@MastersThesis{Gonçalves:2013:MaOrSa,
               author = "Gon{\c{c}}alves, Liana Dias",
                title = "Manobras orbitais de satelites artificiais lunares com 
                         aplica{\c{c}}{\~a}o de propuls{\~a}o cont{\'{\i}}nua",
               school = "Instituto Nacional de Pesquisas Espaciais (INPE)",
                 year = "2013",
              address = "S{\~a}o Jos{\'e} dos Campos",
                month = "2013-02-28",
             keywords = "perturba{\c{c}}{\~a}o, elementos orbitais, propuls{\~a}o 
                         cont{\'{\i}}nua, manobras orbitais, pertubation, orbital 
                         elements, continuous thrust, orbital manuvers.",
             abstract = "S{\~a}o realizados estudos avaliando a influ{\^e}ncia do 
                         potencial gravitacional e do albedo lunar sobre a {\'o}rbita de 
                         um sat{\'e}lite artificial. O potencial gravitacional {\'e} 
                         modelado por meio de harm{\^o}nicos esf{\'e}ricos, de acordo com 
                         o modelo apresentado em Konopliv (2001), e o albedo lunar {\'e} 
                         calculado a partir de adapta{\c{c}}{\~o}es no modelo apresentado 
                         em Rocco (2008a, 2009a). O modelo do albedo fornece o incremento 
                         de velocidade aplicado ao sat{\'e}lite devido {\`a} for{\c{c}}a 
                         causada pelo albedo lunar e o modelo do potencial gravitacional 
                         fornece as componentes x, y e z para a acelera{\c{c}}{\~a}o da 
                         gravidade em cada instante de tempo ao longo da {\'o}rbita de um 
                         sat{\'e}lite artificial, sendo poss{\'{\i}}vel considerar os 
                         harm{\^o}nicos esf{\'e}ricos at{\'e} grau e ordem 100. A partir 
                         da compara{\c{c}}{\~a}o da acelera{\c{c}}{\~a}o gravitacional 
                         de um campo central e da acelera{\c{c}}{\~a}o gerada pelo campo 
                         fornecido pelo modelo de Konopliv pode ser obtida a 
                         varia{\c{c}}{\~a}o da velocidade perturbadora aplicada ao 
                         ve{\'{\i}}culo, possibilitando, por meio da solu{\c{c}}{\~a}o 
                         do problema inverso, a obten{\c{c}}{\~a}o dos elementos 
                         keplerianos que caracterizam a {\'o}rbita do sat{\'e}lite 
                         artificial, afim de que seja feita uma an{\'a}lise do movimento 
                         orbital. Manobras de transfer{\^e}ncia e corre{\c{c}}{\~a}o 
                         orbitais de sat{\'e}lites lunares s{\~a}o simuladas considerando 
                         as perturba{\c{c}}{\~o}es citadas, utilizando empuxo 
                         cont{\'{\i}}nuo e controle de trajet{\'o}ria em malha fechada. 
                         As simula{\c{c}}{\~o}es s{\~a}o realizadas utilizando o 
                         simulador de trajet{\'o}ria \textit{Spacecraft Trajectory 
                         Simulator- STRS}, Rocco (2008b), em que s{\~a}o avaliados o 
                         comportamento dos elementos orbitais, o consumo de 
                         combust{\'{\i}}vel e o empuxo aplicado ao sat{\'e}lite ao longo 
                         do tempo. ABSTRACT: The studies evaluating the influence of the 
                         gravitational potential and the lunar albedo on the orbit of an 
                         artificial satellite are presented. The gravitational potential is 
                         modeled by spherical harmonics, in accordance with the model shown 
                         in Konopliv (2001) and the lunar albedo is calculated using a 
                         model presented in Rocco (2008a, 2009a) adapted to the Moon. The 
                         albedo model provides the velocity increment applied to the 
                         satellite due to the force caused by the lunar albedo and the 
                         model of gravitational potential provides the components x, y and 
                         z for the acceleration of gravity at each instant of time along 
                         the orbit of an artificial satellite. It allows to consider the 
                         spherical harmonics up to degree and order 100. From the 
                         comparison of the gravitational acceleration of a central field 
                         and the acceleration generated by the field provided by the 
                         Konopliv model the disturbing velocity variation applied to the 
                         vehicle can be obtained. Through the solution of the inverse 
                         problem, that provides the Keplerian elements of the orbit, an 
                         analysis of the orbital motion is made. Transfer maneuvers and 
                         orbital correction of lunar satellites are simulated considering 
                         the mentioned disturbances using continuous thrust and trajectory 
                         control in closed loop. The simulations are performed using the 
                         simulator \textquotedblleft{\textit{Spacecraft Trajectory 
                         Simulator-STRS}}\textquotedblright, Rocco (2008b), which assess 
                         the behavior of the orbital elements, the fuel consumption and the 
                         thrust applied to the satellite over the time.",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)}",
            committee = "Prado, Antonio Fernando Bertachini de Almeida (presidente) and 
                         Rocco, Evandro Marconi (orientador) and Moraes, Rodolpho Vilhena 
                         (orientador) and Chiaradia, Ana Paula Marins",
           copyholder = "SID/SCD",
         englishtitle = "Orbital maneuvers of artificial lunar satellite with continuous 
                         thrust application",
             language = "pt",
                pages = "301",
                  ibi = "8JMKD3MGP7W/3DL2KKS",
                  url = "http://urlib.net/ibi/8JMKD3MGP7W/3DL2KKS",
           targetfile = "publicacao.pdf",
        urlaccessdate = "11 maio 2024"
}