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

Table 5

Lunar mission, major parameters, ℎ_LEO=463km, ℎ_LMO=200km.

Model	Maneuver	Δ𝑣Total	Δ𝑣1	Δ𝑣2	𝑇	𝜃𝐸𝑃(0)	Feasibility
		(km/s)	(km/s)	(km/s)	(days)	(deg)
		3.8614	3.0648	0.7966	4.562	−116.832	Yes
		3.8635	3.0653	0.7983	14.168	9.002	Yes
Simplified	Counterclockwise	3.8602	3.0646	0.7956	23.811	135.376	Yes
PCR3BP		3.8263	3.0585	0.7678	32.110	232.270	Yes
		3.8296	3.0591	0.7705	40.873	347.204	Yes
		3.7826	3.0506	0.7320	58.398	216.284	Yes
		3.8670	3.0677	0.7993	4.753	−114.187	Yes
		3.8688	3.0681	0.8007	14.798	17.390	Yes
Simplified	Clockwise	3.8643	3.0672	0.7971	24.930	150.050	Yes
PCR3BP		3.8167	3.0586	0.7581	32.080	232.475	Yes
		3.8200	3.0592	0.7608	40.863	347.613	Yes
		3.7679	3.0498	0.7181	58.530	220.726	Yes