期刊
CHINESE JOURNAL OF AERONAUTICS
卷 34, 期 11, 页码 182-199出版社
ELSEVIER SCIENCE INC
DOI: 10.1016/j.cja.2020.12.024
关键词
Collision avoidance; Disturbance rejection; Fixed-time stability; Sliding mode control; Spacecraft formation flying
资金
- Major Program of Natural Science Foundation of China [61690210]
- Science Fund for Excellent Young Scholars of Heilongjiang Province, China [YQ2020F007]
- National Natural Science Foundation of China [6191101340]
This paper introduces a fixed-time stability control method for spacecraft formation reconfiguration. By designing terminal sliding mode surfaces and coordinated controllers, the system states achieve finite settling time while meeting mutual distance constraints.
In this paper, the fixed-time stability of spacecraft formation reconfiguration (position tracking) is studied. Firstly, a novel nonsingular terminal sliding mode surface is designed and based on which a fixed-time coordinated controller is designed to keep the closed-loop system states have a finite settling time bounded by some predefined constants. Secondly, another nonsingular terminal sliding mode surface is designed by combining the artificial potential function and the aforementioned sliding surface, which meets the mutual distance constraint during transition process among spacecraft when it is bounded. Then another coordinated controller with fixed-time observer considering mutual distance constraint is presented, which guarantees the closed-loop system states stable also in bounded settling time. Finally, simulation results are shown to validate the correctness of the proposed theorems. It is worth mentioning that the control schemes also work even though there is a properly limit on the control input. (c) 2021 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).
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