抄録
In this paper, we examine the pointing control of a spacecraft using two SGCMGs. A pointing control directs the line-of-sight of an antenna or a camera that is fixed on the spacecraft toward the desired direction. Because the total angular momentum vector of a spacecraft is conserved in the inertial frame, the angular momentum vector of a spacecraft is aligned with the angular momentum vector of the SGCMGs at a final state of rest. This imposes a restriction on the feasible orientations of the spacecraft at rest. First, we designed an LQR controller as a simpler method for a linearized system. Thereafter, we developed a nonlinear controller on the basis of the Lyapunov stability theory for large initial condition. The feasibility of the proposed controller is shown by numerical simulations.
