FINITE-TIME ATTITUDE TRACKING CONTROL FOR SPACECRAFT WITHOUT ANGULAR VELOCITY MEASUREMENT

被引：0
作者：
Jiang, Boyan [1 ]
Li, Chuanjiang [1 ]
Guo, Yanning [1 ]
Dong, Hongyang [1 ]
机构：
[1] Harbin Inst Technol, Dept Control Sci & Engn, Harbin 150001, Heilongjiang, Peoples R China
来源：
SPACEFLIGHT MECHANICS 2017, PTS I - IV | 2017年 / 160卷
基金：
中国国家自然科学基金;
关键词：
TERMINAL SLIDING MODE; RIGID SPACECRAFT; OUTPUT-FEEDBACK; NONLINEAR-SYSTEMS; STABILIZATION; DISTURBANCES;
D O I：
暂无
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
This paper investigates the finite-time output feedback problem of attitude tracking control for spacecraft. It is assumed that the angular velocity information is not available for the controller design. An adding a power integrator technique based filter is designed to generate the pseudo-angular-velocity estimates, then a finite-time output feedback attitude tracking controller is developed with relative-attitude-only measurement. Overall finite-time stability of the entire closed-loop system is given, which shows the attitude tracking errors will converge into a region of zero in the presence of external disturbance. The simulation results illustrate the highly precision and robust attitude control performance of the proposed controllers.
引用
收藏
页码：2591 / 2602
页数：12
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