Influence of apophis’ spin axis variations on a spacecraft during the 2029 close approach with earth

Registro completo de metadados
MetadadosDescriçãoIdioma
Autor(es): dc.contributorINPE-
Autor(es): dc.contributorUPMC Univ Paris 06-
Autor(es): dc.contributorUniversidade Estadual Paulista (UNESP)-
Autor(es): dc.creatorAljbaae, Safwan-
Autor(es): dc.creatorSouchay, Jean-
Autor(es): dc.creatorCarruba, Valerio-
Autor(es): dc.creatorSanchez, Diogo M.-
Autor(es): dc.creatorPrado, Antonio F. B. A.-
Data de aceite: dc.date.accessioned2025-08-21T21:16:31Z-
Data de disponibilização: dc.date.available2025-08-21T21:16:31Z-
Data de envio: dc.date.issued2022-11-29-
Data de envio: dc.date.issued2022-11-29-
Data de envio: dc.date.issued2020-12-31-
Fonte completa do material: dc.identifierhttp://hdl.handle.net/11449/237933-
Fonte: dc.identifier.urihttp://educapes.capes.gov.br/handle/11449/237933-
Descrição: dc.descriptionTumbling asteroids belong to a group of objects, whose angular velocity vector is unaligned with any of its principal axes of inertia. This rotation state leads to challenges when modelling a spacecraft's orbit around these bodies. In this work, we refine a previous study on this topic, concerning asteroid (99942) Apophis during its close encounter with the Earth in 2029. We analyze the orbital behaviour of a spacecraft orbiting the asteroid during this event by including the effects of the changes of orientation of the spin axis of the asteroid, depending on two sets of initial conditions. We analyze the global dynamics of the spacecraft around the target using three approaches, MEGNO, PMap, and Time-Series prediction. We limited our work on the equatorial plan choosing critical initial conditions of the span orientation of the target. We confirm that no spacecraft with natural orbits (orbits without control) could survive the high perturbations caused by the close encounter with our planet.-
Descrição: dc.descriptionCoordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES)-
Descrição: dc.descriptionConselho Nacional de Desenvolvimento Científico e Tecnológico (CNPq)-
Descrição: dc.descriptionINPE, Div Space Mech & Control, CP 515, BR-12227310 Sao Jose Dos Campos, SP, Brazil-
Descrição: dc.descriptionUPMC Univ Paris 06, SYRTE, Observ Paris, PSL Res Univ,CNRS,Sorbonne Univ,LNE, 61 Ave Observ, Paris, France-
Descrição: dc.descriptionSao Paulo State Univ, UNESP, Sch Nat Sci & Engn, BR-12516410 Guaratingueta, SP, Brazil-
Descrição: dc.descriptionSao Paulo State Univ, UNESP, Sch Nat Sci & Engn, BR-12516410 Guaratingueta, SP, Brazil-
Descrição: dc.descriptionCAPES: 88887.374148/2019-00-
Descrição: dc.descriptionCNPq: 301577/2017-0-
Formato: dc.format317-338-
Idioma: dc.languageen-
Publicador: dc.publisherEditura Acad Romane-
Relação: dc.relationRomanian Astronomical Journal-
???dc.source???: dc.sourceWeb of Science-
Palavras-chave: dc.subjectCelestial Mechanics-
Palavras-chave: dc.subjectDynamical astronomy-
Palavras-chave: dc.subjectMinor planets-
Palavras-chave: dc.subjectAsteroids: individual (Apophis)-
Título: dc.titleInfluence of apophis’ spin axis variations on a spacecraft during the 2029 close approach with earth-
Tipo de arquivo: dc.typelivro digital-
Aparece nas coleções:Repositório Institucional - Unesp

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