@MastersThesis{Pardal:2007:DeÓrVi,
               author = "Pardal, Paula Cristiane Pinto Mesquita",
                title = "Determina{\c{c}}{\~a}o de {\'o}rbita via GPS considerando 
                         modelo de press{\~a}o de radia{\c{c}}{\~a}o solar para o 
                         sat{\'e}lite Topex/Poseidon",
               school = "Instituto Nacional de Pesquisas Espaciais (INPE)",
                 year = "2007",
              address = "S{\~a}o Jos{\'e} dos Campos",
                month = "2007-02-27",
             keywords = "determina{\c{c}}{\~a}o de {\'o}rbita, GPS, 
                         estima{\c{c}}{\~a}o de estado, m{\'e}todo de m{\'{\i}}nimos 
                         quadrados recursivo, press{\~a}o de radia{\c{c}}{\~a}o solar, 
                         space technology and engineering, orbit determination, GPS, state 
                         estimation, recursive least squares method, solar radiation 
                         pressure.",
             abstract = "Foi determinada a {\'o}rbita de um sat{\'e}lite artificial, 
                         utilizando sinais da constela{\c{c}}{\~a}o GPS e o M{\'e}todo 
                         de M{\'{\i}}nimos Quadrados Recursivo atrav{\'e}s de 
                         ortogonaliza{\c{c}}{\~o}es de Givens como t{\'e}cnica de 
                         estima{\c{c}}{\~a}o, por ser um m{\'e}todo mais robusto e mais 
                         r{\'a}pido. A motiva{\c{c}}{\~a}o era melhorar o desempenho de 
                         processos de determina{\c{c}}{\~a}o de {\'o}rbitas e, ao mesmo 
                         tempo, minimizar o custo do procedimento computacional. As 
                         perturba{\c{c}}{\~o}es consideradas foram aquelas devidas ao 
                         geopotencial (at{\'e} ordem e grau 50×50), {\`a} press{\~a}o de 
                         radia{\c{c}}{\~a}o solar direta e {\`a} atra{\c{c}}{\~a}o 
                         luni-solar. Foi considerada tamb{\'e}m a posi{\c{c}}{\~a}o da 
                         antena GPS no sat{\'e}lite que, em {\'u}ltima an{\'a}lise, 
                         consiste na influ{\^e}ncia do movimento da atitude do 
                         sat{\'e}lite no processo de determina{\c{c}}{\~a}o de 
                         {\'o}rbita. Uma aplica{\c{c}}{\~a}o foi feita, utilizando dados 
                         reais do sat{\'e}lite Topex/Poseidon, dispon{\'{\i}}veis na 
                         Internet. A melhor precis{\~a}o em posi{\c{c}}{\~a}o obtida foi 
                         de 2 m para o curto per{\'{\i}}odo (2 horas) e de 7 m para o 
                         longo per{\'{\i}}odo (24 horas) de determina{\c{c}}{\~a}o de 
                         {\'o}rbita. Em ambos os casos, todas as perturba{\c{c}}{\~o}es 
                         mencionadas foram consideradas e as an{\'a}lises ocorreram sem a 
                         degrada{\c{c}}{\~a}o dos sinais das medidas. ABSTRACT: The orbit 
                         of an artificial satellite, using signals of the GPS constellation 
                         and the Recursive Least Squares Method as the estimation 
                         technique, which is more powerfull and faster, was determinated, 
                         with the aim of improving the performance of the orbits estimation 
                         process and, at the same time, minimizing the procedure 
                         computational cost. Perturbations up to high order geopotential 
                         (50×50), direct solar radiation pressure and Sun-Moon atraction 
                         were taken into account. It was also taken into consideration the 
                         position of the GPS antenna on the satellite body that, lately, 
                         consists of the influence of the satellite attitude motion in the 
                         orbit determination process. One application has been done, using 
                         real data from the Topex/Poseidon satellite, freely available at 
                         Internet. The best accuracy obtained in position was 2 meters for 
                         short period (2 hours) and 7 meters for long period (24 hours) 
                         orbit determination. In both cases all the perturbations mentioned 
                         before were taken into account and the analysis occurred without 
                         selective availability on the signals measurements.",
            committee = "Orlando, Valcir (presidente) and Kuga, H{\'e}lio Koiti 
                         (orientador) and Moraes, Rodolpho Vilhena de (orientador) and 
                         Chiaradia, Ana Paula Marins",
           copyholder = "SID/SCD",
         englishtitle = "Orbit determination using GPS considering solar radiation pressure 
                         model for the Topex/Poseidon satellite",
             language = "pt",
                pages = "178",
                  ibi = "6qtX3pFwXQZGivnK2Y/Q5bov",
                  url = "http://urlib.net/ibi/6qtX3pFwXQZGivnK2Y/Q5bov",
           targetfile = "publicacao.pdf",
        urlaccessdate = "11 maio 2024"
}