Analytical study of the powered Swing-By maneuver for elliptical systems and analysis of its efficiency

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dc.contributor.authorFerreira, Alessandra F. S. [UNESP]
dc.contributor.authorPrado, Antônio F. B. A.
dc.contributor.authorWinter, Othon C. [UNESP]
dc.contributor.authorSantos, Denilson P. S. [UNESP]
dc.contributor.institutionInstituto Nacional de Pesquisas Espaciais—INPE
dc.contributor.institutionUniversidade Estadual Paulista (Unesp)
dc.date.accessioned2018-12-11T17:37:24Z
dc.date.available2018-12-11T17:37:24Z
dc.date.issued2018-07-01
dc.description.abstractAnalytical equations describing the velocity and energy variation of a spacecraft in a Powered Swing-By maneuver in an elliptic system are presented. The spacecraft motion is limited to the orbital plane of the primaries. In addition to gravity, the spacecraft suffers the effect of an impulsive maneuver applied when it passes by the periapsis of its orbit around the secondary body of the system. This impulsive maneuver is defined by its magnitude δV and the angle that defines the direction of the impulse with respect to the velocity of the spacecraft (α). The maneuver occurs in a system of main bodies that are in elliptical orbits, where the velocity of the secondary body varies according to its position in the orbit following the rules of an elliptical orbit. The equations are dependent on this velocity. The study is done using the “patched-conics approximation”, which is a method of simplifying the calculations of the trajectory of a spacecraft traveling around more than one celestial body. Solutions for the velocity and energy variations as a function of the parameters that define the maneuver are presented. An analysis of the efficiency of the powered Swing-By maneuver is also made, comparing it with the pure gravity Swing-by maneuver with the addition of an impulse applied outside the sphere of influence of the secondary body. After a general study, the techniques developed here are applied to the systems Sun-Mercury and Sun-Mars, which are real and important systems with large eccentricity. This problem is highly nonlinear and the dynamics very complex, but very reach in applications.en
dc.description.affiliationInstituto Nacional de Pesquisas Espaciais—INPE
dc.description.affiliationGrupo de Dinâmica Orbital e Planetologia São Paulo State University—UNESP
dc.description.affiliationSão Paulo State University—UNESP
dc.description.affiliationUnespGrupo de Dinâmica Orbital e Planetologia São Paulo State University—UNESP
dc.description.affiliationUnespSão Paulo State University—UNESP
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: 2016/14665-2
dc.description.sponsorshipIdFAPESP: 2016/23542-1
dc.description.sponsorshipIdFAPESP: 2016/24561-0
dc.description.sponsorshipIdFAPESP: 2017/04643-4
dc.description.sponsorshipIdCNPq: 301338/2016-7
dc.description.sponsorshipIdCNPq: 312813/2013-9
dc.description.sponsorshipIdCNPq: 406841/2016-0
dc.identifierhttp://dx.doi.org/10.1007/s10509-018-3362-6
dc.identifier.citationAstrophysics and Space Science, v. 363, n. 7, 2018.
dc.identifier.doi10.1007/s10509-018-3362-6
dc.identifier.file2-s2.0-85048501746.pdf
dc.identifier.issn1572-946X
dc.identifier.issn0004-640X
dc.identifier.scopus2-s2.0-85048501746
dc.identifier.urihttp://hdl.handle.net/11449/179951
dc.language.isoeng
dc.relation.ispartofAstrophysics and Space Science
dc.rights.accessRightsAcesso aberto
dc.sourceScopus
dc.subjectAstrodynamics
dc.subjectElliptical systems
dc.subjectImpulsive maneuver
dc.subjectPowered Swing-By maneuvers
dc.subjectSpacecraft trajectories
dc.titleAnalytical study of the powered Swing-By maneuver for elliptical systems and analysis of its efficiencyen
dc.typeArtigo
unesp.author.orcid0000-0002-4901-3289[3]
unesp.author.orcid0000-0003-2682-4043[4]

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