Abstract
For the sake of space mission design, it is indispensable to develop low-energy trajectories from the viewpoint of fuel cost. As one of the approaches to such low-energy trajectories, the Coupled Planar Restricted Circular Three-Body Problem(PRC3BP) was proposed by using the tube dynamics associated with unstable Lagrange points. In this paper, we show how the low-energy trajectory from the vicinity of Earth to Lyapunov orbit around L2 in Sun-Earth-spacecraft system can be developed by coupling Sun-Earth-spacecraft and Earth-Moon-spacecraft PRCSBPs, and we specifically consider the regions of prevalence to detect the effective areas of the PRC3BP.
