Momentum Envelope Design for Roof-Array Control Moment Gyroscope Arrays

This paper proposes a momentum envelope design strategy for a satellite equipped with control moment gyroscopes (CMGs). The objective is to improve spacecraft maneuverability while preserving singularity-free operation of a roof-array CMG assembly. To this end, the three-axis angular momentum components are optimally redistributed according to a prescribed eigen-axis maneuver condition so that the achievable rotational speed is maximized within the feasible angular momentum region. The optimization problem is formulated analytically and solved with a low-complexity numerical procedure. Numerical examples show that the proposed method improves the achievable rotational speed compared with the previous fixed-envelope design approach, while additional attitude control simulations confirm that the designed envelope avoids near-singular operation. The proposed method therefore provides a maneuver-dependent extension of the previous singularity-free momentum envelope design framework.