NEC TOSHIBA Space Systems
NEC TOSHIBA Space Systems
NEC
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
For steering a control moment gyro (CMG)-system which is installed as an actuator system of spacecraft, there are lots of previous researches which aim to avoid and leave from vicinity of the singular points of CMG-system. But some steering laws may not be able to manage to output enough torque during an attitude maneuver phase. Because almost all of these researches does not consider the feature of required torque during an attitude maneuver phase. During an attitude maneuver phase, a large feed forward torque is required in an attitude maneuver direction. So the CMG steering law is required the capability of avoiding not only singular points but also the insufficient torque area near a singular point and provide enough torque in an attitude maneuver direction. In some previous researches, only singular points are taken into consideration. Such a steering law will be useful only during the attitude pointing phase in which a small torque is required. During an attitude maneuver phase, there is an important feature that a large control torque is required in a maneuver direction only, and the control torque perpendicular to the maneuver direction is not of importance. In other words, the torquing capability of the CMG-system can be optimized especially for the maneuver direction during an attitude maneuver phase. There is no research which takes this feature into consideration. From this point of view, in this paper, we propose a new steering law of CMG that generate torque effectively in any required direction. A large torque can be generated in the required torque direction with this method. Therefore, this is the method of utilizing the CMG system resource most effectively. This method provides an improved use of the torquing capability of the CMG-system especially during attitude maneuver of spacecraft.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
異方性重み付き傾斜法によるCMGシステム駆動
