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Transfer orbits in restricted problem

This paper studies transfer orbits in the planar restricted three-body problem. In particular, we are searching for orbits that can be used in two situations: 1) to transfer a spacecraft from one body back to the same body (known in the literature as Henon's problem) and 2) to transfer a spacecraft from one body to the respective Lagrangian points 1,4 and L§. To avoid numerical problems during close approaches, the global Lemaitre regularization is used. Under this model, Henon's problem becomes a Lambert three-body problem. After the simulations, we found orbits to transfer a spacecraft between any two points in the group formed by Earth and the Lagrangian points Z/j, £4, LS (in the Earth-sun system) with near-zero A V (near 10 ~ in canonical units). We also found several orbits that can be used to make a tour to the Lagrangian points for reconnaissance purposes with near-zero AF for the entire tour. The method employed was to solve the two-point boundary value problem for each transfer using the results available from the two-body version of this problem as a first guess.