DC Field | Value | Language |
---|---|---|
dc.contributor.advisor | Kwon, Sejin | - |
dc.contributor.advisor | 권세진 | - |
dc.contributor.author | Kim, Kyu-Seop | - |
dc.date.accessioned | 2019-09-04T02:50:55Z | - |
dc.date.available | 2019-09-04T02:50:55Z | - |
dc.date.issued | 2019 | - |
dc.identifier.uri | http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=843677&flag=dissertation | en_US |
dc.identifier.uri | http://hdl.handle.net/10203/267266 | - |
dc.description | 학위논문(석사) - 한국과학기술원 : 항공우주공학과, 2019.2,[ix, 100 p. :] | - |
dc.description.abstract | In a rocket system, a material exposed to an extremely high-temperature environment. Existing materials such as metal, pyrolytic composite and graphite suffer from ablation. The ablation problem causes enlargement of nozzle throat during operation. As the nozzle enlarges, the combustion pressure drops significantly. Hence, long-term combustion is a challenging problem for the rocket system without proper cooling. In this study, the refractoriness of the rocket nozzle was raised by implementing Ultra-High Temperature Ceramics (UHTCs). The UHTC has a high melting point of above 2,000℃ and superior oxidation/ablation resistance. Unlike the existing material, UHTC forms the refractory oxide layer when the material oxidized. This self-generating oxide layer of UHTC protects the structural materials by hampering oxidizing-compound to diffuse into the base material. In this study, to test the feasibility of applying UHTC into rocket nozzle, 250N scale %H_2O_2$/HDPE hybrid thruster was designed. The long-term hot fire tests were conducted to test the ablation characteristics of HfC-SiC and $HfB_2$-SiC nozzle insert. The UHTC insert showed near zero erosion on the nozzle throat compare to graphite nozzle which presented substantial ablation. The combustion parameter such as chamber pressure and thermal behavior of UHTC were profoundly analyzed. Based on the analysis, the feasibility of UHTC application into the rocket nozzle evaluated. | - |
dc.language | eng | - |
dc.publisher | 한국과학기술원 | - |
dc.subject | Ultra High-Temperature Ceramics (UHTC)▼arefractory▼ahydrogen peroxide▼ahybrid thruster▼aablation resistance▼aoxidation resistance▼ahafnium carbide▼ahafnium diBoride | - |
dc.subject | 초고온 세라믹스▼a과산화수소▼a하이브리드 추력기▼a삭마 저항성▼a산화 저항성▼a하프늄 카바이드▼a하프늄 보라이드 | - |
dc.title | Feasibility study and thermal behavior analysis of rocket nozzle using UHTC-based refractory material | - |
dc.title.alternative | 초고온 세라믹스 기반 소재의 로켓 노즐 적용 가능성 평가 및 열적 거동 분석 | - |
dc.type | Thesis(Master) | - |
dc.identifier.CNRN | 325007 | - |
dc.description.department | 한국과학기술원 :항공우주공학과, | - |
dc.contributor.alternativeauthor | 김규섭 | - |
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