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(Referência obtida automaticamente do Web of Science, por meio da informação sobre o financiamento pela FAPESP e o número do processo correspondente, incluída na publicação pelos autores.)

Lunar gravity assists using patched-conics approximation, three and four body problems

Texto completo
Autor(es):
Negri, Rodolfo Batista [1] ; Sukhanov, Alexander [2] ; Bertachini de Almeida Prado, Antonio Fernando [3]
Número total de Autores: 3
Afiliação do(s) autor(es):
[1] INPE, Natl Inst Space Res, Sao Jose Dos Campos - Brazil
[2] Russian Acad Sci, Space Res Inst, Moscow - Russia
[3] Natl Inst Space Res, Sao Jose Dos Campos - Brazil
Número total de Afiliações: 3
Tipo de documento: Artigo Científico
Fonte: Advances in Space Research; v. 64, n. 1, p. 42-63, JUL 1 2019.
Citações Web of Science: 0
Resumo

The gravity assist is a maneuver greatly applied to space missions, with the main goal of giving or removing energy of a spacecraft through a passage near a celestial body. The patched-conics approximation is the first approximation that is usually considered in the mission planning. It gives a good accuracy in the majority of the situations. However, when using the Moon for the close approach, the results have a tendency to diverge from a more complete three body dynamics. This is due to the large mass of the Moon compared to the Earth. In that sense, the goal of the present paper is to study the errors given by the patched-conics approximation in a lunar gravity assist maneuver. To find those errors we compare the results coming from this approximation with the equivalent results obtained from the circular restricted three body problem and the bi-circular restricted four body problem for a same periselenium condition. This comparison is made in the orbital elements before the maneuver and the C-3 of the spacecraft after the maneuver under the three models considered. Different values for the initial conditions of the spacecraft are used to obtain general conclusions about the behavior of the errors involved. We conclude that there is a tendency to a better agreement between the patched-conics and the three body problem for retrograde transfer orbits. We also find that the effects of the Sun in the maneuver needs to be included only in more accurate steps of the mission. (C) 2019 COSPAR. Published by Elsevier Ltd. All rights reserved. (AU)

Processo FAPESP: 16/24561-0 - A relevância dos pequenos corpos em dinâmica orbital
Beneficiário:Othon Cabo Winter
Linha de fomento: Auxílio à Pesquisa - Temático
Processo FAPESP: 17/20794-2 - Estudo de dinâmica, guiagem e controle aplicado a deflexão de asteroides
Beneficiário:Rodolfo Batista Negri
Linha de fomento: Bolsas no Brasil - Doutorado
Processo FAPESP: 16/18613-7 - Manobras orbitais assistidas por gravidade para missões a asteroides
Beneficiário:Rodolfo Batista Negri
Linha de fomento: Bolsas no Brasil - Mestrado
Processo FAPESP: 15/19880-6 - Projeto Aster: análise de missão para um asteroide triplo
Beneficiário:Antônio Fernando Bertachini de Almeida Prado
Linha de fomento: Auxílio à Pesquisa - Pesquisador Visitante - Internacional
Processo FAPESP: 16/14665-2 - Astrodinâmica aplicada a veículos espaciais
Beneficiário:Antônio Fernando Bertachini de Almeida Prado
Linha de fomento: Auxílio à Pesquisa - Regular