Attitude control of low-orbit micro-satellite with active magnetic torque and aerodynamic torque

In this paper a new scheme of attitude control with active magnetic torque and aerodynamic stabilization torque is proposed for low-orbit micro-satellite (orbit altitude lower than 500km), to take full advantage of environmental torque. Aerodynamic torque will be configured as stabilization torque by designing the relatively position of the center of pressure and the centroid. Simulation results show that detumbling is achieved in one orbit period. The angular velocities of three axes are reduced under 0.5deg/s, under the situation of attitude determination accuracy 1deg(1σ) and 0.02deg/s(1σ). Under the same situation, attitude acquisition is achieved in one orbit period, even though satellite is in a flip state. The pointing accuracy and stabilization accuracy are better than 1deg(1σ) and 0.02 deg/s(1σ).