Dynamics of synodic resonant near rectilinear halo orbits in the bicircular four-body problem

As evidenced by the Global Exploration Roadmap, international interest exists in a new era of human exploration of the solar system. Such an effort is commencing with the examination of options for maintaining a facility-at times crewed-in an orbit nearby the Moon. Thus, the key objectives in advancing colonization of interplanetary space include positioning and maintaining an inhabited facility in a long-term and relatively stable orbit in the lunar vicinity. At this time, one orbit of interest for a habitat spacecraft is a Near Rectilinear Halo Orbit (NRHO). Near rectilinear halo orbits near the Moon are members of the L-1 or L-2 halo orbit families and are characterized by favorable stability properties. As such, they are strong candidates for a future habitat facility in cislunar space. This type of trajectory is identified in cislunar space in terms of the Earth-Moon Circular Restricted Three-Body Problem (CR3BP). However, for arrival to and departure from the Earth-Moon region, the impact of the solar gravity generally cannot be ignored. Thus, the orbital characteristics and stability properties are examined within the context of the bicircular restricted four-body problem. (C) 2020 COSPAR. Published by Elsevier Ltd. All rights reserved.