I. Introduction
Attitude control systems are necessary for satellites in order to complete earth or astronomical observations missions. Most of the time, reaction and momentum wheels (dc brushless motors) are used to perform the attitude control of satellites. Despite significant improvements on electronic parts, they have many drawbacks, directly linked to their ball bearings [1]. To overcome this situation, that means using no moving solid component, a solution consists in using a conductive liquid accelerated by the Lorentz force because of transverse electric and magnetic fields. A magnetohydrodynamic (MHD) reaction wheel has been studied using a dynamic lumped parameter model based on a 1-D steady-state analytical model [2].