Abstract: Research involved in this paper focuses on attitude dynamics modeling and control of a spin-stabilized micro-satellite for near-earth space exploration. There are some special requirements for attitude control due to the scientific mission. During modeling, the effect of double-side booms-extended disturbance on the satellite attitude has been considered in detail. Using the nutation characteristics of the spin-stabilized satellite, a controller of attitude control combined with nutation control has been designed. The firing time is determined based on the phase of satellite transverse angular velocity and the orientation of jet torque in the inertial space. Following control strategy has been applied: firstly coarse nutation control and precession control, then fine nutation control. When the satellite nutation angle is large due to the long term action of disturbance torques and orbit maneuver is needed, this controller can be used to adjust the orientation of spin axis conveniently.

Key words: spin-stabilized micro-satellite, modeling, attitude dynamics, nutation control , attitude control