DC Field | Value | Language |
---|---|---|
dc.contributor.author | Moon, Yongjun | ko |
dc.contributor.author | Park, Chul | ko |
dc.contributor.author | Jo, Sungkwon | ko |
dc.contributor.author | Kwon, Sejin | ko |
dc.date.accessioned | 2014-08-29T04:23:15Z | - |
dc.date.available | 2014-08-29T04:23:15Z | - |
dc.date.created | 2014-06-02 | - |
dc.date.created | 2014-06-02 | - |
dc.date.issued | 2014-02 | - |
dc.identifier.citation | AEROSPACE SCIENCE AND TECHNOLOGY, v.33, no.1, pp.118 - 121 | - |
dc.identifier.issn | 1270-9638 | - |
dc.identifier.uri | http://hdl.handle.net/10203/189069 | - |
dc.description.abstract | Over the last decade, interest has been rekindled on hydrogen peroxide as a rocket propellant. As a result, 1000-N-class H2O2/hydrocarbon bipropellant rocket systems are in a stage requiring a serious exploration for application. Application to orbit-raising maneuvers is proposed here as the most appropriate use of the 1000-N-class thrusters. In this study, optimal design specifications of a 90% H2O2/kerosene rocket system for an apogee kick motor were derived. The optimal design specifications are configured with a thrust of 742 N, a chamber pressure of 11.7 bar, a mixture ratio of 736, and a nozzle expansion ratio of 580. It was found that, in the case of the latest Korean geosynchronous satellite, replacing the current apogee kick motor with the H2O2/kerosene rocket system would result in a mass increase of less than 0.5% of the total mass. (C) 2014 Elsevier Masson SAS. All rights reserved. | - |
dc.language | English | - |
dc.publisher | ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER | - |
dc.subject | HYDROGEN-PEROXIDE | - |
dc.subject | PERFORMANCE | - |
dc.subject | ENGINE | - |
dc.subject | COMBUSTOR | - |
dc.title | Design specifications of H2O2/kerosene bipropellant rocket system for space Missions | - |
dc.type | Article | - |
dc.identifier.wosid | 000334486400013 | - |
dc.identifier.scopusid | 2-s2.0-84898009758 | - |
dc.type.rims | ART | - |
dc.citation.volume | 33 | - |
dc.citation.issue | 1 | - |
dc.citation.beginningpage | 118 | - |
dc.citation.endingpage | 121 | - |
dc.citation.publicationname | AEROSPACE SCIENCE AND TECHNOLOGY | - |
dc.identifier.doi | 10.1016/j.ast.2014.01.006 | - |
dc.embargo.liftdate | 9999-12-31 | - |
dc.embargo.terms | 9999-12-31 | - |
dc.contributor.localauthor | Kwon, Sejin | - |
dc.contributor.nonIdAuthor | Jo, Sungkwon | - |
dc.type.journalArticle | Article | - |
dc.subject.keywordAuthor | H2O2/kerosene bipropellant rocket system | - |
dc.subject.keywordAuthor | Propulsion specifications | - |
dc.subject.keywordAuthor | Apogee kick motor | - |
dc.subject.keywordAuthor | Design optimization | - |
dc.subject.keywordPlus | HYDROGEN-PEROXIDE | - |
dc.subject.keywordPlus | PERFORMANCE | - |
dc.subject.keywordPlus | ENGINE | - |
dc.subject.keywordPlus | COMBUSTOR | - |
Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.