Spin-axis pointing of a magnetically actuated spacecraft

Spin-axis pointing of a magnetically actuated spacecraft

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Article ID: iaor2014967
Volume: 94
Issue: 1
Start Page Number: 493
End Page Number: 501
Publication Date: Jan 2014
Journal: Acta Astronautica
Authors: , ,
Keywords: optimization
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.

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