Abstract Attitude control is an essential operation for spacecraft to perform space missions, and control strategies play a decisive role. In this paper, a second-order quaternion system of rigid spacecraft attitude dynamics is derived based on the fully actuated system approach. The quaternion system has two constraints that lead it to be a fully actuated system. Two closed-loop control strategies are proposed to achieve attitude tracking and stabilization for the fully actuated system. The stabilization strategy can control the scalar quaternion to reach the desired value and be used to deal with the unwinding phenomenon. Numerical simulations demonstrate the second-order quaternion system’s validity and the control strategies’ effectiveness.
Highlights A second-order quaternion system is derived from an intuitive perspective. The control laws are much easier to design than the first-order system. Arbitrary three quaternions can be employed as the controlled variables. The unwinding phenomenon is handled in a simple way.
Fully actuated systems in terms of quaternions for spacecraft attitude control
Acta Astronautica ; 209 ; 1-5
2023-04-15
5 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Fully Actuated Spacecraft Attitude Control via the Hybrid Magnetocoulombic and Magnetic Torques
Online Contents | 2017
|Fully Actuated Spacecraft Attitude Control via the Hybrid Magnetocoulombic and Magnetic Torques
Online Contents | 2017
|