@PhDThesis{Silva:2017:EsMiEs,
author = "Silva, Maria Rita da",
title = "Estudo de uma miss{\~a}o espacial aos pontos colineares
lagrangianos no sistema Terra-Lua",
school = "Instituto Nacional de Pesquisas Espaciais (INPE)",
year = "2017",
address = "S{\~a}o Jos{\'e} dos Campos",
month = "2017-06-30",
keywords = "pontos de equil{\'{\i}}brio lagrangianos, sistema Terra-Lua,
cintur{\~o}es de radia{\c{c}}{\~a}o de Van Allen,
transfer{\^e}ncia de {\'o}rbitas, manobra orbitais, Lagrangian
equilibrium points, Earth-Moon system, Van Allen radiation belts,
transfer orbits, orbital maneuvers.",
abstract = "Em um sistema planeta-lua-ve{\'{\i}}culo espacial existem cinco
pontos de equil{\'{\i}}brio, sendo que tr{\^e}s s{\~a}o
inst{\'a}veis (L1, L2, L3) e dois s{\~a}o est{\'a}veis (L4,
L5). Estes pontos s{\~a}o alvos constantes das
perturba{\c{c}}{\~o}es externas gravitacionais e
n{\~a}o-gravitacionais, que podem inviabilizar a
utiliza{\c{c}}{\~a}o dos mesmos em miss{\~o}es espaciais para
observar o Universo e o nosso Sistema Solar. Deste modo, neste
trabalho, objetiva-se estudar e analisar as manobras orbitais de
um ve{\'{\i}}culo espacial utilizando propuls{\~a}o
cont{\'{\i}}nua, controladas por um sistema de controle PID em
malha fechada, a partir de uma {\'o}rbita de baixa altitude, em
torno da Terra, para cada um dos tr{\^e}s pontos colineares
lagrangianos do sistema Terra-Lua considerando as
perturba{\c{c}}{\~o}es externas como efeito durante as manobras
orbitais. Assim, primeiramente, modelou-se os cintur{\~o}es de
radia{\c{c}}{\~a}o utilizando os dados fornecidos pela
miss{\~a}o Van Allen Probes. Em seguida, determinou-se as
localiza{\c{c}}{\~o}es dos pontos colineares lagrangianos por
meio do somat{\'o}rio das atra{\c{c}}{\~o}es gravitacionais da
Terra e da Lua, a cada instante de tempo, compensadas com a
pseudo-for{\c{c}}a centr{\'{\i}}fuga, em um referencial
n{\~a}o-inercial; logo ap{\'o}s, determinou-se o mesmo,
por{\'e}m sob a influ{\^e}ncia da atra{\c{c}}{\~a}o
gravitacional do Sol, da press{\~a}o de radia{\c{c}}{\~a}o
solar e do potencial gravitacional dos corpos prim{\'a}rios
n{\~a}o-esf{\'e}ricos. A partir destas localiza{\c{c}}{\~o}es
instant{\^a}neas, obteve-se os elementos de estado
instant{\^a}neos que foram transformados em elementos orbitais
instant{\^a}neos, o que resultou na identifica{\c{c}}{\~a}o das
pseudo-{\'o}rbitas dos pontos colineares lagrangianos, no
referencial inercial. Desta forma, iniciou-se as
simula{\c{c}}{\~o}es, sendo que, primeiramente, incluiu-se um
estudo sobre a passagem do ve{\'{\i}}culo espacial atrav{\'e}s
dos cintur{\~o}es de Van Allen, durante as manobras de
transfer{\^e}ncia, nos per{\'{\i}}odos de baixa e alta
atividade solar. Isto possibilitou obter, com maior precis{\~a}o,
o tempo que o ve{\'{\i}}culo espacial permaneceu nas
regi{\~o}es de radia{\c{c}}{\~a}o e a taxa de dosagem de
radia{\c{c}}{\~a}o equivalente considerando o alum{\'{\i}}nio,
sil{\'{\i}}cio, tungst{\^e}nio, t{\^a}ntalo e chumbo como
materiais de blindagem. Ap{\'o}s as manobras de
transfer{\^e}ncia, aplicou-se a manobra de corre{\c{c}}{\~a}o
de {\'o}rbita para estabilizar o ve{\'{\i}}culo espacial em
cada um dos pontos colineares lagrangianos. ABSTRACT: In a
planet-moon-space-vehicle system there are five equilibrium
points, being that three are unstable (L1, L2, L3), and two are
stable (L4, L5). These points are targets of external
gravitational and non-gravitational perturbations, which may make
it impossible to use them in space missions to observe the
Universe and our Solar System. So, in this work, the objective is
to study and analyze the orbital maneuvers of a space vehicle
using continuous propulsion, controlled by a closed-loop PID
control system, from a low altitude orbit, around the Earth, for
each one of the three collinear Lagrangian points in the
Earth-Moon system considering the external perturbations as effect
during the orbital maneuvers. Thereby, the radiation belts were
first modeled using the data provided by the Van Allen Probes
mission. Next, the locations of the collinear Lagrangian points
were determined by sum of the Earths and Moons gravitational
attractions, at each instant of time, compensated by the
centrifugal pseudo-force, in a noninertial frame; subsequently,
they were determined, but under the influence of the gravitational
attraction of the Sun, the solar radiation pressure and the
gravitational potential of the non-spherical primary bodies. From
these instantaneous locations, the instantaneous state elements
were obtained and transformed into instantaneous orbital elements,
which resulted in the identification of the pseudo-orbits of the
collinear Lagrangian points, in the inertial reference frame.
Therefore, the simulations were initiated. Firstly, a study was
included on the passage of the space vehicle through the Van Allen
belts, during the maneuvers of transfer, during periods of low and
high solar activity. This made it possible to obtain, with more
precision, the time the spacecraft remained in the radiation
regions and the equivalent radiation dose rate considering
aluminum, silicon, tungsten, tantalum and lead as shielding
materials. After the maneuvers of transfer, the orbit correction
maneuver was applied to stabilize the space vehicle at each of the
collinear Lagrangian points.",
committee = "Ricci, Mario Cesar (presidente) and Rocco, Evandro Marconi
(orientador) and Moraes, Rodolpho Vilhena de and Carvalho,
Francisco das Chagas and Costa Filho, Aguinaldo Cardozo da",
englishtitle = "Study of a space mission to collinear Lagrange points in the
Earth-Moon system",
language = "pt",
pages = "249",
ibi = "8JMKD3MGP3W34P/3PDP29P",
url = "http://urlib.net/ibi/8JMKD3MGP3W34P/3PDP29P",
targetfile = "publicacao.pdf",
urlaccessdate = "27 abr. 2024"
}