@Article{MeloMacaWint:2009:StPlCh,
               author = "Melo, Cristian Fiorilo and Macau, Elbert Einstein Nehrer and 
                         Winter, O. C.",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)}",
                title = "Strategies for plane change of Earth orbits using lunar gravity 
                         and derived trajectories of family G",
              journal = "Celestial Mechanics and Dynamical Astronomy",
                 year = "2009",
               volume = "103",
               number = "4",
                pages = "281--299",
                month = "Apr.",
             keywords = "Astrodynamics, Earth-Moon system, Mission design, Orbital 
                         maneuvers, Swing-by, Gravity assisted maneuver.",
             abstract = "The dynamics of the circular restricted three-body 
                         Earth-Moon-particle problem predicts the existence of the 
                         retrograde periodic orbits around the Lagrangian equilibrium point 
                         L1. Such orbits belong to the so-called family G (Broucke, 
                         Periodic orbits in the restricted three-body problem with 
                         Earth-Moon masses, JPL Technical Report 32-1168, 1968) and 
                         starting from them it is possible to define a set of trajectories 
                         that form round trip links between the Earth and the Moon. These 
                         links occur even with more complex dynamical systems as the 
                         complete Sun-Earth-Moon-particle problem. One of the most 
                         remarkable properties of these trajectories, observed for the 
                         four-body problem, is a meaningful inclination gain when they 
                         penetrate into the lunar sphere of influence and accomplish a 
                         swing-by with the Moon. This way, when one of these trajectories 
                         returns to the proximities of the Earth, it will be in a different 
                         orbital plane from its initial Earth orbit. In this work, we 
                         present studies that show the possibility of using this property 
                         mainly to accomplish transfer maneuvers between two Earth orbits 
                         with different altitudes and inclinations, with low cost, taking 
                         into account the dynamics of the four-body problem and of the 
                         swing-by as well. The results show that it is possible to design a 
                         set of nominal transfer trajectories that require Delta V (Total) 
                         less than conventional methods like Hohmann, bi-elliptic and 
                         bi-parabolic transfer with plane change.",
                  doi = "10.1007/s10569-009-9193-6",
                  url = "http://dx.doi.org/10.1007/s10569-009-9193-6",
                 issn = "0923-2958",
             language = "en",
           targetfile = "strategies for plane.pdf",
        urlaccessdate = "29 jun. 2024"
}