SLIDING-MODE CONTROLLER-DESIGN FOR SPACECRAFT ATTITUDE TRACKING MANEUVERS

doi:10.1109/7.259536

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DC 欄位	值	語言
dc.contributor.author	CHEN, YP	en_US
dc.contributor.author	LO, SC	en_US
dc.date.accessioned	2014-12-08T15:04:20Z	-
dc.date.available	2014-12-08T15:04:20Z	-
dc.date.issued	1993-10-01	en_US
dc.identifier.issn	0018-9251	en_US
dc.identifier.uri	http://dx.doi.org/10.1109/7.259536	en_US
dc.identifier.uri	http://hdl.handle.net/11536/2831	-
dc.description.abstract	This paper presents a robust sliding-mode control law to deal with the spacecraft attitude tracking problems. Two important natural properties related to the spacecraft model of motion are shown and then by using these properties and the second method of Lyapunov theory, the system stability in the sliding mode can be easily achieved. The success of the sliding-mode controller and the robustness to uncertainties are illustrated by an example of multiaxial attitude tracking maneuvers.	en_US
dc.language.iso	en_US	en_US
dc.title	SLIDING-MODE CONTROLLER-DESIGN FOR SPACECRAFT ATTITUDE TRACKING MANEUVERS	en_US
dc.type	Letter	en_US
dc.identifier.doi	10.1109/7.259536	en_US
dc.identifier.journal	IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS	en_US
dc.citation.volume	29	en_US
dc.citation.issue	4	en_US
dc.citation.spage	1328	en_US
dc.citation.epage	1333	en_US
dc.contributor.department	交大名義發表	zh_TW
dc.contributor.department	電控工程研究所	zh_TW
dc.contributor.department	National Chiao Tung University	en_US
dc.contributor.department	Institute of Electrical and Control Engineering	en_US
dc.identifier.wosnumber	WOS:A1993MD77700025	-
dc.citation.woscount	65	-
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