Design and Analysis of Direct Abort Orbits in the Earth-Moon Transfer Phase of Crewed Lunar Exploration Missions

Table 5

The results of the two-impulse abort orbits (when the maximum abort return time is 1.25 times the minimum return time of a single-impulse abort orbit).

Parameter	(h)	(m/s)	(m/s)	(h)	(m/s)	(m/s)	(m/s)	(h)
Preliminary calculation	4	(1175.60, -911.82, 18.95)	1487.89	1.91	(31.14, -22.76, -0.12)	38.57	1526.46	37.03
Accurate design	4	(1175.85, -912.75, 19.39)	1488.67	1.91	(31.32, -23.67, 0.23)	39.25	1527.92	37.03
Error		(0.25, -0.93, 0.44)	0.78	0.00	(0.18, -0.91, 0.35)	0.68	1.46	0.00
Preliminary calculation	8	(1081.84, -784.20, -7.24)	1336.19	7.57	(0.51, -0.32, -0.02)	0.60	1336.79	46.76
Accurate design	8	(1082.84, -785.77, -5.82)	1337.91	7.57	(0.93, -1.75, 0.49)	2.04	1339.95	46.76
Error		(1.00, -1.57, 1.42)	1.72	0.00	(0.42, -1.43, 0.51)	1.44	3.16	0.00
Preliminary calculation	12	(987.37, -679.81, -22.79)	1198.98	7.87	(5.11, -3.13, -0.29)	6.00	1204.98	55.79
Accurate design	12	(988.97, -682.49, -22.06)	1201.81	7.87	(6.00, -5.58, 1.14)	8.28	1210.09	55.79
Error		(1.60, -2.68, 0.73)	2.83	0.00	(0.89, 2.45, 1.43)	2.28	5.11	0.00