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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.

Pointing Control of Spacecraft Using Two Single-Gimbal Control Moment Gyros