Abstract
Control moment gyro (CMG) generates higher torque than common reaction wheel. Thus it is focused on mounting CMGs on future satellites for agile maneuver. The authors are studying on optimal maneuver of satellites actuated by CMGs as application of optimal control theory. This paper discusses on the minimum energy. The criterion of problem is square of gimbal rate, which is equivalent of energy consumption. The numerical results show that energy consumption increases when one of CMGs is malfunctioned. The ratio is almost five times in the worst case.
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