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Over the past three decades, ballistic and impulsive trajectories between libration
point orbits (LPOs) in the Sun–Earth–Moon system have been investigated to a large extent.
It is known that coupling invariant manifolds of LPOs of two different circular restricted
three-body problems (i.e., the Sun–Earth and the Earth–Moon systems) can lead to significant
mass savings in specific transfers, such as from a low Earth orbit to the Moon’s vicinity.
Previous investigations on this issuemainly considered the use of impulsive maneuvers along
the trajectory. Here we investigate the dynamical effects of replacing impulsive V’s with
low-thrust trajectory arcs to connect LPOs using invariant manifold dynamics. Our investigation
shows that the use of low-thrust propulsion in a particular phase of the transfer and the
adoption of a more realistic Sun–Earth–Moon four-body model can provide better and more
propellant-efficient solution. For this purpose, methods have been developed to compute the
invariant tori and their manifolds in this dynamical model
CitationRen, Y. [et al.]. Optimal low-thrust transfers between libration point orbits. "Celestial mechanics and dynamical astronomy", Gener 2012, vol. 112, núm. 1, p. 1-21.
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