@inproceedings{oai:jaxa.repo.nii.ac.jp:00007612,
 author = {遠藤, 達也 and Endo, Tatsuya},
 book = {第15回アストロダイナミクスシンポジウム講演後刷り集　2005, Proceedings of 15th Workshop on JAXA Astrodynamics and Flight Mechanics},
 month = {Mar},
 note = {筆者らはこれまでに、2ホイール衛星の姿勢変更について、エネルギ最小制御則を議論してきた。これらは、姿勢変更をホイールの存在しない軸周りの姿勢変更に限定して検討を行ってきた。本論では、3軸の慣性モーメント比が2軸対称、1軸非対称の初期角運動量を持つ衛星(バイアスモーメンタム衛星を含む)の3軸姿勢制御について角運動量保存の観点から安定化可能な姿勢について議論するため、数値最適解をニューテーション周期と比較した。結果、最適解とニューテーション周期の相関は見られなかった。, Authors have been discussing the energy minimum control low about the satellite maneuver with only two reaction wheel. The maneuver is limited around the axis where the wheel doesn't exist and these have been being examined. This paper discuss about the energy minimum control low of satellite having initial angular momentum. That is included the bias momentum satellite. The satellite's moment of inertia is axisymmetric. The attitude stability of satellite on three-axis pointing control is discussed from the point of angular momentum preservation rule. Moreover, a numerical solution is compared with the Nutation cycle., 資料番号: AA0063480047},
 pages = {296--299},
 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 = {Optimization of three axis control of two wheel satellite with initial angular momentum},
 year = {2006}
}