DC Field | Value | Language |
---|---|---|
dc.contributor.author | Lee, Doyun | ko |
dc.contributor.author | Kim, Ju Won | ko |
dc.contributor.author | Kwon, Sejin | ko |
dc.date.accessioned | 2018-12-20T05:10:07Z | - |
dc.date.available | 2018-12-20T05:10:07Z | - |
dc.date.created | 2018-12-03 | - |
dc.date.created | 2018-12-03 | - |
dc.date.created | 2018-12-03 | - |
dc.date.created | 2018-12-03 | - |
dc.date.issued | 2018-11 | - |
dc.identifier.citation | SENSORS AND ACTUATORS A-PHYSICAL, v.283, pp.211 - 219 | - |
dc.identifier.issn | 0924-4247 | - |
dc.identifier.uri | http://hdl.handle.net/10203/247619 | - |
dc.description.abstract | A high performance environmentally friendly ammonium dinitramide (ADN) based liquid monopropellant was used to develop a thruster with improved performance compared to a conventional hydrogen peroxide propellant microthruster. Compared to regular thrusters, microthrusters have high heat loss due to the higher reactor surface area to volume ratio. A high enthalpy propellant needs to be used to increase the decomposition temperature in order to enhance the thruster performance. There is a need to increase the heat tolerance of the catalyst given the increased reactor temperature. A lanthanum doped Pt/Al2O3 catalyst was fabricated and applied to increase the heat resistance performance against the ADN-based propellant with a theoretical adiabatic decomposition temperature of 1630 degrees C. The microthruster was manufactured using a MEMS process. A total of five layers of photosensitive glass with different shapes were fabricated by wet etching and stacked and adhered, and sensors were assembled to measure the pressure and temperature. A combustion experimentation was carried out. 90 wt.% hydrogen peroxide was injected in advance for catalyst preheating and then the ADN-based propellant was injected. In the experimental results, ignition was observed within the reactor and the combustion temperature was 983. The thrust and specific impulse performances were obtained. Compared to a microthruster using 90 wt.% hydrogen peroxide, the ADN-based propellant enhanced thrust by 19% while the specific impulse increased by 86%. (C) 2018 Elsevier B.V. All rights reserved. | - |
dc.language | English | - |
dc.publisher | ELSEVIER SCIENCE SA | - |
dc.title | High performance microthruster with ammonium-dinitramide-based monopropellant | - |
dc.type | Article | - |
dc.identifier.wosid | 000450539300025 | - |
dc.identifier.scopusid | 2-s2.0-85054367054 | - |
dc.type.rims | ART | - |
dc.citation.volume | 283 | - |
dc.citation.beginningpage | 211 | - |
dc.citation.endingpage | 219 | - |
dc.citation.publicationname | SENSORS AND ACTUATORS A-PHYSICAL | - |
dc.identifier.doi | 10.1016/j.sna.2018.09.047 | - |
dc.contributor.localauthor | Kwon, Sejin | - |
dc.description.isOpenAccess | N | - |
dc.type.journalArticle | Article | - |
dc.subject.keywordAuthor | Microthruster | - |
dc.subject.keywordAuthor | Ammonium dinitramide (ADN) based monopropellant | - |
dc.subject.keywordAuthor | Platinum/alumina/lanthanum catalyst | - |
dc.subject.keywordPlus | THRUSTER | - |
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