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

Autor(es)

Salazar, F. J. T. ; de Melo, C. F. ; Macau, E. E. N. ; Winter, O. C.

• Tipo de documento: Artigo Científico
• Fonte: CELESTIAL MECHANICS & DYNAMICAL ASTRONOMY; v. 114, n. 1-2, p. 13-pg., 2012-10-01.

Resumo

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)

• Processo FAPESP: 08/06066-5 - Análise e controle de caos da dinâmica de movimento coletivo de satélites em vôo de formação
• Beneficiário: Francisco Javier Tipán Salazar
• Modalidade de apoio: Bolsas no Brasil - Doutorado