Rao-Blackwellized Particle Filter for the CBERS-4 attitude and gyros bias estimation

Página do item simplificado
dc.contributor.authorSilva, W. R.
dc.contributor.authorGarcia, R. V.
dc.contributor.authorSantilli, G.
dc.contributor.authorKuga, H. K.
dc.contributor.authorZanardi, M. C.F.P.S. [UNESP]
dc.contributor.authorPardal, P. C.P.M.
dc.contributor.institutionSetor Leste (Gama)
dc.contributor.institutionUniversidade de São Paulo (USP)
dc.contributor.institutionSpace Mechanics and Control Division (DMC)
dc.contributor.institutionUniversidade Estadual Paulista (UNESP)
dc.date.accessioned2022-04-28T19:43:35Z
dc.date.available2022-04-28T19:43:35Z
dc.date.issued2022-04-01
dc.description.abstractThe Rao-Blackwellized Particle Filter (RaoBPF) and the Unscented Kalman Filter (UKF) were applied in this work to attitude and gyros bias estimation using simulated orbit and attitude measurement data for CBERS-4 (China Brazil Earth Resources Satellite 4) recently in operation. CBERS-4 was launched in 2014, controlled and operated in shifts by China (Xi'an Control Center) and Brazil (Satellite Control Center). Its orbit is heliosynchronous with an inclination of 98.504 degrees, a semi-major axis of 7148.865 km, eccentricity 1.1×10−3, crossing equador line at 10h30min in a descending direction with perigee frozen at 90 degrees, which establishes a commitment relationship between a satisfactory amount of solar irradiance, contrast between targets, and the presence of clouds. This configuration provides global coverage every 26 days. The real orbit and attitude measurements were provided by the Satellite Control Center of the National Institute for Space Research (CCS - INPE) from September 1st, 2015. The dynamic attitude model is described by quaternions. The available attitude sensors are two Digital Sun Sensors (DSS), two Infrared Earth Sensor (IRES) and a triad of mechanical gyroscopes. The two IRES give direct measurements of roll and pitch angles with a certain level of error. The two DSS are nonlinear functions of roll, pitch, and yaw attitude angles. The gyros furnish the angular measurements in the body frame reference system. Gyros provide direct incremental angles or angular velocities; however, they present several sources of error, and the drift is the most troublesome. Such drifts yield along time an accumulation of errors which must be accounted in the attitude determination process. The RaoBPF estimation method used to attitude and gyros bias estimation is a technique that exploits the state space structure in order to reduce the number of particles, decreasing the processing time, avoiding the computational effort common to the standard particle filter. The logical extension of the RaoBPF provides a more general model that can be divided into purely non-linear and conditionally linear-Gaussian aspects, which explores this structure, marginalizing the conditional linear parts and estimating them using exact filters, such as the Extended Kalman Filter (EKF). The results show that it is possible to achieve precision in determining attitudes within the prescribed requirements using the RaoBPF, with lower computational cost when compared to the standard particle filter and its branches, in addition to have competitive results such as the UKF.en
dc.description.affiliationUniversity of Brasilia (UnB) Gama Campus (FGA) Área Especial de Indústria Projeção A Setor Leste (Gama), DF
dc.description.affiliationUniversity of São Paulo (USP) Lorena School of Engineering (EEL) Estrada Municipal do Campinho, S/N. Ponte Nova, SP
dc.description.affiliationNational Institute for Space Research (INPE) Space Mechanics and Control Division (DMC), Avenida dos Astronautas, 1758, Jardim da Granja, SP
dc.description.affiliationSão Paulo State University (UNESP) Campus Guaratinguetá, Av. Dr. Ariberto Pereira da Cunha, 333, Pedregulho, SP
dc.description.affiliationUnespSão Paulo State University (UNESP) Campus Guaratinguetá, Av. Dr. Ariberto Pereira da Cunha, 333, Pedregulho, SP
dc.description.sponsorshipConselho Nacional de Desenvolvimento Científico e Tecnológico (CNPq)
dc.description.sponsorshipIdCNPq: 307255/2018-2
dc.description.sponsorshipIdCNPq: 405468/2016-4
dc.description.sponsorshipIdCNPq: 407296/2016-6
dc.description.sponsorshipIdCNPq: 421672/2016-1
dc.format.extent679-690
dc.identifierhttp://dx.doi.org/10.1016/j.actaastro.2021.07.049
dc.identifier.citationActa Astronautica, v. 193, p. 679-690.
dc.identifier.doi10.1016/j.actaastro.2021.07.049
dc.identifier.issn0094-5765
dc.identifier.scopus2-s2.0-85113171588
dc.identifier.urihttp://hdl.handle.net/11449/222251
dc.language.isoeng
dc.relation.ispartofActa Astronautica
dc.sourceScopus
dc.subjectArtificial satellites
dc.subjectAttitude estimation
dc.subjectCBERS-4
dc.subjectGyros bias
dc.subjectRao-Blackwellized Particle Filter
dc.subjectUnscented Kalman Filter
dc.titleRao-Blackwellized Particle Filter for the CBERS-4 attitude and gyros bias estimationen
dc.typeArtigo
unesp.author.orcid0000-0002-4843-0267[1]
unesp.author.orcid0000-0002-0259-0724[4]
unesp.author.orcid0000-0003-1046-6587[6]

Arquivos

Coleções

Artigos