A new approach to the attitude control of an over actuated satellite is presented. A control moment gyroscopes cluster containing four actuators in a pyramid mounting configuration, and a set of three orthogonal magnetic torque rods are considered to steer the satellite. Two steering algorithms, Moore-Penrose pseudo inverse, and the recently developed blended-inverse, are considered. The success of the blended-inverse algorithm to select the desired actuators in the system is demonstrated. It is also shown through simulations that the blended-inverse algorithm successfully carries out the maneuver without getting trapped in singular configurations, while the classical Moore-Penrose pseudo inverse algorithm fails to realize.