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dc.contributor.authorChiaradia, Ana Paula Marins [UNESP]
dc.contributor.authorPrado, Antonio Fernando Bertachini de Almeida
dc.contributor.authorKuga, Hélio Koiti
dc.date.accessioned2014-05-27T11:27:05Z
dc.date.available2014-05-27T11:27:05Z
dc.date.issued2012-10-01
dc.identifierhttp://www.wseas.org/multimedia/journals/mechanics/2012/55-725.pdf
dc.identifier.citationWSEAS Transactions on Applied and Theoretical Mechanics, v. 7, n. 4, p. 263-275, 2012.
dc.identifier.issn1991-8747
dc.identifier.issn2224-3429
dc.identifier.urihttp://hdl.handle.net/11449/73644
dc.description.abstractIn the present paper a study is made in order to find an algorithm that can calculate coplanar orbital maneuvers for an artificial satellite. The idea is to find a method that is fast enough to be combined with onboard orbit determination using GPS data collected from a receiver that is located in the satellite. After a search in the literature, three algorithms are selected to be tested. Preliminary studies show that one of them (the so called Minimum Delta-V Lambert Problem) has several advantages over the two others, both in terms of accuracy and time required for processing. So, this algorithm is implemented and tested numerically combined with the orbit determination procedure. Some adjustments are performed in this algorithm in the present paper to allow its use in real-time onboard applications. Considering the whole maneuver, first of all a simplified and compact algorithm is used to estimate in real-time and onboard the artificial satellite orbit using the GPS measurements. By using the estimated orbit as the initial one and the information of the final desired orbit (from the specification of the mission) as the final one, a coplanar bi-impulsive maneuver is calculated. This maneuver searches for the minimum fuel consumption. Two kinds of maneuvers are performed, one varying only the semi major axis and the other varying the semi major axis and the eccentricity of the orbit, simultaneously. The possibilities of restrictions in the locations to apply the impulses are included, as well as the possibility to control the relation between the processing time and the solution accuracy. Those are the two main reasons to recommend this method for use in the proposed application.en
dc.format.extent263-275
dc.language.isoeng
dc.relation.ispartofWSEAS Transactions on Applied and Theoretical Mechanics
dc.sourceScopus
dc.subjectArtificial satellite
dc.subjectAstrodynamics
dc.subjectGPS
dc.subjectLambert problem
dc.subjectOrbital maneuver
dc.titleDetermination of onboard coplanar orbital maneuvers with orbits determined using GPSen
dc.typeArtigo
dc.contributor.institutionUniversidade Estadual Paulista (UNESP)
dc.contributor.institutionInstituto Nacional de Pesquisas Espaciais (INPE)
dc.description.affiliationGrupo de Dinâmica Orbital and Planetologia FEG-UNESP, Av. Ariberto Pereira da Cunha, 333, Guaratinguetá -SP-CEP: 12 516-410
dc.description.affiliationINPE, Av. dos Astronautas 1758, São José dos Campos -SP -CEP: 12 227-010
dc.description.affiliationUnespGrupo de Dinâmica Orbital and Planetologia FEG-UNESP, Av. Ariberto Pereira da Cunha, 333, Guaratinguetá -SP-CEP: 12 516-410
dc.rights.accessRightsAcesso aberto
dc.identifier.scopus2-s2.0-84885231186
unesp.campusUniversidade Estadual Paulista (UNESP), Faculdade de Engenharia, Guaratinguetápt
dc.identifier.lattes5651353474953307
unesp.author.lattes5651353474953307
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