@Article{RibeiroMeloPrad:2022:ApTrNe,
               author = "Ribeiro, Rebeca de Souza and Melo, Cristiano F. de and Prado, 
                         Antonio Fernando Bertachini de Almeida",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and 
                         {Universidade Federal de Minas Gerais (UFMG)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)}",
                title = "Trajectories Derived from Periodic Orbits around the Lagrangian 
                         Point L1 and Lunar Swing-Bys: Application in Transfers to 
                         Near-Earth Asteroids",
              journal = "Symmetry",
                 year = "2022",
               volume = "14",
               number = "6",
                pages = "1132",
             keywords = "periodic orbits, escape trajectories, lunar swing-by, near-earth 
                         asteroids, mission analysis.",
             abstract = "To present a set of trajectories derived from the retrograde 
                         periodic orbits around the Lagrangian equilibrium point L1 , this 
                         paper considers the Circular Restricted Three-body Problem with 
                         Earth-Moon masses (CR3BP), the Restricted Bicircular, and Full 
                         Four-Body Sun-Earth-Moonspacecraft Problems (BCR4BP and FR4BP, 
                         respectively). These periodic orbits are predicted by the dynamics 
                         of the CR3BP. To generate the trajectories of this set, first, 
                         slightly different increments of velocity (\∆Vs) from those 
                         needed to generate periodic orbits around L1 are applied to a 
                         spacecraft in circular low Earth orbits in the same direction of 
                         their motion when the Earth, the spacecraft, and the Moon are 
                         aligned in this order. Thus, translunar trajectories derived from 
                         the periodic orbits are obtained and they will lead the spacecraft 
                         to the vicinity of the Moon. Depending on the values of the 
                         |\∆Vs|, which are also functions of the relative 
                         positioning between the Sun, the Earth, and the Moon, three types 
                         of trajectories of interest are found: Collision with the Moon, 
                         escape, and geocentric orbits with large semi-major axes. For a 
                         well-defined interval of the |\∆Vs|, the trajectories 
                         accomplish swing-bys with the Moon and obtain energy to escape 
                         from the EarthMoon system and reach Near-Earth Asteroids (NEAs) 
                         between the orbits of Venus and Mars. This procedure reduces the 
                         costs of inserting spacecraft into transfer trajectories to a set 
                         of NEAs in terms of the required |\∆V| by up to 5% when 
                         compared to Lamberts problem, for example. This work also presents 
                         analyses of examples of transfers to the NEAs 3361 Orpheus, 99942 
                         Apophis, and 65803 Didymos, from 2025 on.",
                  doi = "10.3390/sym14061132",
                  url = "http://dx.doi.org/10.3390/sym14061132",
                 issn = "2073-8994",
                label = "lattes: 1226006844793712 1 RibeiroMeloPrad:2022:ApTrNe",
             language = "en",
           targetfile = "symmetry-14-01132-v2.pdf",
        urlaccessdate = "10 maio 2024"
}