Quaternion-based attitude maneuver hardware-in-the-loop simulation for micro satellite

The paper presents a quaternion-based attitude control algorithm which is subject to control input constraints for rigid spacecrafts. Lyapunov theory is employed to prove the global asymptotic stability of the zero equilibrium points of the close loop system. Also the algorithm is validated by the corresponding hardware-in-the-loop (HIL) simulation using a single-axis air bearing table and other hardware. And the simulation results indicate that the algorithm can efficiently accomplish the attitude maneuver.