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In early 2014, three micro-satellites, named UNIFORM-1, HODOYOSHI-3, and HODOYOSHI-4, were launched. These satellites used the newly developed standard micro-satellite bus system, which aims to reduce the development period and cost of a satellite with the help of a recoverable system concept. This paper describes the system concept, design summary, on-ground evaluation system, and on-orbit performance of the attitude determination and control system. The satellites have achieved initial attitude acquisition and shown acceptable levels of three-axis stabilization performance and system survivability despite unexpected anomalies in the components. In its discussion of on-orbit performance, this paper focuses on the three-axis stabilization phase. The unexpected problems are summarized and the procedures for adjusting to the anomalies are explained.

On-Orbit Evaluations of the Three Axis Stabilization Performances of Standard Micro-Satellite Buses