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

Table 2

The results of the single-impulse abort orbit (when is 0.4).

Parameter	(h)	(m/s)	(m/s)	(h)
Preliminary calculation	4	(1263.92, -978.84, 19.71)	1598.75	35.21
Accurate design	4	(1264.82, -980.59, 20.12)	1600.54	35.21
Error		(0.90, -1.75, 0.41)	1.79	0.00
Preliminary calculation	8	(1159.82, -839.36, -8.37)	1431.71	43.72
Accurate design	8	(1161.75, -842.22, -7.72)	1434.94	43.72
Error		(1.93, -2.86, 0.65)	3.23	0.00
Preliminary calculation	12	(1073.05, -737.20, -25.48)	1302.13	51.83
Accurate design	12	(1076.54, -741.80, -25.18)	1307.60	51.83
Error		(3.49, -4.60, 0.30)	5.47	0.00