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dc.contributor.authorSilva, Alessandra F.
dc.contributor.authorPrado, Antonio F. B. A.
dc.contributor.authorWinter, Othon C. [UNESP]
dc.date.accessioned2014-05-27T11:30:42Z
dc.date.available2014-05-27T11:30:42Z
dc.date.issued2013-09-16
dc.identifierhttp://dx.doi.org/10.2514/6.2013-4722
dc.identifier.citationAIAA Guidance, Navigation, and Control (GNC) Conference.
dc.identifier.urihttp://hdl.handle.net/11449/76568
dc.description.abstractThis paper studies the problem of applying an impulsive control in a spacecraft that is performing a Swing-By maneuver. The objective is to study the changes in velocity, energy and angular momentum for this maneuver as a function of the three usual parameters of the standard Swing-By plus the three parameters (the magnitude of the impulse, the point of its application and the angle between the impulse and the velocity of the spacecraft) that specify the impulse applied. The dynamics used is the restricted three body problem under the regularization of Lemaitre, made to increase the accuracy of the numerical integration near the primaries. The present research develops an algorithm to calculate the variation of energy and angular momentum in a maneuver where the application of the impulsive control occurs before or after the passage of the spacecraft by the periapsis, but within the sphere of influence of the secondary body and in a non-tangential direction. Using this approach, it is possible to find the best position and direction to apply the impulse to maximize the energy change of the total maneuver. The results showed that the application of the impulse at the periapsis and in the direction of motion of the spacecraft is usually not the optimal solution.en
dc.language.isoeng
dc.relation.ispartofAIAA Guidance, Navigation, and Control (GNC) Conference
dc.sourceScopus
dc.subjectDirection of motion
dc.subjectImpulsive controls
dc.subjectITS applications
dc.subjectNumerical integrations
dc.subjectOptimal impulsive control
dc.subjectOptimal solutions
dc.subjectRestricted three body problem
dc.subjectSphere of influences
dc.subjectAngular momentum
dc.subjectSpacecraft
dc.titleOptimal impulsive control in a powered Swing-Byen
dc.typeTrabalho apresentado em evento
dcterms.licensehttp://arc.aiaa.org/page/authorrights
dc.contributor.institutionInstituto Nacional de Pesquisas Espaciais (INPE)
dc.contributor.institutionUniversidade Estadual Paulista (UNESP)
dc.description.affiliationDivision of Space Mechanics and Control INPE-Av dos Astronautas 1758 Instituto Nacional de Pesquisas Espaciais, São José dos Campos, São Paulo 12227-010
dc.description.affiliationDepartment of Mathematics Universidade Estadual Paulista, Guaratinguetá, SP 12516-410
dc.description.affiliationUnespDepartment of Mathematics Universidade Estadual Paulista, Guaratinguetá, SP 12516-410
dc.identifier.doi10.2514/6.2013-4722
dc.rights.accessRightsAcesso aberto
dc.identifier.scopus2-s2.0-84883699740
unesp.campusUniversidade Estadual Paulista (UNESP), Faculdade de Engenharia, Guaratinguetápt
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