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

Salazar, F. J. T.de Melo, C. F.Macau, E. E. N.Winter, O. C. [UNESP]2014-05-202014-05-202012-10-01Celestial Mechanics & Dynamical Astronomy. Dordrecht: Springer, v. 114, n. 1-2, p. 201-213, 2012.0923-2958http://hdl.handle.net/11449/39862An 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.201-213engAlternative transfersStable Lagrangian pointsL4L5Three-body problemTrajectories-GThree-body problem, its Lagrangian points and how to exploit them using an alternative transfer to L4 and L5Artigo10.1007/s10569-012-9426-yWOS:000309864700009Acesso restrito0960024575647258