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The optimal controllers for the management of 3-axis reaction-wheel momentum of rigid Earth-pointing satellites are analyzed in detail using magnetorquers and/or thrusters. Especially, two novel, optimal combined control schemes are proposed in order to achieve rapid, propellant-saving reaction wheel momentum dumping control by employing magnetorquers and thrusters. Finally, simulation results are presented to demonstrate the superiority of these algorithms. These two combined algorithms could easily be applied in real-time onboard an LEO Earth-pointing satellite. I.
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Chen et al. (1999) studied this question.
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