Celestial Mechanics and Dynamical Astronomy

, Volume 114, Issue 1–2, pp 201–213 | Cite as

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

  • F. J. T. Salazar
  • C. F. de Melo
  • E. E. N. Macau
  • O. C. Winter
Original Article


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.


Alternative transfers Stable Lagrangian points L4 L5 Three-body problem Trajectories-G 


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Copyright information

© Springer Science+Business Media B.V. 2012

Authors and Affiliations

  • F. J. T. Salazar
    • 1
  • C. F. de Melo
    • 2
  • E. E. N. Macau
    • 1
  • O. C. Winter
    • 3
  1. 1.Instituto Nacional de Pesquisas EspaciaisSão José dos CamposBrazil
  2. 2.Universidade Federal do ABCSanto AndréBrazil
  3. 3.Univ Estadual Paulista—UNESP, Grupo de Dinâmica Orbital e PlanetologiaGuaratinguetáBrazil

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