飞行器攻角非线性自适应反演控制方法研究  

Study on Nonlinear Adaptive Backstepping Control Method for Aircraft Angle of Attack

作　　者：郭法涛[1] 王晓予 关成启[1] 

机构地区：[1]中国航天科工集团公司第三研究院,北京100074 [2]第二炮兵装备部,北京100085

出　　处：《战术导弹技术》2007年第5期75-77,共3页Tactical Missile Technology

摘　　要：讨论了飞行器纵向攻角控制方法.攻角的状态方程中存在时变参数和外部扰动不确定性.基于自适应反演控制技术的迭代设计方法可以保证闭环系统一致最终有界.仿真结果证明了此方法的良好效果.A discussion is devoted to longitudinal angle of attack control method for aircraft. The aircraft angle of attack states equations may possess a class of uncertainties with time varying parameters and external disturbances. Recursive design based on adaptive backstepping technique can guarantees closed loop system uniform ultimate boundedness （UUB）. It is shown from numerical simulations of aircraft model provides good performance.

关 键 词：飞行器 攻角 非线性 自适应 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程]