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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.)

Studying sequences of resonant orbits to perform successive close approaches with the Moon

Texto completo
Autor(es):
Formiga, Jorge Kennety S. [1, 2] ; Prado, Antonio F. B. A. [1]
Número total de Autores: 2
Afiliação do(s) autor(es):
[1] INPE, Natl Inst Space Res, Sao Jose Dos Campos, SP - Brazil
[2] FATEC SJC, Coll Technol, Sao Jose Dos Campos, SP - Brazil
Número total de Afiliações: 2
Tipo de documento: Artigo Científico
Fonte: Journal of the Brazilian Society of Mechanical Sciences and Engineering; v. 37, n. 4, p. 1391-1404, JUL 2015.
Citações Web of Science: 7
Resumo

This research shows a study of the dynamical behavior of a spacecraft that performs a series of close approaches with the Moon. This maneuver is also known in the literature as Gravity-Assisted Maneuver. It is a technique to reduce the fuel expenditure in interplanetary missions by replacing maneuvers based on engines by passages near a massive body. The spacecraft moves under the gravitational attraction of the two bodies that dominate the system, the Earth and the Moon in the present study, and has a negligible mass. The main assumption to study this problem is that the motions are planar everywhere. In particular, we are looking for geometries that allow multiple close approaches without any major correction maneuvers. It means that the only maneuvers allowed are the negligible ones made to force the spacecraft to pass by the Moon with a specified distance from its surface. So, resonant orbits are required to obtain the series of close approaches. Analytical equations are derived to obtain the values of the parameters required to get this sequence of close approaches. The main motivation for this study is the existence of several studies for missions that has the goal of studying the space around the Earth-Moon system using multiple close approaches to make the spacecraft to cover a larger portion of the space without any major maneuver. After obtaining the trajectories, the criterion of Tisserand is used to validate the trajectories found. Then, a verification of the accuracy of the ``patched-conics{''} method for the Earth-Moon system is made. (AU)

Processo FAPESP: 11/08171-3 - Dinâmica orbital de pequenos corpos
Beneficiário:Othon Cabo Winter
Linha de fomento: Auxílio à Pesquisa - Temático
Processo FAPESP: 12/21023-6 - Dinâmica de satélites artificiais
Beneficiário:Rodolpho Vilhena de Moraes
Linha de fomento: Auxílio à Pesquisa - Temático
Processo FAPESP: 14/06688-7 - Dinâmica de satélites artificiais
Beneficiário:Antônio Fernando Bertachini de Almeida Prado
Linha de fomento: Auxílio à Pesquisa - Regular
Processo FAPESP: 11/13101-4 - Estudo de manobras orbitais para escape de colisão de um veículo espacial com grupos de partículas
Beneficiário:Vivian Martins Gomes
Linha de fomento: Auxílio à Pesquisa - Apoio a Jovens Pesquisadores