DC Field | Value | Language |
---|---|---|
dc.contributor.author | Kim, Yehyun | ko |
dc.contributor.author | Kim, Hyuntak | ko |
dc.contributor.author | Jeong, Junyeong | ko |
dc.contributor.author | Kwon, Sejin | ko |
dc.date.accessioned | 2022-06-13T09:01:50Z | - |
dc.date.available | 2022-06-13T09:01:50Z | - |
dc.date.created | 2022-06-13 | - |
dc.date.created | 2022-06-13 | - |
dc.date.issued | 2022-01 | - |
dc.identifier.citation | JOURNAL OF PROPULSION AND POWER, v.38, no.1, pp.51 - 58 | - |
dc.identifier.issn | 0748-4658 | - |
dc.identifier.uri | http://hdl.handle.net/10203/296896 | - |
dc.description.abstract | This study provides an experimental analysis of the throttling methods implemented using a throttleable injector that generates a thrust in the range 24-64% on a 50 N monopropellant thruster using 90 wt.% hydrogen peroxide and MnO2/PbO/Al2O3. The injector proposed in this study is a dual-plate injector. It is capable of controlling the mass flow rate using radial slotted and showerhead-type plates. The slotted plate was rotated and pressed against the showerhead-type plate by intersecting a number of injection ports to control the mass flow rate. Firing tests were conducted over the throttling range to verify the feasibility of the concept of the dual-plate injector. The experimental data of the injectant flow rate and chamber pressure were analyzed parametrically. It was observed that the dual-plate injector had a characteristic velocity in the range 81-97% depending on the range of thrust. In addition, a correlation was observed between the characteristic velocity efficiency and response time of the injector under varying injection conditions; that is, the characteristic velocity tends to increase with a decrease in the response time. The result can be applied to optimal control systems, and also be used to execute advanced missions accurately using a monopropellant thruster. | - |
dc.language | English | - |
dc.publisher | AMER INST AERONAUTICS ASTRONAUTICS | - |
dc.title | Dual-Plate Injector for Throttling of Hydrogen Peroxide Monopropellant Thruster | - |
dc.type | Article | - |
dc.identifier.wosid | 000802213900006 | - |
dc.identifier.scopusid | 2-s2.0-85122871378 | - |
dc.type.rims | ART | - |
dc.citation.volume | 38 | - |
dc.citation.issue | 1 | - |
dc.citation.beginningpage | 51 | - |
dc.citation.endingpage | 58 | - |
dc.citation.publicationname | JOURNAL OF PROPULSION AND POWER | - |
dc.identifier.doi | 10.2514/1.B38283 | - |
dc.contributor.localauthor | Kwon, Sejin | - |
dc.description.isOpenAccess | N | - |
dc.type.journalArticle | Article | - |
dc.subject.keywordPlus | CHUGGING INSTABILITY | - |
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