Dynamics Analysis of a Nonlinear Satellite Attitude Control System Using an Exact Linear Model

Meirbek Moldabekov, Anna Sukhenko, Yerkin Orazaly () and Alisher Aden
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Meirbek Moldabekov: AALR “Institute of Space Technique and Technology”, Almaty 050010, Kazakhstan
Anna Sukhenko: AALR “Institute of Space Technique and Technology”, Almaty 050010, Kazakhstan
Yerkin Orazaly: Institute of Telecommunications and Space Engineering, Almaty University of Power Engineering and Telecommunications Named after Gumarbek Daukeyev, Almaty 050013, Kazakhstan
Alisher Aden: Institute of Telecommunications and Space Engineering, Almaty University of Power Engineering and Telecommunications Named after Gumarbek Daukeyev, Almaty 050013, Kazakhstan

Mathematics, 2023, vol. 11, issue 12, 1-15

Abstract: This study aims to analyze the nonlinear dynamics of a satellite attitude control system equipped with reaction wheels and a PD controller. Based on the angular momentum conservation theorem for a closed mechanical system, the nonlinear equations of the attitude control system dynamics are presented as a linear system of differential equations with time-varying parameters. The asymptotic properties of the angular momentum of a mechanical system including a satellite and reaction wheels as rigid bodies are investigated. A relation has been established between the dynamic parameters of the attitude control system and the initial value of the angular momentum of the satellite. The issue of asymptotic stability for differential equations with time-varying parameters is simplified to the asymptotic stability problem for the ultimate homogeneous system of linear differential equations with constant elements. The dependencies of the dynamic parameters of the attitude control system on the constant parameters of this ultimate system of linear differential equations, as well as the initial values of the satellite’s angular momentum, enable us to apply proven and effective engineering methods. These methods are used not only for analyzing the stability of the control system but also for synthesizing the parameters of the control law based on the quality requirements of transient processes such as the stability margin, responsiveness, oscillation, transient time, and overshoot. In this case, the calculation of the control law parameters will be grounded in exact equations, not on approximate equations of the control system dynamics obtained by linearization.

Keywords: satellite; attitude control system; dynamics; kinematics; asymptotic stability (search for similar items in EconPapers)
JEL-codes: C (search for similar items in EconPapers)
Date: 2023
References: View complete reference list from CitEc
Citations: View citations in EconPapers (1)

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