A Robust Attitude Control Scheme Based on Eigenaxis Rotation for Spacecraft

고유축 회전에 근거한 우주비행체 강인 자세제어 기법

In this paper, a robust attitude control scheme based on Eigenaxis rotation for the spacecraft is proposed. Eigenaxis rotation transforms the attitude of spacecraft to the shortest path and is represented by quaternion. The control law consists of PD-type control part for the nominal system and the robust control part for compensating inertia uncertainty. For the proposed controller, stability analysis is performed and the performance is shown via computer simulation.