An Earth-Moon Transfer Trajectory Design and Analysis Considering Spacecraft’s Visibility from Daejeon Ground Station at TLI and LOI Maneuvers
The optimal Earth-Moon transfer trajectory considering spacecraft’s visibility from the Daejeon ground station visibility at both the trans lunar injection (TLI) and lunar orbit insertion (LOI) maneuvers is designed. Both the TLI and LOI maneuvers are assumed to be impulsive thrust. As the success...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English |
| Published: |
The Korean Space Science Society
2010-09-01
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| Series: | Journal of Astronomy and Space Sciences |
| Subjects: | |
| Online Access: | http://ocean.kisti.re.kr/downfile/volume/kosss/OJOOBS/2010/v27n3/OJOOBS_2010_v27n3_195.pdf |
| Summary: | The optimal Earth-Moon transfer trajectory considering spacecraft’s visibility from the Daejeon ground station visibility
at both the trans lunar injection (TLI) and lunar orbit insertion (LOI) maneuvers is designed. Both the TLI and LOI maneuvers
are assumed to be impulsive thrust. As the successful execution of the TLI and LOI maneuvers are crucial factors
among the various lunar mission parameters, it is necessary to design an optimal lunar transfer trajectory which guarantees
the visibility from a specified ground station while executing these maneuvers. The optimal Earth-Moon transfer
trajectory is simulated by modifying the Korean Lunar Mission Design Software using Impulsive high Thrust Engine
(KLMDS-ITE) which is developed in previous studies. Four different mission scenarios are established and simulated
to analyze the effects of the spacecraft’s visibility considerations at the TLI and LOI maneuvers. As a result, it is found
that the optimal Earth-Moon transfer trajectory, guaranteeing the spacecraft’s visibility from Daejeon ground station at
both the TLI and LOI maneuvers, can be designed with slight changes in total amount of delta-Vs. About 1% difference is
observed with the optimal trajectory when none of the visibility condition is guaranteed, and about 0.04% with the visibility
condition is only guaranteed at the time of TLI maneuver. The spacecraft’s mass which can delivered to the Moon,
when both visibility conditions are secured is shown to be about 534 kg with assumptions of KSLV-2’s on-orbit mass
about 2.6 tons. To minimize total mission delta-Vs, it is strongly recommended that visibility conditions at both the TLI
and LOI maneuvers should be simultaneously implemented to the trajectory optimization algorithm. |
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| ISSN: | 2093-5587 2093-1409 |