DC Field | Value | Language |
---|---|---|
dc.contributor.author | Lee, Donghun | ko |
dc.contributor.author | Kwon, Jae-Wook | ko |
dc.contributor.author | Bang, Hyochoong | ko |
dc.contributor.author | Kim, Bang-Yeop | ko |
dc.date.accessioned | 2023-10-05T12:00:39Z | - |
dc.date.available | 2023-10-05T12:00:39Z | - |
dc.date.created | 2023-10-05 | - |
dc.date.issued | 2015-08 | - |
dc.identifier.citation | AAS/AIAA Astrodynamics Specialist Conference, ASC 2015, pp.1979 - 1990 | - |
dc.identifier.issn | 1081-6003 | - |
dc.identifier.uri | http://hdl.handle.net/10203/313053 | - |
dc.description.abstract | In this paper, a modified polynomial guidance law is studied for a powered terminal descent of a lunar lander. Also, Zero-Effort-Miss/Zero-Effort-Velocity (ZEM/ZEV) and modified Apollo guidance laws including off-line trajectory optimization approach are analyzed. Because each guidance law has advantages and drawbacks, modified polynomial guidance law is proposed. The modified guidance law is derived quasi-analytically after taking advantages of previous real-time guidance laws for onboard application. In the numerical simulation section, performance will be compared from several points of view such as avoiding surface collision and fuel consumption. | - |
dc.language | English | - |
dc.publisher | Univelt Inc. | - |
dc.title | Modified polynomial guidance law for lunar landing | - |
dc.type | Conference | - |
dc.identifier.wosid | 000387517700115 | - |
dc.identifier.scopusid | 2-s2.0-85007378142 | - |
dc.type.rims | CONF | - |
dc.citation.beginningpage | 1979 | - |
dc.citation.endingpage | 1990 | - |
dc.citation.publicationname | AAS/AIAA Astrodynamics Specialist Conference, ASC 2015 | - |
dc.identifier.conferencecountry | US | - |
dc.identifier.conferencelocation | Vail, CO | - |
dc.contributor.localauthor | Bang, Hyochoong | - |
dc.contributor.nonIdAuthor | Lee, Donghun | - |
dc.contributor.nonIdAuthor | Kwon, Jae-Wook | - |
dc.contributor.nonIdAuthor | Kim, Bang-Yeop | - |
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