基于干扰抑制控制的飞行器姿态跟踪  

Attitude tracking of aircraft based on disturbance rejection control

作　　者：王璐 苏剑波[1,2] 

机构地区：[1]上海交通大学自动化系 [2]系统控制与信息处理教育部重点实验室,上海200240

出　　处：《控制理论与应用》2013年第12期1609-1616,共8页Control Theory & Applications

基　　金：国家自然科学基金资助项目(60935001,61221003)

摘　　要：本文针对飞行器姿态跟踪控制问题,考虑系统的内部模型不确定性和外界扰动,设计了使跟踪误差一致最终有界的控制器.以四元数为姿态参数,建立系统的非线性误差模型;将控制系统分为内环观测器和外环控制器分别设计,其中,线性扩张状态观测器作为系统内环将实际系统补偿为标称模型,而外环非线性控制器则用于镇定非线性标称系统.最后,利用Lyapunov理论得到了一致最终有界的稳定性结论,并基于频域理论,分析了线性扩张状态观测器阶次对系统性能的影响.姿态跟踪实验表明,本文设计的控制系统能够有效实现飞行器的姿态跟踪控制.This paper studies the attitude tracking control problem of an aircraft.With the consideration of internal uncertainties of system and external disturbances,the controller proposed stabilizes the system to be uniformly ultimately bounded （UUB）.Firstly,the error model of attitude tracking objective is established based on quatemion.Then,the control system is divided into inner loop of observer and outer loop of controller,respectively.The system model is compensated into the nominal one by a linear extended state observer （ESO）.A controller is hence designed for the compensated system to achieve desired performance,whose UUB stability is proven by Lyapunov theorem.Meanwhile,the performance of linear ESO is analyzed in frequency domain.Experimental results show that the proposed control scheme can accomplish the task of attitude tracking successfully and effectively.

关 键 词：飞行器 姿态跟踪控制 线性扩张状态观测器 非线性反馈控制 一致最终有界 

分 类 号：V249.122.2[航空宇航科学与技术—飞行器设计] TP273[自动化与计算机技术—检测技术与自动化装置]