Abstract
The task of developing a microsatellite orientation control system using rotation wheels with limited control moments is under consideration. For the synthesis of control laws by the method of analytical construction of optimal regulators by minimization of the integral-quadratic functional, the dynamic equations of the rotational motion of the satellite are linearized. The governing bodies of the satellite are three rotation wheels and magnetic coils. Algorithms for controlling the satellite during stabilization, turning and stabilization of the angular position have been developed. Algorithms are tuned depending on the parameters of the satellite and ensure its stable movement in all modes. Considered examples of simulation the satellite movement using full nonlinear models, which showed the effectiveness and universality of the algorithms. The effectiveness of control algorithms for the use of the rotation wheels and magnetic coils is compared.
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