Abstract
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.
Highlights
Spacecraft attitude control can be obtained by adopting several actuation mechanisms
They consist of planar current-driven coils rigidly placed on the spacecraft typically along three orthogonal axes, and they operate on the basis of the interaction between the magnetic dipole moment generated by those coils and the Earth magnetic field
This work studies the problem of attitude stabilization of an Earth-pointing spacecraft using only magnetorquers
Summary
Spacecraft attitude control can be obtained by adopting several actuation mechanisms. Among them electromagnetic actuators are widely used for generation of attitude control torques on satellites flying in low Earth orbits. They consist of planar current-driven coils rigidly placed on the spacecraft typically along three orthogonal axes, and they operate on the basis of the interaction between the magnetic dipole moment generated by those coils and the Earth magnetic field. Known as magnetorquers, have the important limitation that control torque is constrained to belong to the plane orthogonal to the Earth magnetic field. Attitude stabilization of an Earthpointing spacecraft using only magnetorquers is considered, and a stabilizing PD-like control law is applied. The proposed approach is more promising than those in [8, 17]
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