The use of magnetic torquers on satellites flying inclined Low Earth Orbits (LEO) arises challenging problems when dealing with control strategies: since the available torque is perpendicular to the local magnetic field, the Attitude Control System (ACS) results to be inherently underactuated. In this paper a rigorous proof of global asymptotic stability is given about a control law that leads the satellite to a desired pure spin condition around a principal axis of inertia. Besides, a heuristic control contribution to this law, inspired by quaternion feedback control and a geometric result by Avanzini and Giulietti is proposed in order to point the spinning axis along the normal to the orbital plane.
Single-Axis Pointing of a Magnetically Actuated Spacecraft: a Non-Nominal Euler-Axis Approach
AVANZINI, Giulio;
2011-01-01
Abstract
The use of magnetic torquers on satellites flying inclined Low Earth Orbits (LEO) arises challenging problems when dealing with control strategies: since the available torque is perpendicular to the local magnetic field, the Attitude Control System (ACS) results to be inherently underactuated. In this paper a rigorous proof of global asymptotic stability is given about a control law that leads the satellite to a desired pure spin condition around a principal axis of inertia. Besides, a heuristic control contribution to this law, inspired by quaternion feedback control and a geometric result by Avanzini and Giulietti is proposed in order to point the spinning axis along the normal to the orbital plane.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
