Stabilization of Regular Satellite Precessions Using Lorentz Force Moments

The stabilization of regular precessions of a satellite in a circular orbit is considered using control moments determined by Lorentzian forces. The linearized system of equations of motion belongs to a special class of linear time-varying systems that can be reduced to time-invariant ones. Controllability was studied both for the original time-varying systems and on the basis of the reduced time-invariant systems. Optimal stabilization algorithms have been constructed. Mathematical modeling of the proposed algorithms was carried out, confirming the performance and effectiveness of the proposed methodology.