Finite-time Attitude Control of Spacecraft

被引：0
|
作者：
Gao, Dai [1 ]
Meng, Siming [2 ]
Yao, Wei [2 ]
Lv, Jianting [2 ]
机构：
[1] Harbin Inst Technol, Sch Astronaut, Harbin 150080, Peoples R China
[2] Heilongjiang Univ, Sch Math Sci, Harbin 150080, Peoples R China
来源：
PROCEEDINGS OF THE 2012 24TH CHINESE CONTROL AND DECISION CONFERENCE (CCDC) | 2012年
关键词：
Finite Time Converge; Attitude Control; State Feedback; Output Feedback; TRACKING;
D O I：
暂无
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
In this paper, we propose two finite-time control laws for rigid spacecraft. We use quaternion for attitude representation and employ the Lagrange-like model for convenience of system design. First, by using the finite-time control method, a full-state feedback control scheme is presented. Then, considering no angular velocity measurement can be obtained, we propose a finite-time control law. Under the proposed control laws, the attitude of spacecraft converge to desired attitude in finite time.
引用
收藏
页码：1397 / 1401
页数：5
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