Design of Phasing Trajectories From a Low Lunar Orbit To a Near Rectilinear Halo Orbit

The paper presents three different approaches to the design of a phasing trajectory in a cislunar environment, where the third body perturbation is considered non-negligible. The working framework is the one proposed by the ESA’s Heracles mission in witch the passive target spacecraft -LOP-G- is orbiting on a Near Rectilinear Halo Orbit and the Lunar Ascent Element must reach that orbit from a Low Lunar Parking Orbit to start the rendezvous procedure. In this scenario the authors propose three different ways to design such phasing manoeuvre under the Circular Restricted Three Body Problem hypotheses: Lambert/Differential correction, Hohmann/Differential correction and Optimization. The three approaches are compared in therms ofV consumption, accuracy and time of flight. Finally, a selected solution is also validated under the Restricted Elliptic Three Body Problem Hypotheses