中国科学院沈阳自动化研究所机构知识库
Advanced  
SIA OpenIR  > 机器人学研究室  > 会议论文
题名: 有扰情况下航天器姿态的固定时间控制方法
其他题名: Fixed-time attitude control for rigid spacecraft with external disturbances
作者: 姜博严; 陈卓; 胡庆雷; 齐俊桐
作者部门: 机器人学研究室
会议名称: 11th World Congress on Intelligent Control and Automation (WCICA 2014)
会议日期: June 29 - July 4, 2014
会议地点: Shenyang, China
会议录: Proceeding of the 11th World Congress on Intelligent Control and Automation, WCICA 2014
会议录出版者: IEEE
会议录出版地: Piscataway, NJ, USA
出版日期: 2014
页码: 4384-4389
收录类别: EI
ISBN号: 978-1-4799-5825-2
关键词: 航天器 ; 固定时间控制 ; 姿态控制 ; 有限时间控制
摘要: 针对受干扰的航天器姿态稳定控制问题,给出一种基于固定时间概念的有限时间控制方法使姿态快速收敛到平衡点。已有的基于终端滑模的有限时间控制方法,其估计的收敛时间都依赖于系统状态的初值,而本文基于固定时间设计的滑模面和趋近律,不仅使系统具有更快的收敛速度,且在不知道状态初值的情况下亦可估算出系统状态到达滑模面的时间和在滑模面上滑动的时间。而当状态初值已知时,本文亦给出了更为精确收敛时间的估算方法。最后,将设计的固定时间控制器应用于航天器姿态稳定控制,仿真结果表明该控制器能有效抑制外部干扰,且对状态初值具有很强的鲁棒性。
英文摘要: In this paper, a finite-time control method based on fixed-time is developed for attitude stabilization of a rigid spacecraft with external disturbances. In comparison with the existing finite-time techniques based on terminal sliding mode, of which the initial value of system states must be known when estimating the settling time, the proposed fixed-time based sliding mode controller can not only stabilize the attitude faster, but also eliminate the need of the knowledge of the initial condition to estimate the time of the reaching and the sliding phase. Moreover, if the initial condition is known, the expression of a more accurate settling time is also given in this paper. Finally, the attitude stabilizing performance of the controller is evaluated through a numerical example and the results show that the closed-loop system is robust to external disturbances and initial conditions
语种: 中文
产权排序: 3
内容类型: 会议论文
URI标识: http://ir.sia.cn/handle/173321/16927
Appears in Collections:机器人学研究室_会议论文

Files in This Item: Download All
File Name/ File Size Content Type Version Access License
有扰情况下航天器姿态的固定时间控制方法 .pdf(744KB)会议论文--开放获取View Download
Service
Recommend this item
Sava as my favorate item
Show this item's statistics
Export Endnote File
Google Scholar
Similar articles in Google Scholar
[姜博严]'s Articles
[陈卓]'s Articles
[胡庆雷]'s Articles
CSDL cross search
Similar articles in CSDL Cross Search
[姜博严]‘s Articles
[陈卓]‘s Articles
[胡庆雷]‘s Articles
Related Copyright Policies
Null
Social Bookmarking
Add to CiteULike Add to Connotea Add to Del.icio.us Add to Digg Add to Reddit
文件名: 有扰情况下航天器姿态的固定时间控制方法 .pdf
格式: Adobe PDF
所有评论 (0)
暂无评论
 
评注功能仅针对注册用户开放,请您登录
您对该条目有什么异议,请填写以下表单,管理员会尽快联系您。
内 容:
Email:  *
单位:
验证码:   刷新
您在IR的使用过程中有什么好的想法或者建议可以反馈给我们。
标 题:
 *
内 容:
Email:  *
验证码:   刷新

Items in IR are protected by copyright, with all rights reserved, unless otherwise indicated.

 

 

Valid XHTML 1.0!
Copyright © 2007-2016  中国科学院沈阳自动化研究所 - Feedback
Powered by CSpace