Salazar, F. J. T.
de Melo, C. F.
Macau, E. E. N.
Winter, O. C.
Total Authors: 4
 Inst Nacl Pesquisas Espaciais, BR-12227010 Sao Jose Dos Campos, SP - Brazil
 Univ Fed ABC, BR-09210170 Santo Andre, SP - Brazil
 Univ Estadual Paulista UNESP, Grp Dinam Orbital & Planetol, BR-12516410 Guaratingueta, SP - Brazil
Total Affiliations: 3
CELESTIAL MECHANICS & DYNAMICAL ASTRONOMY;
n. 1-2, SI,
Web of Science Citations:
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)