A high precision attitude determination and control system for the UYS-1 nanosatellite

Chaurais, Jefferson R.; Ferreira, Henrique C.; Ishihara, J.Y.; Borges, Renato Alves; Kulabukhov, Anatoliy Mikhaylovich; Larin, Vladimir A.; Belikov, Vladimir V.

doi:10.1109/aero.2013.6496981

Cited by 6 publications

(5 citation statements)

References 17 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The main central moments of inertia for the satellite [25] are I S1 = I S2 =0.1521 kg • m 2 and I S3 =0.0375 kg • m 2 , while the moments of inertia for the reaction wheels are…”

Section: Numerical Examplementioning

confidence: 99%

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

Moldabekov,

Sukhenko,

Orazaly

et al. 2023

Mathematics

View full text Add to dashboard Cite

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.

show abstract

“…The main central moments of inertia for the satellite [25] are I S1 = I S2 =0.1521 kg • m 2 and I S3 =0.0375 kg • m 2 , while the moments of inertia for the reaction wheels are…”

Section: Numerical Examplementioning

confidence: 99%

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

Moldabekov,

Sukhenko,

Orazaly

et al. 2023

Mathematics

View full text Add to dashboard Cite

show abstract

“…For numerical simulation of transient processes on the basis of solving nonlinear equations (3.2), taking into account synthesis of the control law parameters according to the method in Section 5, we assume that the satellite moments of inertia are equal to J 1 = J 2 = 0.1521 kg m 2 , J 3 = 0.0375 kg m 2 (Chaurais et al, 2013), the initial values of the angular position are φ 1 (t 0 ) = φ 2 (t 0 ) = φ 3 (t 0 ) = 45 • , the initial angular velocities of the satellite and reaction wheels are equal to zero, the transient time is set equal to the transient time 20 s in Chaurais et al (2013), where the parameters of the PD controller are determined empirically. In this article, the parameters of the control law are determined according to the method in Section 5 and, In comparison with the simulation results given in the work of Chaurais et al (2013), the transient processes are monotonic without oscillation, the final time of the transient process is practically the same for all three angles, which indicates high efficiency of the proposed method for synthesizing the control law parameters.…”

Section: Numerical Studiesmentioning

confidence: 99%

“…As a rule, the control law of the satellite attitude control system is based on the PD-regulator (Moldabekov et al, 2015;Chaurais et al, 2013;Narkiewicz et al, 2020;Mehrjardi et al, 2014;Ran et al, 2016;Nasrolahi and Abdollahi, 2016) and the dynamics of the satellite attitude control system is described by nonlinear differential equations. The interest arises for the question of whether it is possible to represent the dynamical equations of the satellite attitude control system in the linear form.…”

Section: Introductionmentioning

confidence: 99%

The use of the linear form of dynamical equations of the satellite attitude control system for its analysis and synthesis

Moldabekov¹,

Sukhenko²,

Shapovalova³

et al. 2020

Journal of Theoretical and Applied Mechanics

View full text Add to dashboard Cite

At present, the methods based on using linearized dynamical equations are applied for synthesis of an attitude control system of a satellite with nonlinear dynamics. Linearized equations describe the satellite dynamics approximately, which is the main their disadvantage. This article shows that basing on the angular momentum theorem, the nonlinear dynamical equations of the satellite attitude control system can be represented in the form of linear differential equations with variable coefficients, which makes it possible to use engineering methods of stability analysis and analysis of transient quality in the process of synthesis of the satellite attitude control system.

show abstract

“…Consider the inertia matrix of the UYS-1 nanosatellite [9] given by I diag0.1521; 0.1521; 0.0375 kg · m 2 and the following parameters adjusted by simulations: a 1 0.2, a 2 0.2, k 0.9, g 3, K diag10; 10; 0, and maximum torque u MAX 0.002 N · m. Also consider the sampling time Δt 0.01 s and the initial conditions of the attitude q 1 0 q 2 0 q 3 0 0.2236, q 4 0 0.9220, and angular velocity ω0 0.…”

Section: Simulationsmentioning

confidence: 99%

“…Section IV presents the proposed controller and its stability analysis. Section V shows the simulations and a comparison between the new and the singular nonlinear controllers applied in a Ukrainian nanosatellite UYS-1 [9]. Finally, Sec.…”

Section: Introductionmentioning

confidence: 99%

Attitude Control of an Underactuated Satellite Using Two Reaction Wheels

Chaurais

Ferreira

Ishihara

et al. 2015

Journal of Guidance, Control, and Dynamics

View full text Add to dashboard Cite

A high precision attitude determination and control system for the UYS-1 nanosatellite

Cited by 6 publications

References 17 publications

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

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

The use of the linear form of dynamical equations of the satellite attitude control system for its analysis and synthesis

Attitude Control of an Underactuated Satellite Using Two Reaction Wheels

Contact Info

Product

Resources

About