Abstract A method is presented for designing trajectories from Earth to Earth–Moon L3 halo orbits using dynamical systems theory in the Circular Restricted Three-Body Problem. Stable pseudo-manifold trajectories of L3 halo orbits, which behave in a similar manner to stable invariant manifold trajectories, are mapped and close approaches with the Earth are located. In the three-body model, only two deterministic maneuvers are necessary to complete the transfer; an injection maneuver from Earth orbit onto the stable pseudo-manifold trajectory, and a smaller maneuver to transfer from the pseudo-manifold trajectory onto the halo orbit. The transfers analyzed have of approximately 3.2km/s and flight durations between 44 and 90 days.
Highlights We present a method for designing transfers from Earth to Earth–Moon L3 Orbits. We introduce a pseudo-manifold to enable transfers with durations less than 90 days. All trajectories located utilized at least one lunar flyby. Transfers cost to L3 orbits are comparable to costs required to L1 or L2 orbits.
Transfers to Earth–Moon L3 halo orbits
Acta Astronautica ; 88 ; 116-128
2013-03-04
13 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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