This paper considers a feedback control law that achieves attitude stabilization for Earth-pointing spacecraft using only magnetorquers as torque actuators. The control law is proportional derivative (PD)-like with matrix gains, and it guarantees asymptotic stability. The PD matrix gains are determined through the numerical solution of a periodic linear quadric regulator problem. A case study shows the effectiveness of the considered control law, and specifically of the gain selection method, in a simplified simulation scenario.
Gain Selection for Attitude Stabilization of Earth-Pointing Spacecraft Using Magnetorquers
Aerotec. Missili Spaz.
Aerotecnica Missili & Spazio ; 100 , 1 ; 15-24
2021-03-01
10 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Robust three-axis attitude stabilization for inertial pointing spacecraft using magnetorquers
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