In this paper we consider the problem of controlling the orientation of a satellite with thrusters which provide two control torques. We derive open loop steering control laws for steering the satellite from one orientation to another. Then, we develop closed loop regulation control laws. For a ﲳymmetric satellite, (i.e. one with two moments of inertia equal) we stabilize a five dimensional subset of the states. The regulator for the asymmetric satellite, which is controllable, renders an arbitrary configuration asymptotically stable. A novel choice of ﲌisting coordinates for SO (3) proves to be useful in deriving these control laws.