| Summary: | Approved for public release; distribution is unlimited. === This thesis develops a suite of automated techniques aimed at analyzing the characteristics of arrays of control moment gyroscopes (CMGs) and/or reaction wheels (RWs). Three specific areas, relevant to the design of new spacecraft, are examined: momentum space, torque space, and reaction forces. The momentum space analysis creates a maximum saturation envelope for both pure CMG/RW arrays and for hybrid arrays. The torque space analysis creates a maximum envelope for RWs and presents the idea of state-space analysis for CMGs, which leads to the ability to determine singularity free operational envelopes. These envelopes allow satellite slew performance to be estimated, allowing for an initial determination of component size. The reaction forces and moments seen at the attachment points of the RWs and CMGs during maneuvers is also analyzed. This analysis, which has not been reported in the literature, utilizes telemetry data and the geometry of the spacecraft to explore the relationship between maneuver types and the loads seen by the CMG/RW mechanism.
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