Abstract
DOI: 10.2514/1.53074 In this paper, a control law that detumbles a spacecraft with magnetic actuators only is developed. A rigorous mathematical proof of global asymptotic convergence from arbitrary initial tumbling conditions to zero angular velocity in a time-varying magnetic field is derived. Furthermore, a simple criterion for determining a reasonable value of the control gain is developed. The selected gain results in a quasi-minimum time detumbling for different initialconditions,inthepresenceofmagneticcoilsaturation.Performanceoftheproposeddetumblingcontrollawis demonstrated by numerical simulations on a large set of test cases using a Monte Carlo approach.
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