Transfers to Earth-Moon L3 halo orbits

Kathryn E. Davis, George H. Born, Masoud Deilami, Annie Larsen, Eric A. Butcher

Research output: Chapter in Book/Report/Conference proceedingConference contribution

12 Scopus citations


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 ΔVs of approximately 3.2 km/s and flight durations as short at 46 days.

Original languageEnglish (US)
Title of host publicationAIAA/AAS Astrodynamics Specialist Conference 2012
StatePublished - 2012
EventAIAA/AAS Astrodynamics Specialist Conference 2012 - Minneapolis, MN, United States
Duration: Aug 13 2012Aug 16 2012

Publication series

NameAIAA/AAS Astrodynamics Specialist Conference 2012


OtherAIAA/AAS Astrodynamics Specialist Conference 2012
Country/TerritoryUnited States
CityMinneapolis, MN

ASJC Scopus subject areas

  • Aerospace Engineering
  • Astronomy and Astrophysics


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