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

Table 4

The results of the two-impulse abort orbits (when the maximum abort return time is 1.5 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	(987.67, -769.25, 17.35)	1252.01	9.57	(23.41, -14.80, -1.13)	27.72	1279.73	44.56
Accurate design	4	(988.30, -770.57, 18.18)	1253.33	9.57	(23.55, -16.02, -0.62)	28.49	1281.82	44.56
Error		(0.63, -1.32, 0.83)	1.32	0.00	(0.14, -1.22, 0.51)	0.77	2.09	0.00
Preliminary calculation	8	(909.20, -661.83, -4.83)	1124.58	13.56	(2.45, -1.43, -0.17)	2.84	1127.42	55.15
Accurate design	8	(910.68, -664.02, -4.24)	1127.07	13.56	(2.86, -3.37, 1.82)	4.78	1131.85	55.15
Error		(1.48, -2.19, 0.59)	2.49	0.00	(0.41, -1.94, 1.99)	1.94	4.43	0.00
Preliminary calculation	12	(795.42, -550.75, -16.96)	967.63	1.93	(14.88, -9.77, -0.56)	17.81	985.44	67.00
Accurate design	12	(799.84, -565.67, -14.91)	979.77	1.93	(12.10, -3.33, -1.56)	12.64	992.41	67.00
Error		(4.32, -14.92, 2.05)	12.14	0.00	(-2.78, 6.44, -1.00)	-5.17	6.97	0.00