Research Article
Design and Analysis of Direct Abort Orbits in the Earth-Moon Transfer Phase of Crewed Lunar Exploration Missions
Table 3
The results of the single-impulse abort orbit (when
is 0.8).
| | Parameter | (h) | (m/s) | (m/s) | (h) |
| | Preliminary calculation | 4 | (803.70, -629.91, 15.89) | 1021.26 | 55.12 | | Accurate design | 4 | (804.02, -634.27, 17.43) | 1024.23 | 55.12 | | Error | | (0.32, -4.36, 1.54) | 2.97 | 0.00 | | Preliminary calculation | 8 | (747.14, -547.12, -2.50) | 926.05 | 66.08 | | Accurate design | 8 | (747.83, -554.93, -1.87) | 931.24 | 66.08 | | Error | | (0.69, -7.81, 0.63) | 5.19 | 0.00 | | Preliminary calculation | 12 | (696.21, -484.11, -13.91) | 848.09 | 76.27 | | Accurate design | 12 | (716.77, -471.00, 31.80) | 858.26 | 76.27 | | Error | | (20.56, 13.11, 45.71) | 10.17 | 0.00 |
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