Abstract
Control moment gyro (CMG) generates higher torque than reaction wheel. Thus it is focused to mount CMGs on future satellites which is required to make fast maneuver. CMGs, however, have singular points. To avoid the singular points, number of CMGs is more than the degree of freedom of satellite. This paper discusses on the minimum energy maneuvers of a satellite using CMGs. The criterion is square of gimbal rate, which is equivalent to energy consumption. The numerical results show that twice of energy is required when one of CMGs malfunctions.
