Fig. 1 QSIn space Systems Dynamics Laboratory at Kyushu University, the micro-satellite QSAT
Attitude Determination and Control System for QSAT
Yuya Mimasu*, Kikuko Miyata, Tomohiro Narumi, Jozef C. van der Ha
Department of Aeronautics and Astronautics,
Faculty of Engineering, Kyushu University, Fukuoka, Japan
Phone: +81-92-802-3049, e-mail:number9@ aero.kyushu-u.ac.jp
Abstract
In Space Systems Dynamics Laboratory (SSDL) at Kyushu University, the small satellite QSAT is being developed. In order to achieve the mission objectives, the attitude must be determined and controlled precisely. One function of the Attitude Determination and Control Subsystem (ADCS) is to estimate the attitude of the satellite by means of a Sun sensor, magnetometer and gyro rate sensor. Another function is to control the attitude by using the three-axis magnetorquer. The attitude determination of QSAT is based on a combination of the Weighted-Least-Square and Kalman-filter estimation methods. The Weighted-Least-Square method uses the Sun sensor and magnetometer measurements and the Kalman-filter combines the resulting angular observations with the gyro rate measurements. The attitude control is performed by a magnetorquer on the basis of a B-dot control for the de-tumbling phase and a Proportional-Derivative (PD) control law for the normal-mode.
「QSATにおける姿勢決定及び姿勢制御」
三桝裕也* 宮田喜久子 鳴海智博 Jozef C. van der Ha
九州大学大学院 工学府 航空宇宙工学専攻
概要
九州大学の宇宙機ダイナミクス研究室では、小型衛星QSATの開発が進められている。ミッション達成のために正確に姿勢決定及び姿勢制御を行うことが不可欠で、QSATにおいては太陽センサ、磁気センサ、ジャイロセンサを用いた姿勢決定、及び磁気トルカを用いた姿勢制御を行う。最小二乗法とKalman Filterを併用した姿勢決定法、B-dot制御とPD制御を使用した制御則の確立のために、独自で開発したシミュレータを用いて検証を行っており、今回はその進捗を報告する。