Spin-axis pointing of a magnetically actuated spacecraft

You are here: Homepage > Search

Spin-axis pointing of a magnetically actuated spacecraft

Avanzini, G. / de Angelis, E.L. / Giulietti, F.

Abstract 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.

Highlights ► Magnetic control provides higher reliability and lower energy consumption at the cost of under-actuation. ► A proof of asymptotic stability for a prescribed pure spin condition is derived. ► The control law performs the feedback of two different angular momentum error signals. ► The spin axis is aligned with a desired direction in spite of inherent under-actuation. ► Monte Carlo simulation is used for determining optimal values of control law gains.