@MastersThesis{Felipe:2000:MaOrAp,
               author = "Felipe, Gislaine de",
                title = "Manobras orbitais aplicadas aos problemas de dois e tr{\^e}s 
                         corpos",
               school = "Instituto Nacional de Pesquisas Espaciais (INPE)",
                 year = "2000",
              address = "Sao Jose dos Campos",
                month = "2000-02-03",
             keywords = "mec{\^a}nica celeste, problema de dois corpos, problema de 
                         tr{\^e}s corpos, transfer{\^e}ncia orbital, orbita de 
                         sat{\'e}lites, trajet{\'o}rias, astrodin{\^a}mica, celestial 
                         mechanics, two body problem, tree body problem, spacecrafts 
                         orbits, trajectories, astrodynamics.",
             abstract = "Nas atividades espaciais, e de grande import{\^a}ncia o estudo 
                         das trajet{\'o}rias que os ve{\'{\i}}culos espaciais devem 
                         seguir para completar uma miss{\~a}o. Com essa 
                         motiva{\c{c}}{\~a}o, o presente trabalho esta concentrado no 
                         estudo dessas trajet{\'o}rias, dentro da din{\^a}mica dada por: 
                         a) o problema tradicional de dois corpos com orbitas keplerianas, 
                         onde e suposto que o veiculo espacial se move em torno de um corpo 
                         celeste modelado por um ponto de massa; b) o famoso problema 
                         restrito de tr{\^e}s corpos, onde o veiculo espacial e assumido 
                         como sendo um ponto de massa que se move devido as forcas 
                         gravitacionais de dois prim{\'a}rios que s{\~a}o dois corpos 
                         celestes modelados como pontos de massa e em orbitas keplerianas 
                         ao redor de um centro de massa comum. Ser{\~a}o estudadas 
                         manobras realizadas com o uso de propulsores capazes de prover 
                         varia{\c{c}}{\~o}es instant{\^a}neas de velocidade em um 
                         veiculo espacial e manobras que usam apenas forcas gravitacionais. 
                         Ser{\~a}o feitas compara{\c{c}}{\~o}es entre op{\c{c}}{\~o}es 
                         diferentes para as respectivas manobras. As manobras que requerem 
                         que dois ve{\'{\i}}culos espaciais se encontrem no espa{\c{c}}o 
                         (Rendezvous) tamb{\'e}m s{\~a}o considerados, assim como 
                         manobras que consideram constela{\c{c}}{\~o}es de 
                         sat{\'e}lites. ABSTRACT: In the space activities, it is of great 
                         importance the study of the trajectories that the space vehicles 
                         should follow to complete a mission. With that motivation, the 
                         present research is concentrated in the study of those 
                         trajectories, under the dynamics given by: a)The traditional 
                         Problem of Two Bodies with Keplerian orbits where the space 
                         vehicle is supposed to move around a heavenly body modeled by a 
                         point of mass; b)The wellknown Restricted Problem of Three Bodies 
                         Model, where the space vehicle is assumed as being a point of mass 
                         that moves due to the gravitational forces of two primaries, that 
                         are two heavenly bodies modeled as point of mass and that are in 
                         Keplerian orbits around a common center of mass. Maneuvers 
                         accomplished with the use of engines capable to supply 
                         instantaneous variations of velocity in a space vehicle and 
                         maneuver that use only gravitational forces will be studied. 
                         Comparisons among different options for the respective maneuvers 
                         will be made. The maneuvers that requires that two spacecrafts 
                         encounter in the space (Rendezvous)are also considered, as well as 
                         maneuvers considering constellations of satellites.",
            committee = "Moraes, Rodolpho Vilhena de (presidente) and Prado, Antonio 
                         Fernando Bertachini de Almeida (orientador) and Winter, Othon Cabo 
                         and Zanardi, Maria Cecilia Fran{\c{c}}a de Paula Santos",
         englishtitle = "Orbital maneuvers applied to the problems of two and three 
                         bodies",
                label = "8842",
             language = "pt",
                pages = "170",
                  ibi = "6qtX3pFwXQZ4PKzA/o5Nmi",
                  url = "http://urlib.net/ibi/6qtX3pFwXQZ4PKzA/o5Nmi",
           targetfile = "publicacao.pdf",
        urlaccessdate = "03 maio 2024"
}