Mission Orbit Design of CubeSat Impactor Measuring Lunar Local
The current study designs the mission orbit of the lunar CubeSat spacecraft to measure the lunar local magnetic anomaly. To perform this mission, the CubeSat will impact the lunar surface over the Reiner Gamma swirl on the Moon. Orbit analyses are conducted comprising ΔV and error propagation anal...
| Main Authors: | , , , , , |
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| Format: | Article |
| Language: | English |
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The Korean Space Science Society
2017-06-01
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| Series: | Journal of Astronomy and Space Sciences |
| Subjects: | |
| Online Access: | http://ocean.kisti.re.kr/downfile/volume/kosss/OJOOBS/2017/v34n2/OJOOBS_2017_v34n2_127.pdf |
| _version_ | 1797330832994598912 |
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| author | Jeong-Ah Lee Sang-Young Park Youngkwang Kim Jonghee Bae Donghun Lee Gwanghyeok Ju |
| author_facet | Jeong-Ah Lee Sang-Young Park Youngkwang Kim Jonghee Bae Donghun Lee Gwanghyeok Ju |
| author_sort | Jeong-Ah Lee |
| collection | DOAJ |
| description | The current study designs the mission orbit of the lunar CubeSat spacecraft to measure the lunar local magnetic anomaly.
To perform this mission, the CubeSat will impact the lunar surface over the Reiner Gamma swirl on the Moon. Orbit
analyses are conducted comprising ΔV and error propagation analysis for the CubeSat mission orbit. First, three possible
orbit scenarios are presented in terms of the CubeSat’s impacting trajectories. For each scenario, it is important to achieve
mission objectives with a minimum ΔV since the CubeSat is limited in size and cost. Therefore, the ΔV needed for the
CubeSat to maneuver from the initial orbit toward the impacting trajectory is analyzed for each orbit scenario. In addition,
error propagation analysis is performed for each scenario to evaluate how initial errors, such as position error, velocity
error, and maneuver error, that occur when the CubeSat is separated from the lunar orbiter, eventually affect the final
impact position. As a result, the current study adopts a CubeSat release from the circular orbit at 100 km altitude and an
impact slope of 15°, among the possible impacting scenarios. For this scenario, the required ΔV is calculated as the result of
the ΔV analysis. It can be used to practically make an estimate of this specific mission’s fuel budget. In addition, the current
study suggests error constraints for ΔV for the mission. |
| first_indexed | 2024-03-08T07:26:09Z |
| format | Article |
| id | doaj.art-5a1900a4bef242abbb463097a5442419 |
| institution | Directory Open Access Journal |
| issn | 2093-5587 2093-1409 |
| language | English |
| last_indexed | 2024-03-08T07:26:09Z |
| publishDate | 2017-06-01 |
| publisher | The Korean Space Science Society |
| record_format | Article |
| series | Journal of Astronomy and Space Sciences |
| spelling | doaj.art-5a1900a4bef242abbb463097a54424192024-02-02T21:50:10ZengThe Korean Space Science SocietyJournal of Astronomy and Space Sciences2093-55872093-14092017-06-0134212713810.5140/JASS.2017.34.2.127Mission Orbit Design of CubeSat Impactor Measuring Lunar LocalJeong-Ah Lee0Sang-Young Park1Youngkwang Kim2Jonghee Bae3Donghun Lee4Gwanghyeok Ju5Department of Astronomy, Yonsei University, Seoul 03722, KoreaDepartment of Astronomy, Yonsei University, Seoul 03722, KoreaDepartment of Astronomy, Yonsei University, Seoul 03722, Koreaorea Aerospace Research Institute, Daejeon 34133, KoreaKorea Aerospace Research Institute, Daejeon 34133, KoreaKorea Aerospace Research Institute, Daejeon 34133, KoreaThe current study designs the mission orbit of the lunar CubeSat spacecraft to measure the lunar local magnetic anomaly. To perform this mission, the CubeSat will impact the lunar surface over the Reiner Gamma swirl on the Moon. Orbit analyses are conducted comprising ΔV and error propagation analysis for the CubeSat mission orbit. First, three possible orbit scenarios are presented in terms of the CubeSat’s impacting trajectories. For each scenario, it is important to achieve mission objectives with a minimum ΔV since the CubeSat is limited in size and cost. Therefore, the ΔV needed for the CubeSat to maneuver from the initial orbit toward the impacting trajectory is analyzed for each orbit scenario. In addition, error propagation analysis is performed for each scenario to evaluate how initial errors, such as position error, velocity error, and maneuver error, that occur when the CubeSat is separated from the lunar orbiter, eventually affect the final impact position. As a result, the current study adopts a CubeSat release from the circular orbit at 100 km altitude and an impact slope of 15°, among the possible impacting scenarios. For this scenario, the required ΔV is calculated as the result of the ΔV analysis. It can be used to practically make an estimate of this specific mission’s fuel budget. In addition, the current study suggests error constraints for ΔV for the mission.http://ocean.kisti.re.kr/downfile/volume/kosss/OJOOBS/2017/v34n2/OJOOBS_2017_v34n2_127.pdflunar CubeSatdelta-verror propagationlunar explorationlunar magnetic anomaly |
| spellingShingle | Jeong-Ah Lee Sang-Young Park Youngkwang Kim Jonghee Bae Donghun Lee Gwanghyeok Ju Mission Orbit Design of CubeSat Impactor Measuring Lunar Local Journal of Astronomy and Space Sciences lunar CubeSat delta-v error propagation lunar exploration lunar magnetic anomaly |
| title | Mission Orbit Design of CubeSat Impactor Measuring Lunar Local |
| title_full | Mission Orbit Design of CubeSat Impactor Measuring Lunar Local |
| title_fullStr | Mission Orbit Design of CubeSat Impactor Measuring Lunar Local |
| title_full_unstemmed | Mission Orbit Design of CubeSat Impactor Measuring Lunar Local |
| title_short | Mission Orbit Design of CubeSat Impactor Measuring Lunar Local |
| title_sort | mission orbit design of cubesat impactor measuring lunar local |
| topic | lunar CubeSat delta-v error propagation lunar exploration lunar magnetic anomaly |
| url | http://ocean.kisti.re.kr/downfile/volume/kosss/OJOOBS/2017/v34n2/OJOOBS_2017_v34n2_127.pdf |
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