Lunar soft landing with minimum-mass propulsion system using H2O2/kerosene bipropellant rocket system

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dc.contributor.authorMoon, Yongjunko
dc.contributor.authorKwon, Sejinko
dc.date.accessioned2014-09-01T06:41:23Z-
dc.date.available2014-09-01T06:41:23Z-
dc.date.created2014-06-10-
dc.date.created2014-06-10-
dc.date.issued2014-06-
dc.identifier.citationACTA ASTRONAUTICA, v.99, pp.153 - 157-
dc.identifier.issn0094-5765-
dc.identifier.urihttp://hdl.handle.net/10203/189133-
dc.description.abstractMinimum-mass propulsion specifications using a H2O2/kerosene bipropellant rocket system for a small lunar lander were derived. A multivariable optimization was conducted with propulsion specifications and propellant consumptions obtained by solving optimal control problems for a lunar soft landing. In this paper, the optimal specifications, trajectory, and mass budget are presented.-
dc.languageEnglish-
dc.publisherPERGAMON-ELSEVIER SCIENCE LTD-
dc.titleLunar soft landing with minimum-mass propulsion system using H2O2/kerosene bipropellant rocket system-
dc.typeArticle-
dc.identifier.wosid000335612000014-
dc.identifier.scopusid2-s2.0-84896527343-
dc.type.rimsART-
dc.citation.volume99-
dc.citation.beginningpage153-
dc.citation.endingpage157-
dc.citation.publicationnameACTA ASTRONAUTICA-
dc.identifier.doi10.1016/j.actaastro.2014.02.003-
dc.embargo.liftdate9999-12-31-
dc.embargo.terms9999-12-31-
dc.contributor.localauthorKwon, Sejin-
dc.type.journalArticleArticle-
dc.subject.keywordAuthorH2O2/kerosene bipropellant rocket system-
dc.subject.keywordAuthorPropulsion specifications-
dc.subject.keywordAuthorLunar soft landing-
dc.subject.keywordAuthorDesign optimization-
dc.subject.keywordAuthorOptimal control-
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AE-Journal Papers(저널논문)
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