Finite-time attitude tracking control for spacecraft without angular velocity measurements

被引：4
|
作者：
Yuan, Li [1 ]
Ma, Guangfu [1 ]
Li, Chuanjiang [1 ]
Jiang, Boyan [1 ]
机构：
[1] Harbin Inst Technol, Dept Control Sci & Engn, Harbin 150001, Heilongjiang, Peoples R China
来源：
JOURNAL OF SYSTEMS ENGINEERING AND ELECTRONICS | 2017年 / 28卷 / 06期
基金：
中国国家自然科学基金;
关键词：
output feedback; spacecraft attitude stabilization; finite-time control; TERMINAL SLIDING MODE; RIGID SPACECRAFT; OUTPUT-FEEDBACK; NONLINEAR-SYSTEMS; STABILIZATION; DISTURBANCES;
D O I：
10.21629/JSEE.2017.06.15
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
The output feedback control for spacecraft attitude tracking system is investigated in this study. It is assumed that angular velocity measurements are not available for feedback control. A technique named adding power integrator (API) is adopted to estimate the pseudo-angular-velocity. Then we design a finite-time attitude control law, which only utilizes the relative attitude information. The stability analyses of the feedback system are proved as well, which shows the attitude tracking errors will converge into a region of zero even the external disturbances exist. The simulation results illustrate the high precision and robust attitude control performance of the proposed control strategy.
引用
收藏
页码：1174 / 1185
页数：12
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