원주 제한 삼체문제에서의 저추력 달 포착 궤도 설계Low Thrust Lunar Capture Trajectory design in Circular Restricted Three body Problem
| DC Field | Value | Language |
|---|---|---|
| dc.contributor.author | 이진성 | ko |
| dc.contributor.author | 권혁준 | ko |
| dc.contributor.author | 안재명 | ko |
| dc.contributor.author | 방효충 | ko |
| dc.contributor.author | 이상현 | ko |
| dc.date.accessioned | 2021-08-10T08:10:46Z | - |
| dc.date.available | 2021-08-10T08:10:46Z | - |
| dc.date.created | 2021-08-10 | - |
| dc.date.issued | 2020-07-10 | - |
| dc.identifier.citation | 한국항공우주학회 2020년도 춘계학술대회, pp.672 - 673 | - |
| dc.identifier.uri | http://hdl.handle.net/10203/287124 | - |
| dc.description.abstract | In this paper, low thrust spacecraft trajectory optimization for the lunar capture trajectory in the circular restricted threebody problem (CRTBP) is presented. Explanations of the controlled motion of the satellite under the dynamics of CRTBP are presented with the application of the Hills region and Jacobi constant in the trajectory optimization. The initial orbit of the spacecraft of interest is assumed to be a geosynchronous transfer orbit (GTO) with a semi-major axis of 43444km and eccentricity of 0.8. | - |
| dc.language | Korean | - |
| dc.publisher | 한국항공우주학회 | - |
| dc.title | 원주 제한 삼체문제에서의 저추력 달 포착 궤도 설계 | - |
| dc.title.alternative | Low Thrust Lunar Capture Trajectory design in Circular Restricted Three body Problem | - |
| dc.type | Conference | - |
| dc.type.rims | CONF | - |
| dc.citation.beginningpage | 672 | - |
| dc.citation.endingpage | 673 | - |
| dc.citation.publicationname | 한국항공우주학회 2020년도 춘계학술대회 | - |
| dc.identifier.conferencecountry | KO | - |
| dc.identifier.conferencelocation | 델피노 골프앤리조트 | - |
| dc.contributor.localauthor | 안재명 | - |
| dc.contributor.localauthor | 방효충 | - |
| dc.contributor.nonIdAuthor | 권혁준 | - |
| dc.contributor.nonIdAuthor | 이상현 | - |
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