author = "Salazar, F. J. T. and Macau, Elbert Einstein Nehrer and Winter, O. 
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)} and UNESP, Grupo de 
                         Din{\^a}mica Orbital e Planetologia, Guaratinguet{\'a}, SP 
                         12516-410, Brazil",
                title = "Alternative transfer to the Earth-Moon Lagrangian points L4 and L5 
                         using lunar gravity assist",
              journal = "Advances in Space Research",
                 year = "2014",
               volume = "53",
               number = "3",
                pages = "543--557",
             keywords = "L4, L5, Lagrangian points, Patched-conic, Swing by, Three-body 
                         problem, Lagrange multipliers, Space stations, Trajectories, 
             abstract = "Lagrangian points L4 and L5 lie at 60 ahead of and behind the Moon 
                         in its orbit with respect to the Earth. Each one of them is a 
                         third point of an equilateral triangle with the base of the line 
                         defined by those two bodies. These Lagrangian points are stable 
                         for the Earth-Moon mass ratio. As so, these Lagrangian points 
                         represent remarkable positions to host astronomical observatories 
                         or space stations. However, this same distance characteristic may 
                         be a challenge for periodic servicing mission. This paper studies 
                         elliptic trajectories from an Earth circular parking orbit to 
                         reach the Moon's sphere of influence and apply a swing-by maneuver 
                         in order to re-direct the path of a spacecraft to a vicinity of 
                         the Lagrangian points L4 and L5. Once the geocentric transfer 
                         orbit and the initial impulsive thrust have been determined, the 
                         goal is to establish the angle at which the geocentric trajectory 
                         crosses the lunar sphere of influence in such a way that when the 
                         spacecraft leaves the Moon's gravitational field, its trajectory 
                         and velocity with respect to the Earth change in order to the 
                         spacecraft arrives at L4 and L5. In this work, the planar Circular 
                         Restricted Three Body Problem approximation is used and in order 
                         to avoid solving a two boundary problem, the patched-conic 
                         approximation is considered.",
                  doi = "10.1016/j.asr.2013.11.055",
                  url = "http://dx.doi.org/10.1016/j.asr.2013.11.055",
                 issn = "0273-1177 and 1879-1948",
                label = "scopus 2014-05 SalazarMacaWint:2014:AlTrEa",
             language = "en",
           targetfile = "1-s2.0-S0273117713007588-main.pdf",
                  url = "http://dx.doi.org/10.1016/j.asr.2013.11.055",
        urlaccessdate = "01 dez. 2020"