%0 Journal Article
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}
%@nexthigherunit 8JMKD3MGPCW/3ESGTTP
%@secondarytype PRE PI
%@issn 0923-2958
%3 macaulac.pdf
%D 2012
%4 dpi.inpe.br/plutao/2012/11.28.14.42.30
%T Three-body problem, its Lagrangian points and how to exploit them using an alternative transfer to L4 and L5
%@usergroup administrator
%@usergroup banon
%@usergroup lattes
%@usergroup marciana
%U http://link.springer.com/article/10.1007/s10569-012-9426-y?null
%V 114
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@affiliation Universidade Federal do ABC, Rua Santa Adélia 166, Santo André, SP, 09210-170, Brazil O. C. Winter
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@affiliation Univ Estadual Paulista—UNESP, Grupo de Dinâmica Orbital e Planetologia, Guaratinguetá, SP 12516-410, Brazil
%F lattes: 0793627832164040 3 SalazarMeloMacaWint:2012:ThPrLa
%@resumeid
%@resumeid
%@resumeid 8JMKD3MGP5W/3C9JGUT
%8 Oct.
%X An alternative transfer strategy to send spacecraft to stable orbits around the Lagrangian equilibrium points L4 and L5 based in trajectories derived from the periodic orbits around L1 is presented in this work. The trajectories derived, called Trajectories G, are described and studied in terms of the initial generation requirements and their energy variations relative to the Earth through the passage by the lunar sphere of influence. Missions for insertion of spacecraft in elliptic orbits around L4 and L5 are analysed considering the restricted three-body problem Earth-Moon-particle and the results are discussed starting from the thrust, time of flight and energy variation relative to the Earth.
%@versiontype publisher
%@electronicmailaddress
%@electronicmailaddress
%@electronicmailaddress elbert@lac.inpe.br
%@secondarykey INPE--PRE/
%@area COMP
%@e-mailaddress elbert@lac.inpe.br
%@archivingpolicy denypublisher denyfinaldraft12
%K alternative transfers, stable Lagrangian points, L4, L5, three-body problem, trajectories-G, controle de caos, dinamica nao linear, astrodinâmica, dinâmica orbital.
%@documentstage not transferred
%@doi 10.1007/s10569-012-9426-y
%@group LAC-CTE-INPE-MCTI-GOV-BR
%@group
%@group LAC-CTE-INPE-MCTI-GOV-BR
%N 1-2
%O Setores de Atividade: Pesquisa e desenvolvimento científico.
%@dissemination WEBSCI; PORTALCAPES.
%P 201-213
%A Salazar, F. J. T.,
%A Melo, Cristiano Fiorilo de,
%A Macau, Elbert Einstein Nehrer,
%A Winter, Othon Cabo,
%2 dpi.inpe.br/plutao/2012/11.28.14.42.31
%B Celestial Mechanics and Dynamical Astronomy