Attitude Stabilization of a Satellite Having Only Electromagnetic Actuation Using Oscillating Controls

We consider the problem of attitude stabilization for a low Earth orbit satellite having only electromagnetic actuation. Such is not fully actuated, as control torque cross-product magnetic moment due to magnetorquers and geomagnetic field. The aim this work study whether oscillating controls can be designed such that actuated via alone achieve full three-axis irrespective position satellite. To end, we propose considering feedback which generate motion closed-loop system in direction appropriate Lie brackets. Simulation studies show proposed scheme able stabilize considered system.