抄録
This paper studies the attitude control problem of articulated spacecraft. In such a system, it is required to control the spacecraft attitude against disturbances and model variations by appendage rotates at high angular velocity. To this problem, we apply the robust gain scheduled controller synthesis based on H_∞ synthesis of Linear Parameter Varying System. The controller is designed by two type methods of analytical and numerical convex decomposition. The capability of these methods is investigated and compared through a numerical study.
