Application of Periapse Maps for the Design of Trajectories Near the Smaller Primary in Multi-Body Regimes

Figure 12

Low-energy Earth-Moon transfer.

(a) Trajectories at a series of Δ𝑣 values, each oriented for the largest periapse raise; lunar orbital radius marked in green

(b) Sun-Earth initial condition map corresponding to 𝐶=3.000785

(c) Zoom near Earth; 167-km altitude; Earth orbit is green

(d) Initial condition map colored in terms of Δ𝑟_𝑝 over one rev; desired Δ𝑟_𝑝 for Earth-Moon transfer denoted by purple rays; four selected ICs

(e) Four Earth-Moon transfer trajectories correlated to selected points in map (d); Moon’s orbit is green