Please use this identifier to cite or link to this item: https://hdl.handle.net/10356/155207
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dc.contributor.authorWang, Chenliangen_US
dc.contributor.authorGuo, Leien_US
dc.contributor.authorWen, Changyunen_US
dc.contributor.authorHu, Qingleien_US
dc.contributor.authorQiao, Jianzhongen_US
dc.date.accessioned2022-02-15T07:29:00Z-
dc.date.available2022-02-15T07:29:00Z-
dc.date.issued2020-
dc.identifier.citationWang, C., Guo, L., Wen, C., Hu, Q. & Qiao, J. (2020). Event-triggered adaptive attitude tracking control for spacecraft with unknown actuator faults. IEEE Transactions On Industrial Electronics, 67(3), 2241-2250. https://dx.doi.org/10.1109/TIE.2019.2905837en_US
dc.identifier.issn0278-0046en_US
dc.identifier.urihttps://hdl.handle.net/10356/155207-
dc.description.abstractThis paper is devoted to attitude tracking control of fractionated spacecraft with wireless communication. We consider the practical case that the spacecraft suffers from uncertain inertia parameters, external disturbances, and even unknown and time-varying actuator faults. Within the framework of the backstepping method, a novel event-triggered adaptive fault-tolerant control scheme is proposed. In our design, an event-triggering mechanism is introduced to determine the time instants for communication, which successfully avoids continuous communication and Zeno phenomenon. Then, with the aid of a bound estimation approach and a smooth function, the impacts of the actuator faults, as well as the network-induced error, are effectively compensated for. Moreover, by employing the prescribed performance control technique, it is shown that the attitude tracking errors can converge to predefined arbitrarily small residual sets with prescribed convergence rate and maximum overshoot, no matter if there exist unknown actuator faults. Compared with conventional adaptive attitude control schemes, the proposed scheme significantly reduces the communication burden, while providing high reliability and stable, rapid, and accurate response for attitude maneuvers. Simulation results are presented to illustrate the effectiveness of the proposed scheme.en_US
dc.language.isoenen_US
dc.relation.ispartofIEEE Transactions on Industrial Electronicsen_US
dc.rights© 2019 IEEE. All rights reserved.en_US
dc.subjectEngineering::Electrical and electronic engineeringen_US
dc.titleEvent-triggered adaptive attitude tracking control for spacecraft with unknown actuator faultsen_US
dc.typeJournal Articleen
dc.contributor.schoolSchool of Electrical and Electronic Engineeringen_US
dc.identifier.doi10.1109/TIE.2019.2905837-
dc.identifier.scopus2-s2.0-85074681366-
dc.identifier.issue3en_US
dc.identifier.volume67en_US
dc.identifier.spage2241en_US
dc.identifier.epage2250en_US
dc.subject.keywordsAdaptive Controlen_US
dc.subject.keywordsUncertaintiesen_US
dc.description.acknowledgementThis work was supported in part by the National Natural Science Foundation of China under Grant 61673036, Grant 61661136007, and Grant 61603021, in part by the Beijing Natural Science Foundation under Grant 4182036, and in part by the Program for Changjiang Scholars and Innovative Research Team under Grant IRT_16R03.en_US
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