Mapeamento de órbitas em torno de luas do sistema solar
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Data
2021-04-08
Autores
Ferreira, Lucas dos Santos
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Editor
Universidade Estadual Paulista (Unesp)
Resumo
Esse trabalho tem como objetivo investigar a estabilidade de órbitas em torno de diversos satélites naturais do Sistema Solar. Considerando que o sistema foi normalizado, utilizamos o problema de três corpos (P3C) e investigamos os efeitos da perturbação devido aos planetas dos satélites naturais. Para isso utilizamos o pacote do integrador Rebound. As simulações foram escritas de forma a verificar a possibilidade de ejeção, a colisão com os corpos, principais ou a sobrevivência das sondas espaciais no tempo total de integração do problema. Além disso, foram simuladas órbitas em torno dos satélites naturais sobre os mais diversos regimes. As simulações localizaram zonas instáveis e estáveis. Considerando sondas em órbitas iniciais circulares, as dinâmicas em torno dos satelites naturais permitiram localizar intervalos em que os tempos de vida foram altos dependendo do semieixo maior inicial da órbita da sonda, fazendo com que essas sondas orbitassem esses satelites naturais por períodos de meses ou anos. Os estudos em função da inclinação e da excentricidade inicial da sonda em torno desses satélites permitiram identificar que, de modo geral, a escolha da excentricidade inicial da órbita da sonda é importante para determinar a duração dos tempos de vida das órbitas. Pois, uma vez que o efeito Kozai tende a tornar as órbitas excêntricas, as órbitas iniciadas com menor excentricidade apresentaram tempos de vida altos. Foi observado também que a depender da altitude da órbita inicial da sonda, existe uma dominância ou um equilíbrio entre o argumento do pericentro e a longitude do nodo inicial que determinam condições com maiores tempos de vida. Nesse estudo, foi observado a existência de ilhas de estabilidade que foram consideradas regiões importantes, pois apresentam a possibilidade de missões com maiores durações em condições de altas excentricidades e/ou inclinações.
This work aims to investigate the stability of the orbits around several natural satellites in the Solar System. Considering that the system was normalized, it was used the three-body problem (P3C) and investigated the effects of the disturbance due to the planets of the natural satellites. For this purpose, the Rebound integrator package was used. The simulations were written in order to verify the possibility of ejection, the collision with the main bodies or the survival of space probes in the total time of integration of the problem. In addition, orbits around natural satellite were simulated in several conditions as well. The simulations located unstable and stable zones. Considering probes in initial circular orbits, the dynamics around the natural satellites allowed to locate intervals in which the lifetimes were high depending on the initial semi-major axis of the orbit of the probe, causing these probes to orbit these natural satellites for periods of months or years. The studies based on the $ I_ {0} $ and $ e_ {0} $ of the probe around these satellites allowed us to identify that, in general, the choice of the initial eccentricity of the orbit of the probe is important to determine the duration of the orbit life. Since the Kozai effect tends to make orbits eccentric, the orbits started with less eccentricity had high lifetimes. It was also observed that depending on the altitude of the probe's initial orbit, there is a dominance or a balance between the initial conditions of the argument of periapsis as well as the longitude of the ascending node that determine conditions with longer lifetime. In this study, it was observed the existence of islands of stability - considered important regions - as they present the possibility of missions with longer durations in conditions of high eccentricities and/or inclinations.
This work aims to investigate the stability of the orbits around several natural satellites in the Solar System. Considering that the system was normalized, it was used the three-body problem (P3C) and investigated the effects of the disturbance due to the planets of the natural satellites. For this purpose, the Rebound integrator package was used. The simulations were written in order to verify the possibility of ejection, the collision with the main bodies or the survival of space probes in the total time of integration of the problem. In addition, orbits around natural satellite were simulated in several conditions as well. The simulations located unstable and stable zones. Considering probes in initial circular orbits, the dynamics around the natural satellites allowed to locate intervals in which the lifetimes were high depending on the initial semi-major axis of the orbit of the probe, causing these probes to orbit these natural satellites for periods of months or years. The studies based on the $ I_ {0} $ and $ e_ {0} $ of the probe around these satellites allowed us to identify that, in general, the choice of the initial eccentricity of the orbit of the probe is important to determine the duration of the orbit life. Since the Kozai effect tends to make orbits eccentric, the orbits started with less eccentricity had high lifetimes. It was also observed that depending on the altitude of the probe's initial orbit, there is a dominance or a balance between the initial conditions of the argument of periapsis as well as the longitude of the ascending node that determine conditions with longer lifetime. In this study, it was observed the existence of islands of stability - considered important regions - as they present the possibility of missions with longer durations in conditions of high eccentricities and/or inclinations.
Descrição
Palavras-chave
Terceiro corpo, luas, órbitas, sonda, tempo de vida, estabilidade, Third-body, probe, orbit, lifetime, stability, Satélites - órbitas, Sondas espaciais, Sistema solar