Abstract

A linearized mathematical model of a three-axes stabilized symmetric satellite equipped with a magnetic bearing momentum wheel is presented. By an approximative analysis a closed form solution of the eigenvalue problem is derived which permits a quantitative assessment of bearing compliance impact on the satellite nutation. This nutational motion may become unstable due to rotor energy losses. Two various design concepts of magnetic suspension systems, i.e., passive and active magnetic bearings, are investigated for analyzing this effect. The theoretical results are verified by air bearing tests, indicating that actively controlled magnetic bearings can actually be designed to avoid the nutational instability.

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