Preliminary Analysis of Delta-V Requirements for a Lunar CubeSat Impactor with Deployment Altitude Variations
Characteristics of delta-V requirements for deploying an impactor from a mother-ship at different orbital altitudes are analyzed in order to prepare for a future lunar CubeSat impactor mission. A mother-ship is assumed to be orbiting the moon with a circular orbit at a 90 deg inclination and havin...
| Main Authors: | , , |
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| Format: | Article |
| Language: | English |
| Published: |
The Korean Space Science Society
2015-09-01
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| Series: | Journal of Astronomy and Space Sciences |
| Subjects: | |
| Online Access: | http://ocean.kisti.re.kr/downfile/volume/kosss/OJOOBS/2015/v32n3/OJOOBS_2015_v32n3_257.pdf |
| _version_ | 1797369729778712576 |
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| author | Young-Joo Song Jin Ho Bang-Yeop Kim |
| author_facet | Young-Joo Song Jin Ho Bang-Yeop Kim |
| author_sort | Young-Joo Song |
| collection | DOAJ |
| description | Characteristics of delta-V requirements for deploying an impactor from a mother-ship at different orbital altitudes are
analyzed in order to prepare for a future lunar CubeSat impactor mission. A mother-ship is assumed to be orbiting the
moon with a circular orbit at a 90 deg inclination and having 50, 100, 150, 200 km altitudes. Critical design parameters that
are directly related to the success of the impactor mission are also analyzed including deploy directions, CubeSat flight
time, impact velocity, and associated impact angles. Based on derived delta-V requirements, required thruster burn time
and fuel mass are analyzed by adapting four different miniaturized commercial onboard thrusters currently developed for
CubeSat applications. As a result, CubeSat impact trajectories as well as thruster burn characteristics deployed at different
orbital altitudes are found to satisfy the mission objectives. It is concluded that thrust burn time should considered as the
more critical design parameter than the required fuel mass when deducing the onboard propulsion system requirements.
Results provided through this work will be helpful in further detailed system definition and design activities for future lunar
missions with a CubeSat-based payload. |
| first_indexed | 2024-03-08T17:51:06Z |
| format | Article |
| id | doaj.art-689be4f83a2147ec982c584fb0270ba1 |
| institution | Directory Open Access Journal |
| issn | 2093-5587 2093-1409 |
| language | English |
| last_indexed | 2024-03-08T17:51:06Z |
| publishDate | 2015-09-01 |
| publisher | The Korean Space Science Society |
| record_format | Article |
| series | Journal of Astronomy and Space Sciences |
| spelling | doaj.art-689be4f83a2147ec982c584fb0270ba12024-01-02T07:48:21ZengThe Korean Space Science SocietyJournal of Astronomy and Space Sciences2093-55872093-14092015-09-0132325726810.5140/JASS.2015.32.3.257Preliminary Analysis of Delta-V Requirements for a Lunar CubeSat Impactor with Deployment Altitude VariationsYoung-Joo Song0Jin Ho1Bang-Yeop Kim2Lunar Exploration Mission Team, Korea Aerospace Research Institute, Daejeon 34133, KoreaSchool of Space Research, Kyung Hee University, Yongin 17104, KoreaLunar Exploration Mission Team, Korea Aerospace Research Institute, Daejeon 34133, KoreaCharacteristics of delta-V requirements for deploying an impactor from a mother-ship at different orbital altitudes are analyzed in order to prepare for a future lunar CubeSat impactor mission. A mother-ship is assumed to be orbiting the moon with a circular orbit at a 90 deg inclination and having 50, 100, 150, 200 km altitudes. Critical design parameters that are directly related to the success of the impactor mission are also analyzed including deploy directions, CubeSat flight time, impact velocity, and associated impact angles. Based on derived delta-V requirements, required thruster burn time and fuel mass are analyzed by adapting four different miniaturized commercial onboard thrusters currently developed for CubeSat applications. As a result, CubeSat impact trajectories as well as thruster burn characteristics deployed at different orbital altitudes are found to satisfy the mission objectives. It is concluded that thrust burn time should considered as the more critical design parameter than the required fuel mass when deducing the onboard propulsion system requirements. Results provided through this work will be helpful in further detailed system definition and design activities for future lunar missions with a CubeSat-based payload.http://ocean.kisti.re.kr/downfile/volume/kosss/OJOOBS/2015/v32n3/OJOOBS_2015_v32n3_257.pdflunar cubesat impactorDelta-Vimpact trajectory |
| spellingShingle | Young-Joo Song Jin Ho Bang-Yeop Kim Preliminary Analysis of Delta-V Requirements for a Lunar CubeSat Impactor with Deployment Altitude Variations Journal of Astronomy and Space Sciences lunar cubesat impactor Delta-V impact trajectory |
| title | Preliminary Analysis of Delta-V Requirements for a Lunar CubeSat Impactor with Deployment Altitude Variations |
| title_full | Preliminary Analysis of Delta-V Requirements for a Lunar CubeSat Impactor with Deployment Altitude Variations |
| title_fullStr | Preliminary Analysis of Delta-V Requirements for a Lunar CubeSat Impactor with Deployment Altitude Variations |
| title_full_unstemmed | Preliminary Analysis of Delta-V Requirements for a Lunar CubeSat Impactor with Deployment Altitude Variations |
| title_short | Preliminary Analysis of Delta-V Requirements for a Lunar CubeSat Impactor with Deployment Altitude Variations |
| title_sort | preliminary analysis of delta v requirements for a lunar cubesat impactor with deployment altitude variations |
| topic | lunar cubesat impactor Delta-V impact trajectory |
| url | http://ocean.kisti.re.kr/downfile/volume/kosss/OJOOBS/2015/v32n3/OJOOBS_2015_v32n3_257.pdf |
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