Mathematical Problems in Engineering

Research Article

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

Table 8

Lunar mission, major parameters, ℎ L E O = 4 6 3 km, ℎ L M O = 2 0 0 km.
ModelManeuver Δ 𝑣 T o t a l Δ 𝑣 1 Δ 𝑣 2 𝑇 𝜃 𝐸 𝑃 ( 0 ) 𝐶 Feasibility
( k m / s ) ( k m / s ) ( k m / s ) ( d a y s ) ( d e g ) ( k m 2 / s 2 )
3.8634 3.0658 0.7976 4.571 −116.451 2.4793 Yes
3.8587 3.0649 0.7938 14.322 12.340 2.4974 Yes
ClassicalCounterclockwise 3.8633 3.0657 0.7975 24.004 139.846 2.4797No
PCR3BP 3.8280 3.0593 0.7686 31.912 232.461 2.6166 Yes
3.8230 3.0584 0.7645 40.743 348.876 2.6358 Yes
3.8149 3.0570 0.7579 58.417 229.218 2.6669 Yes
3.8688 3.0686 0.8002 4.769 −113.742 2.4178 Yes
3.8643 3.0678 0.7965 14.981 21.198 2.4355 Yes
ClassicalClockwise 3.8679 3.0685 0.7994 25.121 154.542 2.4212 No
PCR3BP 3.8184 3.0595 0.7589 31.873 232.676 2.6137 Yes
3.8195 3.0597 0.7598 39.664 353.119 2.6094 Yes
3.7709 3.0509 0.7199 58.361 223.886 2.7957 Yes