Satellite Controller System Based on Reaction Wheels Using the State-Dependent Riccati Equation (SDRE) on Java

Romero, Alessandro Gerlinger; Souza, Luiz Carlos Gadelha de

doi:10.1007/978-3-319-99268-6_38

Cited by 5 publications

(5 citation statements)

References 11 publications

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“…Such executions used simulation time 200 s, fixed step 0.005 s, the data presented in Table 1 and the following controllers: (1) PID controller [K p ¼ 1, K pd ¼ diagð−24; −26; −32Þ, K pi ¼ 0] defined by Eqs. (16) and (17); and (2) SDRE controller (R ¼ 1 and Q ¼ 1) defined by Eqs. (19) and (3).…”

Section: Simulation Resultsmentioning

confidence: 99%

“…To the best of our knowledge, the proof of concept of the open-source satellite simulator for SDRE controllers is original. 17,18,21 Moreover, the simulator can run in a variety of platformsincluding an Android operating system in a remote sensing CubeSat-and it has low cost. It is worth mentioning that 39.33% of the cost of CONASAT was selected for the acquisition of software license (page 12, Ref.…”

Section: Resultsmentioning

confidence: 99%

“…At INPE, a typical controller for the LEOP is shown in Eq. (17), in which the Sun pointing error is s pe ¼ arccosŝ b1 regarding the reference in Table 1. Þ;s be ¼ ½0 −ŝ b3ŝb2 T ;ω e ¼ω −ω r : (17) Note that this type of controller neither has difficulties in its simulation nor in its numerical real-time implementation.…”

Section: Linear Control Based On Proportional-integral-derivative Conmentioning

confidence: 99%

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State-dependent Riccati equation controller using Java in remote sensing CubeSats

Romero

Souza

2019

J. Appl. Rem. Sens.

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STRaND and PhoneSat programs have attracted the attention of the aerospace community by applying, in CubeSats, commercial off-the-shelf smartphones based on Google's Android. In Android, the development commonly applies Java hence this language is a natural candidate for the attitude and orbit control subsystem (AOCS). Moreover, such AOCS can be designed with success by linear control theory; however, the linearized models are not able to represent all the effects of the nonlinear terms present in the dynamics. Therefore, nonlinear control techniques can yield better performance. An example is the Nano-Satellite Constellation for Environmental Data Collection, used as the reference in this work, a set of remote sensing CubeSats from the Brazilian National Institute for Space Research, in which the AOCS must stabilize the satellite in three-axes. We present the investigation of a state-dependent Riccati equation (SDRE) controller, a nonlinear controller, based on attitude errors given by quaternions. The investigation uses Java, accordingly, it can run on an Android operating system in a CubeSat, and it has low cost. Two controllers (linear and SDRE) were evaluated using a Monte Carlo perturbation model. The initial results show that the SDRE controller provides better performance.

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Section: Simulation Resultsmentioning

confidence: 99%

Section: Resultsmentioning

confidence: 99%

Section: Linear Control Based On Proportional-integral-derivative Conmentioning

confidence: 99%

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State-dependent Riccati equation controller using Java in remote sensing CubeSats

Romero

Souza

2019

J. Appl. Rem. Sens.

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“…The attitude control of spacecraft using nonlinear control feedback linearization was discussed in [16]. In another study, the system model in a form known as state-dependent coefficient matrices was considered [17]. The author avoided using the approximate linearized equations of SACS dynamics, instead representing the nonlinear equations of SACS dynamics as a linear system of differential equations, where the matrix elements are functions of the state vector of the system rather than the constants.…”

Section: Introductionmentioning

confidence: 99%

“…The equations were obtained for a special choice of variables for the state vector of the SACS. Based on the angular momentum conservation theorem for a closed mechanical system in the inertial frame [19,20], the original system of nonlinear equations of the SACS dynamics was presented in the form of a system of linear differential equations, where the matrix elements were functions of time, unlike the linear models proposed in [16,17]. The dependence of the matrix elements of a linear system on time does not limit the equivalence of the linear model to the local area of the considered state of the system, extending it to the whole area of determination of the original nonlinear model.…”

Section: Introductionmentioning

confidence: 99%

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

Moldabekov,

Sukhenko,

Orazaly

et al. 2023

Mathematics

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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.

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Attitude control of an underactuated satellite in presence of disturbance torque with optimal motion planning

Zinjanabi

Pishkenari

Salarieh

et al. 2022

Aerospace Science and Technology

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Satellite Controller System Based on Reaction Wheels Using the State-Dependent Riccati Equation (SDRE) on Java

Cited by 5 publications

References 11 publications

State-dependent Riccati equation controller using Java in remote sensing CubeSats

State-dependent Riccati equation controller using Java in remote sensing CubeSats

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

Attitude control of an underactuated satellite in presence of disturbance torque with optimal motion planning

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