Abstract
TSUBAME is a 50kg microsatellite developed by Matunaga Lab. at ISAS/JAXA and Tokyo Institute of Technology, and was launched and released into a Sun-synchronous orbit on November 6, 2014. TSUBAME automatically deployed solar array paddles and performed the sun pointing sequence after the rocket separation. Before the launch, attitude determination and control subsystem of TSUBAME must be designed and verified to satisfy that even in the worst case scenario, TSUBAME can point to the sun and balance power electricity in 30000s after separation, if not, it loses power and switches to hibernation mode, performing only the battery charging. In this paper, Monte Carlo simulation is conducted for the attitude control behavior after separation using HiLS and Flight model of TSUBAME, and shows a low probability of the power shortage occurring in consideration of precise electric power estimation.
