Attitude Controller Design for Combined Spacecraft after Separated LIU Sai, XU Shijie

Based on varieties of the inertia matrix for a combined spacecraft separated, this paper proposes a adaptive control algorithm. Attitude quaternion is adopted to establish the model of the kind of spacecraft, and based on the Lyapunov stability theory, the algorithm is designed by the backstepping control method. Theoretical analysis proves the algorithm be stable, and the simulation results confirm the effectiveness of the algorithm.