DC Field | Value | Language |
---|---|---|
dc.contributor.author | Huh, Jeongmoo | ko |
dc.contributor.author | Jyoti, Botchu V. S. | ko |
dc.contributor.author | Yun, Yongtae | ko |
dc.contributor.author | Shoaib, M. N. | ko |
dc.contributor.author | Kwon, Sejin | ko |
dc.date.accessioned | 2019-04-15T14:33:43Z | - |
dc.date.available | 2019-04-15T14:33:43Z | - |
dc.date.created | 2019-03-18 | - |
dc.date.created | 2019-03-18 | - |
dc.date.issued | 2018-12 | - |
dc.identifier.citation | INTERNATIONAL JOURNAL OF AEROSPACE ENGINEERING | - |
dc.identifier.issn | 1687-5966 | - |
dc.identifier.uri | http://hdl.handle.net/10203/254169 | - |
dc.description.abstract | In regard to propulsion system applications, the stability of liquid propellants in long-term storage is of increasing importance, and this had led to a greater interest in gelation technology. As part of a preliminary test to determine the feasibility of using a gel propellant in a rocket with a catalyst bed, a hybrid rocket with a catalyst reactor using a gel propellant as an oxidizer was tested for the first time in this study. Experiments were conducted with two different oxidizers: one with liquid phase hydrogen peroxide and the other with gel phase hydrogen peroxide, as well as high-density polyethylene as fuel for a 250N class hybrid thruster performance test. The thruster was designed with the catalyst ignition system, and a catalyst was manufactured to be inserted into the catalyst reactor to facilitate oxidizer decomposition. While the test result with neat hydrogen peroxide indicated sufficient decomposition efficiency using a manganese dioxide/alumina catalyst and successful autoignition of the fuel via the decomposed product, gel hydrogen peroxide exhibited insufficient decomposition and there were difficulties in operating the thruster as a part of the catalyst was covered in the gelling agent. This preliminary study identifies the potential challenges of using a gel phase oxidizer in a catalyst ignited hybrid thruster and discusses the technical issues that should be addressed in regard to a gel propellant hybrid thruster design with a catalyst reactor. | - |
dc.language | English | - |
dc.publisher | HINDAWI LTD | - |
dc.title | Preliminary Assessment of Hydrogen Peroxide Gel as an Oxidizer in a Catalyst Ignited Hybrid Thruster | - |
dc.type | Article | - |
dc.identifier.wosid | 000460411200001 | - |
dc.identifier.scopusid | 2-s2.0-85062643382 | - |
dc.type.rims | ART | - |
dc.citation.publicationname | INTERNATIONAL JOURNAL OF AEROSPACE ENGINEERING | - |
dc.identifier.doi | 10.1155/2018/5630587 | - |
dc.contributor.localauthor | Kwon, Sejin | - |
dc.contributor.nonIdAuthor | Huh, Jeongmoo | - |
dc.contributor.nonIdAuthor | Jyoti, Botchu V. S. | - |
dc.description.isOpenAccess | N | - |
dc.type.journalArticle | Article | - |
dc.subject.keywordPlus | RHEOLOGICAL CHARACTERIZATION | - |
dc.subject.keywordPlus | SPRAY CHARACTERISTICS | - |
dc.subject.keywordPlus | ATOMIZATION CHARACTERISTICS | - |
dc.subject.keywordPlus | PROPELLANTS | - |
dc.subject.keywordPlus | PERFORMANCE | - |
dc.subject.keywordPlus | FUEL | - |
dc.subject.keywordPlus | COMBUSTION | - |
dc.subject.keywordPlus | DELAY | - |
dc.subject.keywordPlus | MONOMETHYLHYDRAZINE | - |
dc.subject.keywordPlus | DECOMPOSITION | - |
Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.