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Barrier function-based adaptive integral sliding mode finite-time attitude control for rigid spacecraft

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Abstract

This paper investigates the problem of attitude tracking control with predefined-time convergence for rigid spacecraft under external disturbances and inertia uncertainties. Firstly, the proposed nominal controller is designed to achieve attitude tracking control of the rigid spacecraft in the absence of disturbances and inertia uncertainties, and the convergence of the spacecraft attitude errors can be selected in advance. Then, the integral sliding mode combined with barrier function-based adaptive laws is proposed to reject the disturbances and inertia uncertainties, and at the same time, a barrier function-based adaptive method can also ensure the solutions of the rigid spacecraft system belonging to a stipulated vicinity of the intended variables starting from the initial moment and the uncertainties’ upper bound is not overestimated. Finally, a numerical simulation is provided to illustrate the efficiency of the proposed control protocol.

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Acknowledgements

The authors would like to express their gratitude to the Editor and all of the reviewers for their professional and constructive comments and suggestions, which have greatly improved the quality of this paper.

Funding

This work is supposed in part by the Foundation under Grant 2019-JCJQ-ZD-049. The National Natural Science Foundation of China under Grants 61703134, 62022060, 62073234, and 61773278. The China Postdoctoral Science Foundation under Grant 2019M650874. The Science and Technology Research Project of Colleges and Universities in Hebei Province under Grant BJ2020017. The Undergraduate Education and Teaching Reform Research and Practice Project 202004023. The Key R &D Program of Hebei Province 20310802D, Natural Science Foundation of Hebei Province under Grants F2019202369, F2018202279 and F2019 202363.

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Authors and Affiliations

  1. Institute of Artificial Intelligence, University of Science and Technology Beijing, Beijing, 100083, China

    Jie Wang

  2. School of Artificial Intelligence and Data Science, Hebei University of Technology, Tianjin, 300130, China

    Yushang Hu & Wenqiang Ji

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  1. Jie Wang
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Correspondence to Jie Wang.

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Wang, J., Hu, Y. & Ji, W. Barrier function-based adaptive integral sliding mode finite-time attitude control for rigid spacecraft. Nonlinear Dyn 110, 1405–1420 (2022). https://doi.org/10.1007/s11071-022-07727-6

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