Survey of Reaction Control Systems for Synchronous Satellites

The analysis performed in the selection of a reaction control system for a spinning synchronous satellite is presented. A 2000 lb satellite is chosen as an illustrative example and the detailed steps followed in defining a tradeoff study leading to the selection of a preferred propulsion system are described. A “genesis” of the propulsion systems' requirements is presented, followed by a definition of those criteria used in the selection of the optimum reaction control system.