Predefined-Time Observer-Based Nonsingular Sliding-Mode Control for Spacecraft Attitude Stabilization

被引：23

作者：

Chen, Jingyi ^{[1
]}

Chen, Zhaoyue ^{[2
]}

Zhang, Haichao ^{[3
]}

Xiao, Bing ^{[3
]}

Cao, Lu ^{[4
]}

机构：

[1] Natl Univ Def Technol, Coll Aerosp Sci & Engn, Changsha 410003, Peoples R China

[2] Beijing Inst Technol, Inst Adv Struct Technol, Beijing 100081, Peoples R China

[3] Northwestern Polytech Univ, Sch Automat, Xian 710072, Peoples R China

[4] Chinese Acad Mil Sci, Natl Innovat Inst Def Technol, Beijing 100071, Peoples R China

来源：

IEEE TRANSACTIONS ON CIRCUITS AND SYSTEMS II-EXPRESS BRIEFS | 2024年 / 71卷 / 03期

基金：

中国国家自然科学基金;

关键词：

Attitude control; Space vehicles; Disturbance observers; Convergence; Upper bound; Lyapunov methods; Sliding mode control; Spacecraft; attitude stabilization; sliding mode control; disturbance observer; predefined-time; TRACKING CONTROL; TOLERANT CONTROL;

D O I：

10.1109/TCSII.2023.3321684

中图分类号：

TM [电工技术]; TN [电子技术、通信技术];

学科分类号：

0808 ; 0809 ;

摘要：

The predefined-time attitude stabilization control problem of a spacecraft with external disturbance is addressed. A predefined-time observer-based control approach is presented using a new nonsingular sliding surface. On this sliding surface, the system states can converge to zero within a predefined time. Moreover, the incorporated disturbance observer is continuous with the chattering phenomenon eliminated. Compared with the existing finite/fixed-time attitude control methods, which need a complex process to determine the settling time, the upper bound of the convergence time ensured by the presented approach is determined by a constant only. Simulation study is further given to confirm that the presented controller is effective.

引用

页码：1291 / 1295

页数：5

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