摘要
针对飞行器在大姿态角飞行时系统存在的非线性、耦合和不确定性因素,提出了自适应模糊滑模的控制方法来设计飞行器的姿态控制系统。采用模糊逼近的方法对姿态控制系统的不确定性进行补偿,并在此基础上设计了自适应模糊滑模解耦控制器。推导了系统的控制律和参数自适应律,并基于李亚普诺夫函数证明了该控制方法可保证闭环系统的全局稳定,最后通过数值仿真验证了本文提出方法的有效性。
There exists nonlinearity, coupling and uncertainty when the aircraft .fly with large attitude an- gle. For this situation, the method of adaptive fuzzy sliding mode control is proposed to design attitude con- trol system of the aircraft. The method of fuzzy approach is adopted to compensate the uncertainty of the sys- tem, and then the adaptive fuzzy sliding mode decoupling controller is designed. The control law and pa- rameter adaptive law are educed in the paper. It is proven that the whole control scheme can guarantee the stability of the closed-loop system. The simulation results show the effectiveness of the proposed methods.
出处
《航天控制》
CSCD
北大核心
2013年第5期13-18,共6页
Aerospace Control
关键词
飞行器
姿态控制
自适应模糊滑模
解耦控制
Aircraft
Attitude control
Adaptive fuzzy sliding mode
Decoupling control
