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.
出处
《导弹与航天运载技术》
北大核心
2009年第1期15-19,共5页
Missiles and Space Vehicles
关键词
自适应控制
滑模变结构
模糊逻辑系统
Adaptive control
Variable structure control （VSC）
Fuzzy logic system
