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@Article{GomesMurcPradGole:2016:AtClAp,
               author = "Gomes, Vivian Martins and Murcia Pineros, Jhonathan Orlando and 
                         Prado, Antonio Fernando Bertachini de Almeida and Golebiewska, 
                         Justyna",
          affiliation = "{Universidade Estadual Paulista (UNESP)} and {Instituto Nacional 
                         de Pesquisas Espaciais (INPE)} and {Instituto Nacional de 
                         Pesquisas Espaciais (INPE)} and {Adam Mickiewicz University}",
                title = "Atmospheric close approaches with the Earth considering drag and 
                         lift forces",
              journal = "Computational \& Applied Mathematics",
                 year = "2016",
               volume = "35",
               number = "3",
                pages = "817--833",
                month = "Oct.",
             keywords = "Astrodynamics, Swing-by, Orbital maneuvers, Aero-gravity maneuver, 
                         Close approach.",
             abstract = "A maneuver called {"}Aero-Gravity Assisted{"} is known in the 
                         literature to increase the energy gains given by a close approach 
                         between a spacecraft and a planet using the atmosphere of the 
                         planet. In a sequence of studies related to this problem, the 
                         present paper studies close approaches between a spacecraft and 
                         the Earth, in situations where the passage is close enough to the 
                         surface of the Earth such that the spacecraft crosses its 
                         atmosphere. The dynamical model considers the atmosphere of the 
                         Earth, in terms of drag and lift, the gravitational fields of the 
                         Earth and the Sun, assumed to be points of mass, and the 
                         spacecraft. The Earth and the Sun are assumed to be in circular 
                         coplanar orbits around their common center of mass. The equations 
                         of motion are the ones given by the circular planar restricted 
                         three-body problem with the addition of the forces generated by 
                         the atmospheric drag and lift. The primary objective is to map the 
                         variations of energy of the orbits of the spacecraft due to this 
                         close approach. The results show how the atmosphere affects the 
                         trajectory of the spacecraft, generating situations where the 
                         variation of energy changes sign with respect to the gravity part 
                         of the maneuver or where they have a zero net result, based in the 
                         equilibrium between atmospheric and gravity forces. This result 
                         opens the possibility of changing only the eccentricity of the 
                         orbit, keeping fixed its semi-major axis.",
                  doi = "10.1007/s40314-015-0256-x",
                  url = "http://dx.doi.org/10.1007/s40314-015-0256-x",
                 issn = "2238-3603",
             language = "en",
           targetfile = "gomes_atmospheric.pdf",
        urlaccessdate = "27 nov. 2020"
}


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