@Article{SalazarWinMacMasGóm:2015:NaFoEa,
               author = "Salazar, F. J. T. and Winter, O. C. and Macau, Elbert Einstein 
                         Nehrer and Masdemont, J. J. and G{\'o}mez, G.",
          affiliation = "{Universidade Estadual Paulista (UNESP)} and {Universidade 
                         Estadual Paulista (UNESP)} and {Instituto Nacional de Pesquisas 
                         Espaciais (INPE)} and ETSEIB-UPC and Departament de 
                         Matem{\`a}tica Aplicada i An{\`a}isi, UB",
                title = "Natural formations at the Earth-Moon triangular point in perturbed 
                         restricted problems",
              journal = "Advances in Space Research",
                 year = "2015",
               volume = "56",
                pages = "144--162",
                 note = "{Setores de Atividade: Pesquisa e desenvolvimento 
                         cient{\'{\i}}fico.}",
             keywords = "Dinamica Nao-Linear, Din{\^a}mica Orbital, Astrodin{\^a}mica, 
                         controle, Din{\^a}mica Ca{\'o}tica.",
             abstract = "Previous studies for small formation flying dynamics about 
                         triangular libration points have determined the existence of 
                         regions of zero and Minimum Relative Radial Acceleration with 
                         respect to the nominal trajectory, that prevent from the expansion 
                         or contraction of the constellation. However, these studies only 
                         considered the gravitational force of the Earth and the Moon using 
                         the Circular Restricted Three Body Problem (CRTBP) scenario. 
                         Although the CRTBP model is a good approximation for the dynamics 
                         of spacecraft in the EarthMoon system, the nominal trajectories 
                         around equilateral libration points are strongly affected when the 
                         primary orbit eccentricity and solar gravitational force are 
                         considered. In this manner, the goal of this work is the analysis 
                         of the best regions to place a formation that is flying close a 
                         bounded solution around L4, taking into account the Moons 
                         eccentricity and Suns gravity. This model is not only more 
                         realistic for practical engineering applications but permits to 
                         determine more accurately the fuel consumption to maintain the 
                         geometry of the formation.",
                  doi = "10.1016/j.asr.2015.03.028",
                  url = "http://dx.doi.org/10.1016/j.asr.2015.03.028",
                 issn = "0273-1177 and 1879-1948",
                label = "lattes: 0793627832164040 3 SalazarWinMacMasG{\'o}m:2015:NaFoEa",
             language = "en",
           targetfile = "salazar_natural.pdf",
        urlaccessdate = "28 abr. 2024"
}