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

Table 9

Lunar mission, major parameters, ℎ_LEO=463km, ℎ_LMO=300km.

Model	Maneuver	Δ𝑣Total	Δ𝑣1	Δ𝑣2	𝑇	𝜃𝐸𝑃(0)	𝐶	Feasibility
		(km/s)	(km/s)	(km/s)	(days)	(deg)	(km^2/s^2)
		3.8502	3.0657	0.7845	4.569	−116.491	2.4802	Yes
		3.8455	3.0649	0.7806	14.313	12.213	2.4983	Yes
Classical	Counterclockwise	3.8501	3.0657	0.7844	23.990	139.643	2.4806	No
PCR3BP		3.8144	3.0593	0.7551	31.913	232.461	2.6166	Yes
		3.8093	3.0584	0.7509	40.745	348.870	2.6359	Yes
		3.8010	3.0570	0.7441	58.422	229.235	2.6671	Yes
		3.8559	3.0687	0.7872	4.771	−113.716	2.4170	Yes
		3.8513	3.0678	0.7834	14.992	21.336	2.4346	Yes
Classical	Clockwise	3.8550	3.0685	0.7865	25.139	154.757	2.4204	No
	PCR3BP	3.8043	3.0595	0.7448	31.873	232.676	2.6137	Yes
		3.8054	3.0597	0.7458	39.665	353.111	2.6094	Yes
		3.7559	3.0509	0.7050	58.361	223.913	2.7957	Yes