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(Reference retrieved automatically from Web of Science through information on FAPESP grant and its corresponding number as mentioned in the publication by the authors.)

Three-body problem, its Lagrangian points and how to exploit them using an alternative transfer to L4 and L5

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Author(s):
Salazar, F. J. T. [1] ; de Melo, C. F. [2] ; Macau, E. E. N. [1] ; Winter, O. C. [3]
Total Authors: 4
Affiliation:
[1] Inst Nacl Pesquisas Espaciais, BR-12227010 Sao Jose Dos Campos, SP - Brazil
[2] Univ Fed ABC, BR-09210170 Santo Andre, SP - Brazil
[3] Univ Estadual Paulista UNESP, Grp Dinam Orbital & Planetol, BR-12516410 Guaratingueta, SP - Brazil
Total Affiliations: 3
Document type: Journal article
Source: CELESTIAL MECHANICS & DYNAMICAL ASTRONOMY; v. 114, n. 1-2, SI, p. 201-213, OCT 2012.
Web of Science Citations: 14
Abstract

An alternative transfer strategy to send spacecraft to stable orbits around the Lagrangian equilibrium points L4 and L5 based in trajectories derived from the periodic orbits around L1 is presented in this work. The trajectories derived, called Trajectories G, are described and studied in terms of the initial generation requirements and their energy variations relative to the Earth through the passage by the lunar sphere of influence. Missions for insertion of spacecraft in elliptic orbits around L4 and L5 are analysed considering the restricted three-body problem Earth-Moon-particle and the results are discussed starting from the thrust, time of flight and energy variation relative to the Earth. (AU)

FAPESP's process: 08/06066-5 - Controlling chaos and analysis of the dynamics of collective motion of satellite in formation flight
Grantee:Francisco Javier Tipán Salazar
Support type: Scholarships in Brazil - Doctorate