Design and Verification of Attitude Control System for A Small Satellite

∗Because of its lightweight, small size, short launch cycle, and many other advantages, microsatellite has been widely used in military and civil fields. In this paper, the attitude control system of a microsatellite is designed according to the project’s requirements, which provides a reference for others to research microsatellite attitude control. This paper first introduces the system’s hardware composition and working mode according to the criteria of attitude control, then designs the software operation flow, data acquisition, and control sequence of the attitude control system, and finally carries out the simulation test to verify the rationality of the design.