Aoyama Gakuin University
Aoyama Gakuin University
Aoyama Gakuin University
出版者
宇宙航空研究開発機構宇宙科学研究本部
出版者（英）
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)
雑誌名
アストロダイナミクスシンポジウム講演後刷り集
雑誌名(英)
Proceedings of 18th workshop on JAXA Astrodynamics and flight mechanics
巻
2008
発行年
2009-03
会議概要（会議名, 開催地, 会期, 主催者等）（英）
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
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.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
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
