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

Table 2

Lunar mission, counterclockwise LMO arrival, major parameters.

LMO altitude	Model	Δ𝑣Total	Δ𝑣1	Δ𝑣2	𝑇	𝜃𝐸𝑃(0)	Feasibility
(km)		(km/s)	(km/s)	(km/s)	(days)	(deg)
100	Patched-conic	3.8482	3.0655	0.7827	4.794	−115.723	Yes
	Simplified PCR3BP	3.8758	3.0649	0.8109	4.564	−116.800	Yes
	Classical PCR3BP	3.8777	3.0658	0.8119	4.573	−116.410	Yes
	Miele and Mancuso [12]	3.876	3.065	0.811	4.37	−118.98	—
200	Patched-conic	3.8331	3.0654	0.7677	4.794	−115.750	Yes
	Simplified PCR3BP	3.8614	3.0648	0.7966	4.562	−116.832	Yes
	Classical PCR3BP	3.8634	3.0658	0.7976	4.571	−116.451	Yes
	Miele and Mancuso [12]	3.862	3.065	0.797	4.37	−119.00	—
300	Patched-conic	3.8194	3.0654	0.7540	4.793	−115.777	Yes
	Simplified PCR3BP	3.8483	3.0648	0.7835	4.560	−116.881	Yes
	Classical PCR3BP	3.8502	3.0657	0.7845	4.569	−116.491	Yes
	Miele and Mancuso [12]	3.849	3.065	0.784	4.37	−119.03	—