Modified polynomial guidance law for lunar landing

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dc.contributor.authorLee, Donghunko
dc.contributor.authorKwon, Jae-Wookko
dc.contributor.authorBang, Hyochoongko
dc.contributor.authorKim, Bang-Yeopko
dc.date.accessioned2023-10-05T12:00:39Z-
dc.date.available2023-10-05T12:00:39Z-
dc.date.created2023-10-05-
dc.date.issued2015-08-
dc.identifier.citationAAS/AIAA Astrodynamics Specialist Conference, ASC 2015, pp.1979 - 1990-
dc.identifier.issn1081-6003-
dc.identifier.urihttp://hdl.handle.net/10203/313053-
dc.description.abstractIn 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.languageEnglish-
dc.publisherUnivelt Inc.-
dc.titleModified polynomial guidance law for lunar landing-
dc.typeConference-
dc.identifier.wosid000387517700115-
dc.identifier.scopusid2-s2.0-85007378142-
dc.type.rimsCONF-
dc.citation.beginningpage1979-
dc.citation.endingpage1990-
dc.citation.publicationnameAAS/AIAA Astrodynamics Specialist Conference, ASC 2015-
dc.identifier.conferencecountryUS-
dc.identifier.conferencelocationVail, CO-
dc.contributor.localauthorBang, Hyochoong-
dc.contributor.nonIdAuthorLee, Donghun-
dc.contributor.nonIdAuthorKwon, Jae-Wook-
dc.contributor.nonIdAuthorKim, Bang-Yeop-
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AE-Conference Papers(학술회의논문)
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