Non-Linear Control Strategies for Attitude Maneuvers in a CubeSat with Three Reaction Wheel

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dc.contributor.advisor Yanyachi Aco-Cardenas, Pablo Raul
dc.contributor.advisor Yanyachi Nina, Ayrton Martin
dc.contributor.author Espinoza Garcia, Brayan Antonio
dc.date.accessioned 2021-08-05T05:40:10Z
dc.date.available 2021-08-05T05:40:10Z
dc.date.issued 2021
dc.identifier.uri http://hdl.handle.net/20.500.12773/12641
dc.description.abstract Development of nanosatellites with CubeSat stan-dard allow students and professionals to get involved into the aerospace technology. In nanosatellites, attitude plays an im-portant role since they can be affected by various disturbances such as gravity gradient and solar radiation. These disturbances generate a torque in the system that must be corrected in order to maintain the CubeSat behavior. In this article, the kinematic and dynamic equations applied to a CubeSat with three reaction wheels are presented. In order to provide a solution to the atti-tude maneuvering problem, three robust control laws developed by Boskovic, Dando, and Chen are presented and evaluated. Furthermore, these laws are compared with a feedback control law developed by Schaub and modified to use Quaternions. The simulated system was subjected to disturbances caused by a Gravity Gradient Torque and misalignments in the reaction wheels. The effectiveness of each law is determined using the Average of Square of the Commanded Control Torque (ASCCT), the Error Euler Angle Integration (EULERINT), the settlement time, the estimated computational cost (O), and the steady-state error (ess). es_PE
dc.format application/pdf es_PE
dc.language.iso spa es_PE
dc.publisher Universidad Nacional de San Agustín de Arequipa es_PE
dc.rights info:eu-repo/semantics/openAccess es_PE
dc.rights.uri http://creativecommons.org/licenses/by-nc-nd/4.0/ es_PE
dc.source Universidad Nacional de San Agustín de Arequipa es_PE
dc.source Repositorio Institucional - UNSA es_PE
dc.subject comparison es_PE
dc.subject reaction wheels es_PE
dc.subject Quaternions es_PE
dc.subject CubeSat es_PE
dc.subject feedback control es_PE
dc.subject adaptive control es_PE
dc.subject attitude maneuvers es_PE
dc.subject Attitude control es_PE
dc.title Non-Linear Control Strategies for Attitude Maneuvers in a CubeSat with Three Reaction Wheel es_PE
dc.type info:eu-repo/semantics/bachelorThesis es_PE
thesis.degree.name Ingeniero Electrónico es_PE
thesis.degree.grantor Universidad Nacional de San Agustín de Arequipa.Facultad de Ingeniería de Producción y Servicios es_PE
thesis.degree.discipline Ingeniería Electrónica es_PE
dc.subject.ocde https://purl.org/pe-repo/ocde/ford#2.02.02 es_PE
renati.advisor.dni 29536160
renati.advisor.dni 71711125
renati.advisor.orcid https://orcid.org/0000-0001-5398-1461 es_PE
renati.advisor.orcid https://orcid.org/0000-0003-1004-1378 es_PE
renati.author.dni 70175457
renati.discipline 712026 es_PE
renati.juror Echaiz Espinoza, German Alberto
renati.juror Yanyachi Aco-Cardenas, Pablo Raul
renati.juror Salazar Alarcon, Oscar Edmundo
renati.level http://purl.org/pe-repo/renati/level#tituloProfesional es_PE
renati.type http://purl.org/pe-repo/renati/type#tesis es_PE
dc.publisher.country PE es_PE


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