Article ID: | iaor2014967 |
Volume: | 94 |
Issue: | 1 |
Start Page Number: | 493 |
End Page Number: | 501 |
Publication Date: | Jan 2014 |
Journal: | Acta Astronautica |
Authors: | Avanzini G, de Angelis E L, Giulietti F |
Keywords: | optimization |
Attitude regulation proves to be a challenging problem, when magnetic actuators alone are used as attitude effectors, since they do not provide three independent control torque components at each time instant. In this paper a rigorous proof of global exponential stability is derived for a magnetic control law that leads the satellite to a desired spin condition around a principal axis of inertia, pointing the spin axis toward a prescribed direction in the inertial frame. The technique is demonstrated by means of numerical simulation of a few example maneuvers. An extensive Monte Carlo simulation is performed for random initial conditions, in order to investigate the effect of changes in control law gains.