Optimal Two-Impulse Trajectories with Moderate Flight Time for Earth-Moon Missions

Figure 17

Multiple revolution ascent, clockwise LMO arrival, Δ𝑣₁=3.0586 km/s, Δ𝑣₂=0.7702 km/s, 𝑇=40.713 days, 𝜃_𝐸𝑃(0)=349.322 deg.

(a) Earth-Moon trajectory, inertial coordinate frame

(b) LEO departure, inertial coordinate frame

(c) LMO arrival, inertial coordinate frame

(d) Earth-Moon trajectory, rotating coordinate frame

(e) LEO departure, rotating coordinate frame

(f) LMO arrival, rotating coordinate frame