@Article{FerreiraPradWintSant:2018:AnStSw,
               author = "Ferreira, Alessandra F. S. and Prado, Antonio Fernando Bertachini 
                         de Almeida and Winter, Othon C. and Santos, Denilson Paulo S.",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)} and {Universidade Estadual 
                         Paulista (UNESP)} and {Universidade Estadual Paulista (UNESP)}",
                title = "Analytical study of the swing-by maneuver in an elliptical 
                         system",
              journal = "Astrophysics and Space Science",
                 year = "2018",
               volume = "363",
               number = "2",
                pages = "e24",
                month = "Feb.",
             keywords = "Astrodynamics, Swing-by maneuvers, Spacecraft trajectories, 
                         Elliptical systems.",
             abstract = "The objective of the present paper is to derive a set of 
                         analytical equations that describe a swing-by maneuver realized in 
                         a system of primaries that are in elliptical orbits. The goal is 
                         to calculate the variations of energy, velocity and angular 
                         momentum as a function of the usual basic parameters that describe 
                         the swing-by maneuver, as done before for the case of circular 
                         orbits. In elliptical orbits the velocity of the secondary body is 
                         no longer constant, as in the circular case, but it varies with 
                         the position of the secondary body in its orbit. As a consequence, 
                         the variations of energy, velocity and angular momentum become 
                         functions of the magnitude and the angle between the velocity 
                         vector of the secondary body and the line connecting the 
                         primaries. The patched-conics approach is used to obtain these 
                         equations. The configurations that result in maximum gains and 
                         losses of energy for the spacecraft are shown next, and a 
                         comparison between the results obtained using the analytical 
                         equations and numerical simulations are made to validate the 
                         method developed here.",
                  doi = "10.1007/s10509-017-3242-5",
                  url = "http://dx.doi.org/10.1007/s10509-017-3242-5",
                 issn = "0004-640X",
             language = "en",
           targetfile = "ferreira_analytical.pdf",
        urlaccessdate = "01 maio 2024"
}