Spin-axis pointing of a magnetically actuated spacecraft

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• 作者：G. Avanzini ; E.L. de Angelis ; F. Giulietti
• 关键词：Attitude control ; Non-linear control ; Spacecraft magnetic control ; Single-axis pointing
• 刊名：Acta Astronautica
• 出版年：2014
• 出版时间：January-February, 2014
• 年：2014
• 卷：94
• 期：1
• 页码：493-501
• 全文大小：577 K

文摘

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.