Terminal Sliding Mode Control for Attitude Tracking of Spacecraft Based on Rotation Matrix
Joint Authors
Song, Shenmin
Guo, Yong
Li, Xue-Hui
Source
Mathematical Problems in Engineering
Issue
Vol. 2015, Issue 2015 (31 Dec. 2015), pp.1-9, 9 p.
Publisher
Hindawi Publishing Corporation
Publication Date
2015-03-02
Country of Publication
Egypt
No. of Pages
9
Main Subjects
Abstract EN
Two finite-time controllers without unwinding for the attitude tracking control of the spacecraft are investigated based on the rotation matrix, in which a novel modified nonsingular fast terminal sliding manifold is developed to keep tr(R~)≠-1.
The first terminal sliding mode controller can compensate external disturbances with known bounds, while the second one can compensate external disturbances with unknown bounds by using an adaptive control method.
Since the first terminal sliding mode controller is continuous, it is able to avoid chattering phenomenon.
Theoretical analysis shows that both the two controllers can make spacecraft follow a time-varying reference attitude signal in finite time.
Numerical simulations also demonstrate that the proposed control schemes are effective.
American Psychological Association (APA)
Guo, Yong& Song, Shenmin& Li, Xue-Hui. 2015. Terminal Sliding Mode Control for Attitude Tracking of Spacecraft Based on Rotation Matrix. Mathematical Problems in Engineering،Vol. 2015, no. 2015, pp.1-9.
https://search.emarefa.net/detail/BIM-1073167
Modern Language Association (MLA)
Guo, Yong…[et al.]. Terminal Sliding Mode Control for Attitude Tracking of Spacecraft Based on Rotation Matrix. Mathematical Problems in Engineering No. 2015 (2015), pp.1-9.
https://search.emarefa.net/detail/BIM-1073167
American Medical Association (AMA)
Guo, Yong& Song, Shenmin& Li, Xue-Hui. Terminal Sliding Mode Control for Attitude Tracking of Spacecraft Based on Rotation Matrix. Mathematical Problems in Engineering. 2015. Vol. 2015, no. 2015, pp.1-9.
https://search.emarefa.net/detail/BIM-1073167
Data Type
Journal Articles
Language
English
Notes
Includes bibliographical references
Record ID
BIM-1073167