Finite-time output feedback attitude stabilisation for rigid spacecraft with input constraints

被引：25
作者：
Sun, Shihao [1 ,2 ]
Zhao, Lin [3 ]
Jia, Yingmin [1 ,2 ]
机构：
[1] Beihang Univ BUAA, Res Div 7, Beijing 100191, Peoples R China
[2] Beihang Univ BUAA, Ctr Informat & Control, Beijing 100191, Peoples R China
[3] Qingdao Univ, Sch Automat & Elect Engn, Qingdao 266071, Peoples R China
来源：
IET CONTROL THEORY AND APPLICATIONS | 2016年 / 10卷 / 14期
关键词：
feedback; attitude control; space vehicles; state feedback; closed loop systems; stability; finite-time output feedback attitude stabilisation problem; rigid spacecraft systems; input constraints; continuous saturated state feedback controller; homogeneous method; closed-loop system; saturated output feedback controller; state observer; semi-global finite-time stability; LINEAR-SYSTEMS SUBJECT; TRACKING CONTROL; SYNCHRONIZATION; SATURATION; CONSENSUS; VELOCITY;
D O I：
10.1049/iet-cta.2015.1174
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
This study deals with finite-time output feedback attitude stabilisation problem for rigid spacecraft systems subject to input constraints. First, a continuous saturated state feedback controller is proposed based on the homogeneous method, after which can guarantee the closed-loop system is global finite-time stable. Then, a switched saturated output feedback controller is developed under a state observer, after which can guarantee the closed-loop system is semi-global finite-time stable. Simulation results are given to demonstrate the effectiveness of the proposed method.
引用
收藏
页码：1740 / 1750
页数：11
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IEEE TRANSACTIONS ON SYSTEMS MAN AND CYBERNETICS PART B-CYBERNETICS, 2011, 41 (04) :950-963
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