%0 Journal Article
%4 dpi.inpe.br/plutao/2012/11.28.14.42.30
%2 dpi.inpe.br/plutao/2012/11.28.14.42.31
%@doi 10.1007/s10569-012-9426-y
%@issn 0923-2958
%F lattes: 0793627832164040 3 SalazarMeloMacaWint:2012:ThPrLa
%T Three-body problem, its Lagrangian points and how to exploit them using an alternative transfer to L4 and L5
%D 2012
%8 Oct.
%A Salazar, F. J. T.,
%A Melo, Cristiano Fiorilo de,
%A Macau, Elbert Einstein Nehrer,
%A Winter, Othon Cabo,
%@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
%@electronicmailaddress
%@electronicmailaddress
%@electronicmailaddress elbert@lac.inpe.br
%B Celestial Mechanics and Dynamical Astronomy
%V 114
%N 1-2
%P 201-213
%K alternative transfers, stable Lagrangian points, L4, L5, three-body problem, trajectories-G, controle de caos, dinamica nao linear, astrodinâmica, dinâmica orbital.
%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.
%@language en
%3 macaulac.pdf
%U http://link.springer.com/article/10.1007/s10569-012-9426-y?null
%O Setores de Atividade: Pesquisa e desenvolvimento científico.