Effective stability regions for elliptic NRHOs in the Earth-Moon CR3BP are set by the maximum analytic domain of optimized discrete normal forms, not by exponential drift, for practical mission durations.
Characterizing transition-challenging regions leveraging the elliptic restricted three-body problem: L2 halo orbits
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Effective Stability of Near-Rectilinear Halo Orbits in the Earth-Moon System
Effective stability regions for elliptic NRHOs in the Earth-Moon CR3BP are set by the maximum analytic domain of optimized discrete normal forms, not by exponential drift, for practical mission durations.