@Article{SantosSoTeMaAlMePr:2022:OpTrMo,
               author = "Santos, Leonardo Barbosa Torres dos and Sousa Silva, P. A. and 
                         Terra, M. O and Mani, Karthik V. and Almeida J{\'u}nior, Alan 
                         Kardec de and Merguizo Sanchez, Diogo and Prado, Antonio Fernando 
                         Bertachini de Almeida",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and 
                         {Universidade Estadual Paulista (UNESP)} and {Instituto 
                         Tecnol{\'o}gico de Aeron{\'a}utica (ITA)} and GomSpace and 
                         {Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)} and {Instituto Nacional de 
                         Pesquisas Espaciais (INPE)}",
                title = "Optimal transfers from Moon to L2 halo orbit of the Earth-Moon 
                         system",
              journal = "Advances in Space Research",
                 year = "2022",
               volume = "70",
               number = "11",
                pages = "3362--3372",
                month = "Dec.",
             keywords = "Mission design, Moon to L2 Halo orbit transfer, Optimal transfers, 
                         Restricted three-body problem, Stable manifold.",
             abstract = "In this paper, optimal solutions are investigated for a transfer 
                         from a parking orbit around the Moon to a halo orbit around L2 of 
                         the Earth-Moon system. The transfers are executed by applying a 
                         single maneuver and exploiting the stable invariant manifold of 
                         the hyperbolic parking solution at arrival. In this regard, an 
                         optimization problem is proposed where both the orbital 
                         characteristics of a parking solution around the Moon (its 
                         Keplerian elements) and the characteristics of a transfer 
                         trajectory (guided by the stable manifold of the arrival Halo 
                         orbit) are considered as variables. The problem involved in the 
                         single maneuver transfer is solved using a nonlinear programming 
                         method (NLP), which aims to minimize the cost of \ΔV within 
                         the framework of the Earth-Moon system using the circular 
                         restricted three-body problem. The feasibility of this kind of 
                         transfer for a Cubesat is shown in this paper through results with 
                         low \ΔV combined with suitable times of flight.",
                  doi = "10.1016/j.asr.2022.08.035",
                  url = "http://dx.doi.org/10.1016/j.asr.2022.08.035",
                 issn = "0273-1177 and 1879-1948",
             language = "en",
           targetfile = "Optimal transfers from Moon to halo orbit of the Earth-Moon 
                         system.pdf",
        urlaccessdate = "05 jun. 2024"
}