The original paper is in English. Non-English content has been machine-translated and may contain typographical errors or mistranslations. ex. Some numerals are expressed as "XNUMX".
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The original paper is in English. Non-English content has been machine-translated and may contain typographical errors or mistranslations. Copyrights notice
Un algorithme de capture rapide de l'attitude initiale est proposé pour l'engin spatial utilisant des roues de réaction. Cet algorithme est composé de deux étapes. La première étape concerne l'absorption du moment cinétique initial du vaisseau spatial dans les roues de réaction et la deuxième étape, une manœuvre à grand angle de repos pour réinitialiser pour le suivi du soleil. Un critère de capture d'attitude initiale et un contrôleur pour la méthode de manœuvre rapide à grand angle sont présentés en tenant compte des contraintes des roues de réaction. Les résultats de la simulation montrent que l'algorithme proposé présente plusieurs avantages en termes de capture d'attitude initiale et de manœuvre rapide à grand angle. Cet algorithme peut être appliqué au contrôle de rotation temporelle quasi minimale du vaisseau spatial.
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Hyunwoo LEE, Dong-Jo PARK, "Fast Capture Algorithm of Initial Attitude for Spacecraft Using Reaction Wheels" in IEICE TRANSACTIONS on Fundamentals,
vol. E85-A, no. 10, pp. 2311-2317, October 2002, doi: .
Abstract: A fast capture algorithm of the initial attitude is proposed for the spacecraft using reaction wheels. This algorithm is composed of two steps. The first step deals with absorption of the initial angular momentum of the spacecraft into the reaction wheels and the second step a rest-to-reset large angle maneuver for sun tracking. A criterion of the initial attitude capture and a controller for the fast large angle maneuver method are presented under considering constraints of the reaction wheels. Simulation results show that the proposed algorithm has several advantages of the initial attitude capture and fast large angle maneuver. This algorithm can be applied to the near minimum time rotation control of the spacecraft.
URL: https://global.ieice.org/en_transactions/fundamentals/10.1587/e85-a_10_2311/_p
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@ARTICLE{e85-a_10_2311,
author={Hyunwoo LEE, Dong-Jo PARK, },
journal={IEICE TRANSACTIONS on Fundamentals},
title={Fast Capture Algorithm of Initial Attitude for Spacecraft Using Reaction Wheels},
year={2002},
volume={E85-A},
number={10},
pages={2311-2317},
abstract={A fast capture algorithm of the initial attitude is proposed for the spacecraft using reaction wheels. This algorithm is composed of two steps. The first step deals with absorption of the initial angular momentum of the spacecraft into the reaction wheels and the second step a rest-to-reset large angle maneuver for sun tracking. A criterion of the initial attitude capture and a controller for the fast large angle maneuver method are presented under considering constraints of the reaction wheels. Simulation results show that the proposed algorithm has several advantages of the initial attitude capture and fast large angle maneuver. This algorithm can be applied to the near minimum time rotation control of the spacecraft.},
keywords={},
doi={},
ISSN={},
month={October},}
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TY - JOUR
TI - Fast Capture Algorithm of Initial Attitude for Spacecraft Using Reaction Wheels
T2 - IEICE TRANSACTIONS on Fundamentals
SP - 2311
EP - 2317
AU - Hyunwoo LEE
AU - Dong-Jo PARK
PY - 2002
DO -
JO - IEICE TRANSACTIONS on Fundamentals
SN -
VL - E85-A
IS - 10
JA - IEICE TRANSACTIONS on Fundamentals
Y1 - October 2002
AB - A fast capture algorithm of the initial attitude is proposed for the spacecraft using reaction wheels. This algorithm is composed of two steps. The first step deals with absorption of the initial angular momentum of the spacecraft into the reaction wheels and the second step a rest-to-reset large angle maneuver for sun tracking. A criterion of the initial attitude capture and a controller for the fast large angle maneuver method are presented under considering constraints of the reaction wheels. Simulation results show that the proposed algorithm has several advantages of the initial attitude capture and fast large angle maneuver. This algorithm can be applied to the near minimum time rotation control of the spacecraft.
ER -