Abstract
In this paper, the analysis, design, implementation and testing of an accurate satellite attitude control system is presented. The control system function is to provide three axis inertial stabilization and accurate earth pointing automatically, over a period of 5 years or more. Of primary concern in the design of the overall control system was the minimization of compensation complexity and control logic without compromising the stabilization requirements and pointing accuracy of the system. In addition to fulfilling the above requirements, the design presented here provides exceptional capability for including nonredundant multi-mode operation; thereby providing additional reliability and highly versatile performance for a wide range of satellite and experiment pointing requirements. The design logic, fabrication problems, and a computeraided design optimization method are described in this paper. Both the theoretically predicted and numerically simulated performance was verified by testing the implemented control system on a spherical air bearing platform and comparing several sets of attitude response data. In addition to the primary control modes, other operating modes are briefly described such as the initial acquisition mode, and a coarse back-up mode that uses thrusters to provide the control torque.
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