基于改进趋近律的模糊自适应滑模控制的导弹姿态控制系统  

Fuzzy Adaptive Variable Structure Control for Missile Attitude Control System Based on Improved Reaching Law

作　　者：米文鹏[1] 刘新学[1] 洪成华 杨建飞 

机构地区：[1]第二炮兵工程学院,西安710025 [2]第二炮兵青州士官学校,青州262500

出　　处：《导弹与航天运载技术》2009年第1期15-19,共5页Missiles and Space Vehicles

摘　　要：针对导弹姿态控制系统的参数具有时变性和不确定性的特点,设计了一种具有指数趋近律的变结构控制器。为克服常规指数趋近律的抖动现象,提出了一种改进的算法。同时,针对姿态控制系统的不确定项,利用模糊逻辑系统设计切换控制项来克服其对系统的影响。结果表明,该控制器在导弹姿态控制系统中的仿真效果较为满意。The parameters of the digital missile attitude structure controller （VSC） with exponential reaching law is given. And for the uncertain disturbance, the switch control show that this controller has a satisfying effect in the missile control system have the characters of variety and uncertainty, so a variable designed. In order to weaken the system jitter, an improved arithmetic is with fuzzy logic theory is designed to overcome its influence. Test results control system.

关 键 词：自适应控制 滑模变结构 模糊逻辑系统 

分 类 号：V448.223[航空宇航科学与技术—飞行器设计]