Searching for orbits to observe the poles of celestial bodies
| Autor: | Tadashi Yokoyama, Allan K. de Almeida Junior, Antonio F. B. A. Prado, Diogo M. Sanchez |
|---|---|
| Přispěvatelé: | Instituto Nacional de Pesquisas Espaciais (INPE), Universidade Estadual Paulista (Unesp), Texas A&M University |
| Jazyk: | angličtina |
| Rok vydání: | 2020 |
| Předmět: |
Atmospheric Science
010504 meteorology & atmospheric sciences Physical system Aerospace Engineering Perturbation (astronomy) Thrust 01 natural sciences Astrodynamics 0103 physical sciences Nonlinear systems 010303 astronomy & astrophysics 0105 earth and related environmental sciences Equilibrium point Physics Spacecraft Computer simulation business.industry Mathematical analysis Equations of motion Astronomy and Astrophysics Artificial equilibrium points Nonlinear system Geophysics Space and Planetary Science Physics::Space Physics General Earth and Planetary Sciences Astrophysics::Earth and Planetary Astrophysics business Restricted three-body problem |
| Zdroj: | Scopus Repositório Institucional da UNESP Universidade Estadual Paulista (UNESP) instacron:UNESP |
| Popis: | Made available in DSpace on 2021-06-25T11:04:41Z (GMT). No. of bitstreams: 0 Previous issue date: 2020-11-15 Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES) Fundação de Amparo à Pesquisa do Estado de São Paulo (FAPESP) Conselho Nacional de Desenvolvimento Científico e Tecnológico (CNPq) The objective of the present paper is to show a method to find orbits near artificial equilibrium points for a satellite equipped with a continuous thrust that allows it to stay near the poles of a celestial body. The physical system includes the presence of a moon of the celestial body under observation, and the perturbation caused by this moon is counteracted by an algorithm to help the satellite to stay close to its original position, instead of escape from it. The equations of motion are changed under some approximations, and analytical solutions for these equations are obtained and analyzed. Initial conditions are used such that their secular terms are nullified. These solutions are restricted to a short period of time, but we propose a method in which there are periodic updates in the thrust. Thus, the solutions can be extended for the duration of the mission. A numerical simulation is obtained, whose results are required to be in agreement with the analytical solution using these periodic adjustments of the thrust. This agreement means that the motion of the spacecraft remains bounded close to its initial position for longer times. Several systems with different sizes and mass parameters are used to show the results of the research, like Sun-Earth-Moon, Sun-Ida-Dactyl, Sun-Saturn-Titan and Sun-Mars-Phobos systems. The results also indicate the locations of points that require minimum magnitude of the thrust. Instituto Nacional de Pesquisas Espaciais (INPE) UNESP Universidade Estadual Paulista Aerospace Engineering Texas A&M University UNESP Universidade Estadual Paulista FAPESP: 2014/22295-5 FAPESP: 2016/24561-0 FAPESP: 2018/07377-6 FAPESP: 2019/18480-5 CNPq: 301338/2016-7 CNPq: 309190/2017-7 CNPq: 406841/2016-0 |
| Databáze: | OpenAIRE |
| Externí odkaz: |
|