@inproceedings{oai:jaxa.repo.nii.ac.jp:00007544,
 author = {坂井, 真一郎 and 福島, 洋介 and 斎藤, 宏文 and Sakai, Shinichiro and Fukushima, Yosuke and Saito, Hirobumi},
 book = {第16回アストロダイナミクスシンポジウム講演後刷り集　2006, Proceedings of 16th Workshop on JAXA Astrodynamics and Flight Mechanics},
 month = {Mar},
 note = {2005年8月に打ち上げられた小型科学衛星'れいめい(INDEX: INnovative-technology Demonstration EXperiment)'では、衛星小型化のためにホイールは1台のみを使用し、主に磁気トルカにより姿勢制御を行っている。このような磁気姿勢制御で0.1度以下の姿勢制御精度を実現している点が、'れいめい'衛星の1つの特徴ともなっている。本発表では、この磁気姿勢制御則の設計とその軌道上評価の結果について報告する。, Magnetic attitude control methods for the REIMEI (INDEX: INnovative-technology Demonstration EXperiment) microsatellite is presented. REIMEI is a 70 (kg) microsatellite and was launched in 2005. REIMEI achieved pointing accuracy of 0.05 - 0.1 (deg), with actuators of three Magnetic Torquers (MTQs) and one moment wheel. With this configuration, the management of magnetic torque is important for attitude control. This paper proposes practical MTQs drive algorithm to generate required magnetic torque, maintaining undesirable disturbance torque to be low enough even in the neighborhood of singular points. Another key technology for the REIMEI satellite is in-orbit estimation of residual magnetic moment and its feedforward cancellation. This method will contribute a lot, not only for a bias momentum satellite, but also for small/micro satellites with pure magnetic ACS (Attitude Control System). These proposed methods are demonstrated with in-orbit data of the REIMEI microsatellite., 資料番号: AA0063481043},
 pages = {248--254},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)},
 title = {Design and on-orbit evaluation of magnetic attitude control system for REIMEI microsatellite},
 year = {2007}
}