@Article{PradoFeli:2007:AnStPo,
               author = "Prado, Antonio Fernando Bertachini de Almeida and Felipe, Gislaine 
                         de",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)}",
                title = "An analytical study of the powered swing-by to perform orbital 
                         maneuvers",
              journal = "Advances in Space Research",
                 year = "2007",
               volume = "40",
               number = "12",
                pages = "1769--1968",
             keywords = "Astrodynamics, Swing-by, Orbital maneuvers, Patched-conics 
                         approximation.",
             abstract = "In the present paper, we present an analytical description of the 
                         powered swing-by maneuver in the three-dimensional space. To 
                         perform this task, new analytical equations are derived for the 
                         three-dimensional unpowered swing-by, including the variation in 
                         velocity, angular momentum, energy and inclination of the 
                         spacecraft due to the maneuver. This is done based on the 
                         patched-conics approximation. From those general three-dimensional 
                         equations, it is possible to confirm some well-known analytical 
                         results for the planar case. The equations developed here are 
                         verified by numerical integrations, using the restricted problem 
                         of three bodies, showing an agreement better than 1%. After that, 
                         based on those equations, some new analytical results are obtained 
                         for the situation when an impulse is applied to the spacecraft 
                         during the close approach. Those new equations are based in the 
                         assumption that the impulse applied is small compared to the 
                         velocity of the spacecraft, and they allow the calculation of the 
                         same variations cited above. Those equations can be simplified for 
                         specific cases, and it can generate some conclusions about the 
                         direction to apply the impulse to attend specific goals. A study 
                         is also executed to investigate in which cases the impulse is more 
                         efficient when applied at the periapsis of the swing-by hyperbola 
                         or at points far way from the swing-by body.",
                  doi = "10.1016/j.asr.2007.04.098",
                  url = "http://dx.doi.org/10.1016/j.asr.2007.04.098",
                 issn = "0273-1177",
             language = "en",
           targetfile = "prado3.pdf",
        urlaccessdate = "24 abr. 2024"
}