Predefined-Time Predefined-Bounded Attitude Tracking Control for Rigid Spacecraft

被引：115

作者：

Ye, Dong ^{[1
]}

Zou, An-Min ^{[2
]}

Sun, Zhaowei ^{[1
]}

机构：

[1] Harbin Inst Technol, Res Ctr Satellite Technol, Harbin 150001, Peoples R China

[2] Shantou Univ, Coll Engn, Dept Elect & Informat Engn, Shantou 515063, Peoples R China

来源：

IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS | 2022年 / 58卷 / 01期

基金：

中国国家自然科学基金;

关键词：

Attitude control; Space vehicles; Materials requirements planning; Angular velocity; Sliding mode control; Sun; Stability criteria; Attitude tracking control; predefined-time stability; rigid spacecraft; sliding-mode control; FINITE-TIME; LYAPUNOV FUNCTION; OUTPUT-FEEDBACK; STABILIZATION; VELOCITY; DESIGN;

D O I：

10.1109/TAES.2021.3103258

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

In this article, we consider the attitude tracking control problem for rigid spacecraft with bounded external disturbances. We propose a predefined-time predefined-bounded attitude tracking control scheme based on a nonsingular predefined-time sliding-mode manifold. The proposed controller is continuous and it can achieve predefined-time predefined-bounded stability. That is, the attitude tracking errors are driven to a predefined-bounded region around the origin within a predefined time, which can be set as a tuning parameter during the controller design, independently of initial conditions. Finally, numerical simulations are carried out to evaluate the performance of the proposed control law.

引用

页码：464 / 472

页数：9

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