Research Article

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

Figure 9

Multiple revolution ascent, counterclockwise LMO arrival, Δ 𝑣 1 = 3 . 0 6 5  km/s, Δ 𝑣 2 = 0 . 8 0 8 2  km/s, 𝑇 = 1 4 . 3 3 days, 𝜃 𝐸 𝑃 ( 0 ) = 1 2 . 4 6 6  deg.
971983.fig.009a
(a) Earth-Moon trajectory, inertial coordinate frame
971983.fig.009b
(b) LEO departure, inertial coordinate frame
971983.fig.009c
(c) LMO arrival, inertial coordinate frame
971983.fig.009d
(d) Earth-Moon trajectory, rotating coordinate frame
971983.fig.009e
(e) LEO departure, rotating coordinate frame
971983.fig.009f
(f) LMO arrival, rotating coordinate frame