Attitude control system for ROCSAT-3 microsatellite: a conceptual design

doi:10.1016/j.actaastro.2004.05.066

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DC 欄位	值	語言
dc.contributor.author	Jan, YW	en_US
dc.contributor.author	Chiou, JC	en_US
dc.date.accessioned	2014-12-08T15:19:44Z	-
dc.date.available	2014-12-08T15:19:44Z	-
dc.date.issued	2005-02-01	en_US
dc.identifier.issn	0094-5765	en_US
dc.identifier.uri	http://dx.doi.org/10.1016/j.actaastro.2004.05.066	en_US
dc.identifier.uri	http://hdl.handle.net/11536/14019	-
dc.description.abstract	The ROCSAT-3 attitude control subsystem is conceptually designed to meet the weight and power constraints of a microsatellite. Attractive features of the proposed design include (a) a control scheme for initial attitude acquisition, which provides a fully autonomous attitude hold, no duration limit and adequate attitude for power generation and (b) a feasible implementation for a microsatellite which has uncommon mission demands such as an orbit raising maneuver and practical weight and power constraints. The proposed control schemes for the three control modes and the spacecraft attitude dynamics are analyzed to demonstrate the satisfaction of the designated mission goals. (C) 2004 Elsevier Ltd. All rights reserved.	en_US
dc.language.iso	en_US	en_US
dc.title	Attitude control system for ROCSAT-3 microsatellite: a conceptual design	en_US
dc.type	Article	en_US
dc.identifier.doi	10.1016/j.actaastro.2004.05.066	en_US
dc.identifier.journal	ACTA ASTRONAUTICA	en_US
dc.citation.volume	56	en_US
dc.citation.issue	4	en_US
dc.citation.spage	439	en_US
dc.citation.epage	452	en_US
dc.contributor.department	電控工程研究所	zh_TW
dc.contributor.department	Institute of Electrical and Control Engineering	en_US
dc.identifier.wosnumber	WOS:000226388000002	-
dc.citation.woscount	8	-
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