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@Article{GonçalvesRoccMora:2013:OrDiAn,
               author = "Gon{\c{c}}alves, L. D and Rocco, Evando Marconi and Moraes, 
                         Rodolpho Vilhena de",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)} and {Universidade Federal 
                         de S{\~a}o Paulo (UNIFESP)}",
                title = "Orbital disturbance analysis due to the lunar gravitational 
                         potential and deviation minimization through the trajectory 
                         control in closed loop",
              journal = "Journal of Physics: Conference Series",
                 year = "2013",
               volume = "465",
               number = "1",
                pages = "Article number 012013",
                 note = "16th Brazilian Colloquium on Orbital Dynamics; Serra Negra, Sao 
                         Paulo; Brazil; 26 November 2012 through 30 November 2012",
             abstract = "A study evaluating the influence due to the lunar gravitational 
                         potential, modeled by spherical harmonics, on the gravity 
                         acceleration is accomplished according to the model presented in 
                         Konopliv (2001). This model provides the components x, y and z for 
                         the gravity acceleration at each moment of time along the 
                         artificial satellite orbit and it enables to consider the 
                         spherical harmonic degree and order up to100. Through a comparison 
                         between the gravity acceleration from a central field and the 
                         gravity acceleration provided by Konopliv's model, it is obtained 
                         the disturbing velocity increment applied to the vehicle. Then, 
                         through the inverse problem, the Keplerian elements of perturbed 
                         orbit of the satellite are calculated allowing the orbital motion 
                         analysis. Transfer maneuvers and orbital correction of lunar 
                         satellites are simulated considering the disturbance due to 
                         non-uniform gravitational potential of the Moon, utilizing 
                         continuous thrust and trajectory control in closed loop. The 
                         simulations are performed using the Spacecraft Trajectory 
                         Simulator-STRS, Rocco (2008), which evaluate the behavior of the 
                         orbital elements, fuel consumption and thrust applied to the 
                         satellite over the time.",
                  doi = "10.1088/1742-6596/465/1/012013",
                  url = "http://dx.doi.org/10.1088/1742-6596/465/1/012013",
                 issn = "1742-6588",
             language = "en",
        urlaccessdate = "25 jan. 2021"
}


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