Abstract
The aim of this study is to explore the space environment near the Lagrange points (L3–L5) in cislunar space using 3:1/3:2 resonant orbital families that can travel in the vicinity of L3–L5. First, the planar and spatial 3:1/3:2 resonant orbital families symmetrical about the x-axis are computed using the continuation method in the circular restricted Earth-Moon three-body problem. Then, the characteristics of the two resonant orbital families are analyzed, including the variation in Kepler orbital elements, apogee direction, Jacobian constant, and distances from apogees to L3–L5 as well as the orbital stability analyzed by the dynamic theory. Furthermore, the correlation between shadow duration and orbit inclination including the strategy for shadow avoidance are proposed based on the Sun-Earth-Moon bicircular restricted four-body problem. The advantages of 3:1/3:2 resonant orbits used in this study are stability, shadow avoidance and L3–L5 tour capability, and potential applications in the cislunar space.
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