Fixed-time attitude tracking control for rigid spacecraft

The problem of fixed-time attitude tracking control for rigid spacecraft is addressed in this paper. Based on the backstepping technique and the idea of “adding a power integrator”, a novel fixed-time attitude control law is proposed. The control scheme derived here is continuous and nonsingular, an...

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Bibliographic Details
Published inAutomatica (Oxford) Vol. 113; p. 108792
Main Authors Zou, An-Min, Kumar, Krishna Dev, de Ruiter, Anton H.J.
Format Journal Article
LanguageEnglish
Published Elsevier Ltd 01.03.2020
Subjects
Adding a power integrator
Backstepping
Fixed-time control
Rigid spacecraft
Rigid spacecraft
Backstepping
Fixed-time control
Adding a power integrator
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Summary:The problem of fixed-time attitude tracking control for rigid spacecraft is addressed in this paper. Based on the backstepping technique and the idea of “adding a power integrator”, a novel fixed-time attitude control law is proposed. The control scheme derived here is continuous and nonsingular, and can guarantee the attitude tracking errors converging to the origin within fixed time if there are no uncertainties and measurement noises and to a small bounded region around zero if there are uncertainties and measurement noises. Finally, numerical simulations are presented to demonstrate the effectiveness of the proposed scheme.
ISSN:0005-1098
1873-2836
DOI:10.1016/j.automatica.2019.108792