@inproceedings{oai:jaxa.repo.nii.ac.jp:00007382,
 author = {菅原, 佳城 and 木田, 康弘 and 小林, 信之 and Sugawara, Yoshiki and Kida, Yasuhiro and Kobayashi, Nobuyuki},
 book = {アストロダイナミクスシンポジウム講演後刷り集, Proceedings of 18th workshop on JAXA Astrodynamics and flight mechanics},
 month = {Mar},
 note = {Symposium on Flight Mechanics and Astrodynamics 2008 (July 28-29, 2008. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)), Sagamihara, Kanagawa Japan, 摘要: 人工衛星における展開機構では打上げ時の負荷や高真空環境に起因する不具合がしばしば発生する。一般に展開機構は展開動作部と展開形状固定部から成るが、後者を省くことで信頼性が向上する一方、展開構造部の柔軟性や衝突運動によって姿勢制御性能の劣化が発生する。このような性能劣化をUnilateral Contactによる力積推定を併用したコンプライアンス制御から構成される制御系によって補償することを提案し、その効果を数値解析によって示す。, Deployment mechanisms of satellites often have some troubles due to high load from launch vehicle and high vacuum environment. Generally, deployment mechanisms consist of two members, one is a deployment drive part and the other is a latching part. Removal of latching part brings higher reliability but induces degradations of attitude control performance due to flexibility and impact motion of that mechanism. In our research such a degradation of the performance is compensated by the use of the controller which consists of compliance control law with impulse torque estimator., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064733008},
 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)},
 title = {簡易展開機構を有する人工衛星の姿勢制御系についての検討},
 volume = {2008},
 year = {2009}
}