| Combustion performance of a novel hybrid rocket fuel grain with a nested helical structure | |
Wang ZZ(王泽众)1,2 ; Lin X(林鑫)1; Li F(李飞)1; Yu XL(余西龙)1,2
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| Corresponding Author | Lin, Xin([email protected]) |
| Source Publication | AEROSPACE SCIENCE AND TECHNOLOGY
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| 2020-02-01 | |
| Volume | 97Pages:8 |
| ISSN | 1270-9638 |
| Abstract | The combustion performance of a novel fuel grain having a nested helical structure was experimentally investigated using a laboratory-scale hybrid rocket engine. This grain comprised a paraffin-based fuel embedded in an acrylonitrile-butadiene-styrene (ABS) substrate that provided a helical structural framework. The helical structure of the grain was maintained throughout the combustion process due to the much lower regression rate of ABS compared with that of the paraffin-based fuel. Using oxygen as the oxidizer at mass flow rates of 7-30 g/s, firing tests were conducted to assess combustion performance parameters of the novel fuel grain, including ignition characteristics, pressure oscillations, regression rate, and combustion efficiency. Pure paraffin-based fuel grains were also tested as a baseline fuel and compared. The novel fuel grain exhibited rapid, reliable ignition with stable combustion pressures. Analysis of pressure fluctuations by fast Fourier transform showed peaks at approximately 62, 130 and 320 Hz, which are consistent with the characteristics of a pure paraffin-based fuel grain. It is highly likely that the nested helical structure did not introduce additional combustion oscillation mechanisms into the hybrid rocket engine. Significant improvements in regression rate were obtained using this novel grain. The regression rate for the novel fuel grain is approximately 20% higher than that of the paraffin-based fuel at an oxidizer mass flow rate of 30 g/s, and the rate of the regression rate rise was higher than that of the pure paraffin-based fuel as the oxidizer mass flow rate increases. Moreover, the nested helical structure was also found to improve combustion efficiency. A tentative explanation of all improvements was proposed, resorting to the exacerbated turbulence and the strengthened heat transfer. (C) 2019 Elsevier Masson SAS. All rights reserved. |
| Keyword | Hybrid rocket engine Paraffin-based fuel Acrylonitrile-butadiene-styrene Regression rate Combustion efficiency |
| DOI | 10.1016/j.ast.2019.105613 |
| Indexed By | SCI ; EI |
| Language | 英语 |
| WOS ID | WOS:000518700300006 |
| WOS Keyword | REGRESSION RATE ; PROPELLANTS ; MOTOR |
| WOS Research Area | Engineering |
| WOS Subject | Engineering, Aerospace |
| Funding Project | National Natural Science Foundation of China[11802315] ; National Natural Science Foundation of China[11872368] ; Equipment Pre-research Foundation of National Defense Key Laboratory[6142701190402] |
| Funding Organization | National Natural Science Foundation of China ; Equipment Pre-research Foundation of National Defense Key Laboratory |
| Classification | 一类 |
| Ranking | 1 |
| Contributor | Lin, Xin |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/81781 |
| Collection | 高温气体动力学国家重点实验室 |
| Affiliation | 1.Chinese Acad Sci, Inst Mech, Beijing 100190, Peoples R China; 2.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100190, Peoples R China |
| Recommended Citation GB/T 7714 | Wang ZZ,Lin X,Li F,et al. Combustion performance of a novel hybrid rocket fuel grain with a nested helical structure[J]. AEROSPACE SCIENCE AND TECHNOLOGY,2020,97:8.Rp_Au:Lin, Xin |
| APA | 王泽众,林鑫,李飞,&余西龙.(2020).Combustion performance of a novel hybrid rocket fuel grain with a nested helical structure.AEROSPACE SCIENCE AND TECHNOLOGY,97,8. |
| MLA | 王泽众,et al."Combustion performance of a novel hybrid rocket fuel grain with a nested helical structure".AEROSPACE SCIENCE AND TECHNOLOGY 97(2020):8. |
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| Jp2020128.pdf（1961KB） | 期刊论文 | 出版稿 | 开放获取 | CC BY-NC-SA | View Download | |
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