Searching for orbits to observe the poles of celestial bodies

Página do item simplificado
dc.contributor.authorde Almeida Junior, Allan Kardec
dc.contributor.authorPrado, Antonio Fernando Bertachini de Almeida
dc.contributor.authorYokoyama, Tadashi [UNESP]
dc.contributor.authorSanchez, Diogo Merguizo
dc.contributor.institutionInstituto Nacional de Pesquisas Espaciais (INPE)
dc.contributor.institutionUniversidade Estadual Paulista (Unesp)
dc.contributor.institutionTexas A&M University
dc.date.accessioned2021-06-25T11:04:41Z
dc.date.available2021-06-25T11:04:41Z
dc.date.issued2020-11-15
dc.description.abstractThe objective of the present paper is to show a method to find orbits near artificial equilibrium points for a satellite equipped with a continuous thrust that allows it to stay near the poles of a celestial body. The physical system includes the presence of a moon of the celestial body under observation, and the perturbation caused by this moon is counteracted by an algorithm to help the satellite to stay close to its original position, instead of escape from it. The equations of motion are changed under some approximations, and analytical solutions for these equations are obtained and analyzed. Initial conditions are used such that their secular terms are nullified. These solutions are restricted to a short period of time, but we propose a method in which there are periodic updates in the thrust. Thus, the solutions can be extended for the duration of the mission. A numerical simulation is obtained, whose results are required to be in agreement with the analytical solution using these periodic adjustments of the thrust. This agreement means that the motion of the spacecraft remains bounded close to its initial position for longer times. Several systems with different sizes and mass parameters are used to show the results of the research, like Sun-Earth-Moon, Sun-Ida-Dactyl, Sun-Saturn-Titan and Sun-Mars-Phobos systems. The results also indicate the locations of points that require minimum magnitude of the thrust.en
dc.description.affiliationInstituto Nacional de Pesquisas Espaciais (INPE)
dc.description.affiliationUNESP Universidade Estadual Paulista
dc.description.affiliationAerospace Engineering Texas A&M University
dc.description.affiliationUnespUNESP Universidade Estadual Paulista
dc.description.sponsorshipCoordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES)
dc.description.sponsorshipFundação de Amparo à Pesquisa do Estado de São Paulo (FAPESP)
dc.description.sponsorshipConselho Nacional de Desenvolvimento Científico e Tecnológico (CNPq)
dc.description.sponsorshipIdFAPESP: 2014/22295-5
dc.description.sponsorshipIdFAPESP: 2016/24561-0
dc.description.sponsorshipIdFAPESP: 2018/07377-6
dc.description.sponsorshipIdFAPESP: 2019/18480-5
dc.description.sponsorshipIdCNPq: 301338/2016-7
dc.description.sponsorshipIdCNPq: 309190/2017-7
dc.description.sponsorshipIdCNPq: 406841/2016-0
dc.format.extent2378-2401
dc.identifierhttp://dx.doi.org/10.1016/j.asr.2020.07.043
dc.identifier.citationAdvances in Space Research, v. 66, n. 10, p. 2378-2401, 2020.
dc.identifier.doi10.1016/j.asr.2020.07.043
dc.identifier.issn1879-1948
dc.identifier.issn0273-1177
dc.identifier.scopus2-s2.0-85091710779
dc.identifier.urihttp://hdl.handle.net/11449/208003
dc.language.isoeng
dc.relation.ispartofAdvances in Space Research
dc.sourceScopus
dc.subjectArtificial equilibrium points
dc.subjectAstrodynamics
dc.subjectNonlinear systems
dc.subjectRestricted three-body problem
dc.titleSearching for orbits to observe the poles of celestial bodiesen
dc.typeArtigo

Arquivos

Coleções

Artigos - Estatistica, Matemática Aplicada e Computação - IGCE