带有干扰观测器的高超声速飞行器滑模控制

吴云洁; 王建敏; 刘晓东; 刘佑民

引用本文:	吴云洁,王建敏,刘晓东,刘佑民.带有干扰观测器的高超声速飞行器滑模控制[J].控制理论与应用,2015,32(6):717~724.[点击复制]
	WU Yun-jie,WANG Jian-min,LIU Xiao-dong,LIU You-min.Disturbance-observer-based sliding mode control for hypersonic flight vehicle[J].Control Theory and Technology,2015,32(6):717~724.[点击复制]

带有干扰观测器的高超声速飞行器滑模控制

Disturbance-observer-based sliding mode control for hypersonic flight vehicle

摘要点击 2907 全文点击 1583 投稿时间：2014-07-22 修订日期：2015-02-10

查看全文查看/发表评论下载PDF阅读器

DOI编号 10.7641/CTA.2015.40690

2015,32(6):717-724

中文关键词高超声速飞行器扩张状态观测器滑模控制干扰观测器连续滑模抖振

英文关键词 hypersonic vehicles extended state observer sliding mode control disturbance observer continuous sliding mode chattering

基金项目国家自然科学基金项目(91216304)资助.

作者	单位	邮编
吴云洁	北京航空航天大学自动化科学与电气工程学院北京航空航天大学虚拟现实技术与系统国家重点实验室	100191
王建敏^*	北京航空航天大学自动化科学与电气工程学院北京航空航天大学虚拟现实技术与系统国家重点实验室	100191
刘晓东	宇航智能控制技术国防科技重点实验室
刘佑民	北京航天发射技术研究所

中文摘要

针对高超声速飞行器非线性和易受干扰影响的特点, 提出了带有扩张状态干扰观测器的连续滑模控制方法. 在对飞行器非线性模型做线性化处理的基础上, 设计了一种连续时间滑模控制器. 该控制器在对不确定性和未知动态保持鲁棒性的基础上, 消除了传统滑模中存在的抖振现象. 对系统中存在的外加干扰, 设计了扩张状态干扰观测器. 将外加干扰作为系统的一个状态变量被估计出来, 再将估计值用作滑模控制器的补偿量, 进而达到消除外干扰的目的. 在高超声速飞行器巡航飞行状态的基础上进行了仿真. 仿真结果表明, 所提出的方案能够满足控制要求.

英文摘要

In accordance with characteristics of nonlinear and vulnerable to disturbance for hypersonic flight vehicle, a scheme of continuous sliding mode control based on extended state disturbance observer is proposed in this paper. A continuous sliding mode controller is designed on the basis of linear processing for nonlinear model of hypersonic flight vehicle. The controller is not only remaining the robust to uncertainties and unknown dynamics, but also eliminating the chattering phenomenon existing in traditional sliding mode control. An extended state disturbance observer is designed for external disturbance of the system. The external disturbance is estimated regarding as a system state variable, and the estimated value is used as a compensation amount in the sliding mode controller. Hence, the goal of counteracting the effect of disturbance is achieved. The simulation is conducted in the cruise flight condition of hypersonic flight vehicle. Simulation results show that the proposed approach meets the control requirements of hypersonic flight vehicle.