Attitude control system for ROCSAT-3 microsatellite: a conceptual design
| dc.citation.epage | 452 | en_US |
| dc.citation.issue | 4 | en_US |
| dc.citation.spage | 439 | en_US |
| dc.citation.volume | 56 | en_US |
| dc.citation.woscount | 8 | |
| dc.contributor.author | Jan, YW | en_US |
| dc.contributor.author | Chiou, JC | 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.date.accessioned | 2014-12-08T15:19:44Z | |
| dc.date.available | 2014-12-08T15:19:44Z | |
| dc.date.issued | 2005-02-01 | en_US |
| 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.identifier.doi | 10.1016/j.actaastro.2004.05.066 | en_US |
| dc.identifier.issn | 0094-5765 | en_US |
| dc.identifier.journal | ACTA ASTRONAUTICA | en_US |
| dc.identifier.uri | http://dx.doi.org/10.1016/j.actaastro.2004.05.066 | en_US |
| dc.identifier.uri | https://ir.lib.nycu.edu.tw/handle/11536/14019 | |
| dc.identifier.wosnumber | WOS:000226388000002 | |
| 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 |