Composite adaptive attitude control for combined spacecraft with inertia uncertainties
This paper examines the attitude control problem of the combined spacecraft subject to inertia uncertainties. A composite adaptive finite-time control scheme with guaranteed parameter convergence is proposed to address this challenging problem, in the absence of persistent excitation. As a stepping...
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| Published in | Aerospace science and technology Vol. 131; p. 107984 |
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| Main Authors | , , |
| Format | Journal Article |
| Language | English |
| Published |
Elsevier Masson SAS
01.12.2022
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| Subjects | |
| Online Access | Get full text |
| ISSN | 1270-9638 1626-3219 |
| DOI | 10.1016/j.ast.2022.107984 |
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| Abstract | This paper examines the attitude control problem of the combined spacecraft subject to inertia uncertainties. A composite adaptive finite-time control scheme with guaranteed parameter convergence is proposed to address this challenging problem, in the absence of persistent excitation. As a stepping stone, the attitude dynamics of the combined spacecraft is first established with explicit consideration of the center-of-mass variation and thruster reconfiguration. Then, a composite adaptive finite-time controller is developed based on a constructive time-varying sliding manifold, and in particular, the concurrent learning technique is used in conjunction with the dynamic regressor extension and mixing procedure to achieve parameter convergence under finite excitation that is strictly weaker than the persistent excitation. Lyapunov stability analysis shows that the derived adaptive controller can simultaneously guarantee finite-time convergence of the attitude tracking and parameter estimation errors; moreover, its robustness against inertia variations and external disturbances is also analyzed. Finally, a set of numerical simulations under ideal and practical scenarios are performed to validate the effectiveness and outperformance of the proposed method. |
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| AbstractList | This paper examines the attitude control problem of the combined spacecraft subject to inertia uncertainties. A composite adaptive finite-time control scheme with guaranteed parameter convergence is proposed to address this challenging problem, in the absence of persistent excitation. As a stepping stone, the attitude dynamics of the combined spacecraft is first established with explicit consideration of the center-of-mass variation and thruster reconfiguration. Then, a composite adaptive finite-time controller is developed based on a constructive time-varying sliding manifold, and in particular, the concurrent learning technique is used in conjunction with the dynamic regressor extension and mixing procedure to achieve parameter convergence under finite excitation that is strictly weaker than the persistent excitation. Lyapunov stability analysis shows that the derived adaptive controller can simultaneously guarantee finite-time convergence of the attitude tracking and parameter estimation errors; moreover, its robustness against inertia variations and external disturbances is also analyzed. Finally, a set of numerical simulations under ideal and practical scenarios are performed to validate the effectiveness and outperformance of the proposed method. |
| ArticleNumber | 107984 |
| Author | Hu, Qinglei Shao, Xiaodong Xu, Yiqi |
| Author_xml | – sequence: 1 givenname: Yiqi surname: Xu fullname: Xu, Yiqi organization: School of Automation Science and Electrical Engineering, Beihang University, Beijing 100191, China – sequence: 2 givenname: Qinglei surname: Hu fullname: Hu, Qinglei email: huql_buaa@buaa.edu.cn organization: School of Automation Science and Electrical Engineering, Beihang University, Beijing 100191, China – sequence: 3 givenname: Xiaodong orcidid: 0000-0003-2640-5594 surname: Shao fullname: Shao, Xiaodong email: xdshao_sasee@buaa.edu.cn organization: School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China |
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| Cites_doi | 10.1109/TAC.2011.2159419 10.1016/j.ast.2021.106746 10.2514/2.4837 10.2514/1.46866 10.1016/j.paerosci.2020.100678 10.2514/1.33308 10.1016/j.ast.2020.106310 10.2514/1.35188 10.2514/1.31158 10.1109/TAES.2017.2729978 10.2514/2.4415 10.1016/j.ast.2020.106331 10.1016/j.actaastro.2018.11.008 10.1016/j.ast.2021.106560 10.1016/j.ast.2020.106380 10.1109/TAC.2017.2737324 10.1109/TAC.2019.2911863 10.1002/acs.2297 10.1016/j.ast.2017.09.044 10.1016/0309-1708(91)90056-T 10.2514/1.G000457 10.1016/j.ast.2016.02.006 10.1109/TCST.2021.3076439 10.1016/j.cja.2018.12.015 |
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