Optimization in Choosing Gimbal Axis Orientations of a CMG Attitude Control System

Control momentum gyros (CMGs) are often chosen for satellites where high attitude precision and torque are needed while using minimal input power. Control of these types of systems is complicated and is directly dependent on the number of actuators and their gimbal axis orientations with respect to the satellite body frame. This paper discusses the potential benets of optimizing these gimbal axis congurations

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