抄録
"TSUBAME", an earth and astronomical observation technology demonstration satellite being now developed by Matunaga laboratory at ISAS/JAXA, has the control moment gyro (CMG) system arranged in the pyramid type as an attitude control device. In this paper, we firstly mention the influence of disturbance torque which the CMG system generates at activation and deactivation on the satellite attitude, and propose an attitude stabilization control method, and explain numerical simulation results of the proposal method compared with hardware experimental results.
