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

Table 7

Lunar mission, major parameters, ℎ_LEO=463km, ℎ_LMO=100km.

Model	Maneuver	Δ𝑣Total	Δ𝑣1	Δ𝑣2	𝑇	𝜃𝐸𝑃(0)	𝐶	Feasibility
		(km/s)	(km/s)	(km/s)	(days)	(deg)	(km^2/s^2)
		3.8777	3.0658	0.8119	4.573	−116.410	2.4784	Yes
		3.8732	3.0650	0.8082	14.330	12.466	2.4965	Yes
Classical	Counterclockwise	3.8776	3.0658	0.8118	24.019	140.054	2.4788	No
PCR3BP		3.8428	3.0593	0.7835	31.910	232.464	2.6166	Yes
		3.8379	3.0584	0.7795	40.742	348.882	2.6358	Yes
		3.8300	3.0570	0.7730	58.415	229.239	2.6668	Yes
		3.8829	3.0686	0.8143	4.763	−113.795	2.4187	Yes
		3.8785	3.0678	0.8107	14.970	21.069	2.4363	Yes
Classical	Clockwise	3.8821	3.0684	0.8136	25.103	154.315	2.4220	No
PCR3BP		3.8337	3.0595	0.7742	31.872	232.674	2.6138	Yes
		3.8288	3.0586	0.7702	40.713	349.322	2.6331	Yes
		3.7893	3.0513	0.7380	58.420	224.480	2.7871	Yes