Transfers to Earth–Moon L3 halo orbits

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, ar...

Full description

Saved in:
Bibliographic Details
Published in:Acta astronautica 2013-07, Vol.88, p.116-128
Main Authors: Davis, Kathryn, Born, George, Butcher, Eric
Format: Article
Language:English
Subjects:
Dynamical systems
Dynamical systems theory
Earth
Earth-Moon system
Halos
Invariant manifolds
Invariants
Libration point orbits
Maneuvers
Orbit transfers
Orbits
Three-body trajectories
Trajectories
Citations: Items that this one cites
Items that cite this one
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary: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 3.2km/s and flight durations between 44 and 90 days. •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.
ISSN:0094-5765
1879-2030
DOI:10.1016/j.actaastro.2013.03.004