The use of magnetic actuators on Low Earth Orbiting spacecrafts represents an attractive solution because of its simplicity, reliability and a power-effective smooth modulation of control actions. Attitude regulation yet proves to be a challenging problem, since magnetic actuators alone do not allow providing three independent control torque components at each time instant. The goal of this paper is to derive a rigorous proof of global asymptotic stability for a magnetic control law that leads the satellite to a desired spin condition around a principal axis of inertia, pointing the spin axis towards a target direction in the inertial reference frame.

Single-Axis Pointing of a Magnetically Actuated Spacecraft

DE ANGELIS, EMANUELE LUIGI;GIULIETTI, FABRIZIO
2012

Abstract

The use of magnetic actuators on Low Earth Orbiting spacecrafts represents an attractive solution because of its simplicity, reliability and a power-effective smooth modulation of control actions. Attitude regulation yet proves to be a challenging problem, since magnetic actuators alone do not allow providing three independent control torque components at each time instant. The goal of this paper is to derive a rigorous proof of global asymptotic stability for a magnetic control law that leads the satellite to a desired spin condition around a principal axis of inertia, pointing the spin axis towards a target direction in the inertial reference frame.
2012
Advances in the Astronautical Sciences
241
258
G. Avanzini; E.L. de Angelis; F. Giulietti
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11585/129059
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