Phasing Maneuver Analysis from a Low Lunar Orbit to a Near Rectilinear Halo Orbit

The paper describes the preliminary design of a phasing trajectory in cislunar environment, where third body perturbation is considered non-negligible. working framework one proposed by ESA’s Heracles mission which passive target station Near Rectilinear Halo Orbit and an active vehicle must reach that orbit to start rendezvous procedure. In this scenario authors examine three different ways such maneuver under circular restricted three-body problem hypotheses: Lambert/differential correction, Hohmann/differential correction optimization. approaches are compared terms ?V consumption, accuracy time flight. selected solution also validated more accurate elliptic hypothesis.