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

Table 3

Lunar mission, clockwise LMO arrival, major parameters.

LMO altitude	Model	Δ𝑣Total	Δ𝑣1	Δ𝑣2	𝑇	𝜃𝐸𝑃(0)	Feasibility
(km)		(km/s)	(km/s)	(km/s)	(days)	(deg)
	Patched-conic	3.8528	3.0683	0.7845	4.936	−113.681	Yes
100	Simplified PCR3BP	3.8811	3.0677	0.8134	4.750	−114.215	Yes
	Classical PCR3BP	3.8829	3.0686	0.8143	4.763	−113.795	Yes
	Miele and Mancuso [12]	3.882	3.068	0.814	4.50	−116.88	—
200	Patched-conic	3.8379	3.0683	0.7696	4.941	−113.638	Yes
	Simplified PCR3BP	3.8670	3.0677	0.7993	4.757	−114.187	Yes
	Classical PCR3BP	3.8688	3.0686	0.8002	4.769	−113.742	Yes
	Miele and Mancuso [12]	3.868	3.068	0.800	4.50	−116.88	—
300	Patched-conic	3.8243	3.0683	0.7560	4.944	−113.608	Yes
	Simplified PCR3BP	3.8541	3.0678	0.7863	4.760	−114.116	Yes
	Classical PCR3BP	3.8559	3.0687	0.7872	4.771	−113.716	Yes
	Miele and Mancuso [12]	3.855	3.068	0.787	4.50	−116.88	—