Transfers to earth-moon L3 halo orbits

Kathryn Davis, George Born, Eric Butcher

Research output: Contribution to journalArticlepeer-review

17 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 L 3 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 between 44 and 90 days.

Original languageEnglish (US)
Pages (from-to)116-128
Number of pages13
JournalActa Astronautica
StatePublished - 2013


  • Dynamical systems theory
  • Invariant manifolds
  • Libration point orbits
  • Orbit transfers
  • Three-body trajectories

ASJC Scopus subject areas

  • Aerospace Engineering


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