@Article{NegriSukhPrad:2019:LuGrAs,
               author = "Negri, Rodolfo Batista and Sukhanov, Alexander and Prado, Antonio 
                         Fernando Bertachini de Almeida",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Space 
                         Research Institute of Russian Academy of Sciences} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)}",
                title = "Lunar gravity assists using patched-conics approximation, three 
                         and four body problems",
              journal = "Advances in Space Research",
                 year = "2019",
               volume = "64",
               number = "1",
                pages = "42--63",
             keywords = "Flyby, Swing-by, Lunar gravity assist maneuver, Patched-conics, 
                         Circular restricted three-body problem, Bi-circular restricted 
                         four-bodyproblem.",
             abstract = "The gravity assist is a maneuver greatly applied to space 
                         missions, with the main goal of giving or removing energy of a 
                         spacecraftthrough a passage near a celestial body. The 
                         patched-conics approximation is the first approximation that is 
                         usually considered in themission planning. It gives a good 
                         accuracy in the majority of the situations. However, when using 
                         the Moon for the close approach, theresults have a tendency to 
                         diverge from a more complete three body dynamics. This is due to 
                         the large mass of the Moon compared to theEarth. In that sense, 
                         the goal of the present paper is to study the errors given by the 
                         patched-conics approximation in a lunar gravityassist maneuver. To 
                         find those errors we compare the results coming from this 
                         approximation with the equivalent results obtained fromthe 
                         circular restricted three body problem and the bi-circular 
                         restricted four body problem for a same periselenium condition. 
                         This com-parison is made in the orbital elements before the 
                         maneuver and theC3of the spacecraft after the maneuver under the 
                         three modelsconsidered. Different values for the initial 
                         conditions of the spacecraft are used to obtain general 
                         conclusions about the behavior ofthe errors involved. We conclude 
                         that there is a tendency to a better agreement between the 
                         patched-conics and the three body problemfor retrograde transfer 
                         orbits. We also find that the effects of the Sun in the maneuver 
                         needs to be included only in more accurate steps ofthe mission.",
                  doi = "10.1016/j.asr.2019.04.002",
                  url = "http://dx.doi.org/10.1016/j.asr.2019.04.002",
                 issn = "0273-1177 and 1879-1948",
                label = "lattes: 0636218258038334 1 NegriSukhBert:2019:LuGrAs",
             language = "en",
           targetfile = "1-s2.0-S0273117719302455-main.pdf",
        urlaccessdate = "27 abr. 2024"
}