@Article{FerreiraMorPraWinSan:2021:CoApPo,
               author = "Ferreira, Alessandra F. S. and Moraes, Rodolpho Vilhena and Prado, 
                         Antonio Fernando Bertachini de Almeida and Winter, Othon C. and 
                         Santtos, Denilson P. S.",
          affiliation = "{Universidade Estadual Paulista (UNESP)} and {Universidade 
                         Estadual Paulista (UNESP)} and {Instituto Nacional de Pesquisas 
                         Espaciais (INPE)} and {Universidade Estadual Paulista (UNESP)} and 
                         {Universidade Estadual Paulista (UNESP)}",
                title = "A computational approach to the powered Swing-By in the elliptic 
                         restricted problem",
              journal = "Journal of the Brazilian Society of Mechanical Sciences and 
                         Engineering",
                 year = "2021",
               volume = "43",
               number = "4",
                pages = "e186",
                month = "Apr.",
             keywords = "Astrodynamics · Close approach · Orbital maneuvers · Elliptical 
                         system · Energy variation.",
             abstract = "This work performs a computational investigation of the energy 
                         variations given by a powered Swing-By maneuver realized in an 
                         elliptical system. It extends previous works by giving the freedom 
                         to choose the location and the direction of the thrust vector, 
                         aspects that were not considered before in the literature. Those 
                         variations are obtained numerically as a function of the 
                         parameters related to the thrust (magnitude, direction and 
                         location of the application) and the orbital parameters of the 
                         primaries (eccentricity and true anomaly). The maneuver is 
                         realized around the smaller primary, and the energy variations are 
                         measured with respect to the main body of the system. The initial 
                         orbit of the space vehicle is defned by its periapsis distance, 
                         angle and approach velocity with respect to the smaller primary. 
                         The study is applied to a system composed of two primaries that 
                         are in elliptic orbits around the center of mass of the system. 
                         The eccentricity is varied as a free parameter, to measure its 
                         efects. The results show that the best maneuvers apply the thrust 
                         at a point inside the sphere of infuence of the secondary body, 
                         but not in the periapsis of the orbit. The best direction of the 
                         thrust is not aligned with the motion of the space vehicle. The 
                         techniques studied here are applied in situations where it is 
                         desired to increase the energy of the space vehicle. Empirical 
                         equations are obtained for the energy variations, based on the 
                         simulations made in the present paper. The numerical approach 
                         makes the results more accurate and not limited to particular 
                         regions of the eccentricity.",
                  doi = "10.1007/s40430-021-02914-9",
                  url = "http://dx.doi.org/10.1007/s40430-021-02914-9",
                 issn = "1678-5878",
             language = "en",
           targetfile = "ferreira_computational.pdf",
        urlaccessdate = "09 maio 2024"
}