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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.)

A study of Earth-Moon trajectories based on analytical expressions for the velocity increments

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Autor(es):
Gagg Filho, Luiz Arthur [1] ; Fernandes, Sandro da Silva [1]
Número total de Autores: 2
Afiliação do(s) autor(es):
[1] Inst Tecnol Aeronaut, Dept Matemat, Praca Marechal Eduardo Gomes 50, BR-12228900 Sao Jose Dos Campos, SP - Brazil
Número total de Afiliações: 1
Tipo de documento: Artigo Científico
Fonte: COMPUTATIONAL & APPLIED MATHEMATICS; v. 37, n. 1, SI, p. 338-364, DEC 2018.
Citações Web of Science: 0
Resumo

A study of Earth-Moon bi-impulsive trajectories is presented in this paper. The motion of the space vehicle is described by the classic planar circular restricted three-body problem. The velocity increments are computed through analytical expressions, which are derived from the development of the Jacobi Integral expression. To determine the trajectories, a new two-point boundary value problem (TPBVP) with prescribed value of Jacobi Integral is formulated. Internal and external trajectories are determined through the solution of this new TPBVP for several times of flight. A relation between the Jacobi Integral and the Kepler's energy at arrival is derived and several kinds of study are performed. Critical values of the Jacobi Integral, for which the Kepler's energy of the space vehicle on the arrival trajectory becomes negative, are calculated for several configurations of arrival at the low Moon orbit in both directions: clockwise and counterclockwise. Results show that the proposed method allows the estimation of the fuel consumption before solving the TPBVP, and it facilitates the determination of trajectories with large time of flight. However, increasing values of the time of flight are not necessarily related with the increase of the Jacobi Integral value, which means that the obtaining of new trajectories becomes more difficult as the Jacobi Integral increases. Moreover, the proposed method provides results to be used as initial guess for more complex models and for optimization algorithms in order to minimize the total fuel consumption. For this case, this paper presents an example where an internal trajectory with large time of flight is optimized considering the Sun's attraction. (AU)

Processo FAPESP: 12/25308-5 - Determinação de trajetórias ótimas na dinâmica do problema restrito de três ou quatro corpos
Beneficiário:Luiz Arthur Gagg Filho
Linha de fomento: Bolsas no Brasil - Doutorado
Processo FAPESP: 12/21023-6 - Dinâmica de satélites artificiais
Beneficiário:Rodolpho Vilhena de Moraes
Linha de fomento: Auxílio à Pesquisa - Temático