Actuator-induced disturbances are among the most crucial factors in correct spacecraft attitude pointing and stability for fine attitude control problems. In order to develop a CMG as an actuator for fine controls, CMG-induced disturbances should be analyzed. Therefore, this paper aims to develop an analytic model that predicts the effect of disturbances to CMGs by assuming static and dynamic imbalances. The proposed analytical model with respect to the disturbances of a CMG is derived using the Lagrange energy method based on the small-signal assumption.

In this letter we provide a steering law for redundant single-gimbal control moment gyros. The proposed steering law is an extended version of the singular direction avoidance (SDA) steering law based on the singular value decomposition (SVD). All internal singularities are escapable for any non-zero constant torque command using the proposed steering law.