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) is inherently underactuated if no other attitude effector is available. In this paper a rigorous proof of global asymptotic stability is derived for a control law that leads the satellite to a desired pure spin condition around a principal axis of inertia. A heuristic contribution is then added, inspired by quaternion feedback control and a previous geometric result obtained by the authors, which allows for pointing the spin axis along the normal to the orbital plane
Single-axis pointing of a magnetically actuated spacecraft: a non-nominal Euler axis approach / G. Avanzini; E.L. de Angelis; F.giulietti. - ELETTRONICO. - (2011), pp. 1227-1246.
Single-axis pointing of a magnetically actuated spacecraft: a non-nominal Euler axis approach
DE ANGELIS, EMANUELE LUIGI;GIULIETTI, FABRIZIO
2011
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) is inherently underactuated if no other attitude effector is available. In this paper a rigorous proof of global asymptotic stability is derived for a control law that leads the satellite to a desired pure spin condition around a principal axis of inertia. A heuristic contribution is then added, inspired by quaternion feedback control and a previous geometric result obtained by the authors, which allows for pointing the spin axis along the normal to the orbital planeI documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
