on Sliding Mode Control

作　　者：苗昊春[1] 马清华[2] 陈韵[2] 严宪军 江婷婷 

机构地区：[1]西北工业大学航天学院,西安710072 [2]中国兵器工业第二〇三研究所,西安710065

出　　处：《计算机测量与控制》2015年第4期1230-1232,共3页Computer Measurement &Control

摘　　要：为了实现一种针对光纤制导的低空战术防空导弹垂直发射过程的姿态控制,首先利用四元数在弹体坐标系下对垂直发射的防空导弹建立了运动方程,并在纵向通道利用小扰动线性化理论将运动方程简化为状态空间模型,然后设计了基于滑模趋近律的姿态控制律,最后建立了Simulink六自由度弹道仿真模型并进行了数字仿真验证,结果表明:基于四元数的运动方程形式运行有效,基于滑模趋近律的姿态控制律可实现对防空导弹垂直发射的有效控制。In order to find out a method of attitude control of vertical launched to a kind of air defense missile, quaternion is used for air defense missile of vertical launched to establish motion equations in missile＇s body coordinate system, then the small perturbation lineariza tion state space model is adopted in pitch channel to design attitude control law based on sliding mode approaching law. Finally the 6 DOF trajectory simulation model in Simulink is established and simulated. The result indicated that the motion equations using quaternion is efficient, and attitude control law based on sliding mode approaching law is practicable in vertical launching control of air defense missile.

关 键 词：防空导弹 垂直出水 四元数 滑模 姿态控制 

分 类 号：V249[航空宇航科学与技术—飞行器设计]