@Article{SalazarMeloMacaWint:2012:ThPrLa,
               author = "Salazar, F. J. T. and Melo, Cristiano Fiorilo de and Macau, Elbert 
                         Einstein Nehrer and Winter, Othon Cabo",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and 
                         Universidade Federal do ABC, Rua Santa Ad{\'e}lia 166, Santo 
                         Andr{\'e}, SP, 09210-170, Brazil O. C. Winter and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)} and Univ Estadual 
                         Paulista—UNESP, Grupo de Din{\^a}mica Orbital e Planetologia, 
                         Guaratinguet{\'a}, SP 12516-410, Brazil",
                title = "Three-body problem, its Lagrangian points and how to exploit them 
                         using an alternative transfer to L4 and L5",
              journal = "Celestial Mechanics and Dynamical Astronomy",
                 year = "2012",
               volume = "114",
               number = "1-2",
                pages = "201--213",
                month = "Oct.",
                 note = "{Setores de Atividade: Pesquisa e desenvolvimento 
                         cient{\'{\i}}fico.}",
             keywords = "alternative transfers, stable Lagrangian points, L4, L5, 
                         three-body problem, trajectories-G, controle de caos, dinamica nao 
                         linear, astrodin{\^a}mica, din{\^a}mica orbital.",
             abstract = "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.",
                  doi = "10.1007/s10569-012-9426-y",
                  url = "http://dx.doi.org/10.1007/s10569-012-9426-y",
                 issn = "0923-2958",
                label = "lattes: 0793627832164040 3 SalazarMeloMacaWint:2012:ThPrLa",
             language = "en",
           targetfile = "macaulac.pdf",
                  url = "http://link.springer.com/article/10.1007/s10569-012-9426-y?null",
        urlaccessdate = "30 abr. 2024"
}