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Regression Rate and Combustion Efficiency of Composite Hybrid Rocket Grains Based on Modular Fuel Units

文献类型：期刊论文

作者Pan JJ(潘俊杰)2,3; Lin X(林鑫)2; Wang ZZ(王泽众)2; Wang RY(王若岩)1,2; Wu K(吴坤)2; Liang, Jinhu3; Yu XL(余西龙)1,2
刊名AEROSPACE
出版日期2024-04-01
卷号11期号:4页码:18
关键词modular unit modification regression rate combustion efficiency hybrid rocket engine
DOI10.3390/aerospace11040262
通讯作者Lin, Xin(linxin_bit@imech.ac.cn) ; Wang, Zezhong(wangzezhong@imech.ac.cn)
英文摘要This study investigated combustion characteristics of composite fuel grains designed based on a modular fuel unit strategy. The modular fuel unit comprised a periodical helical structure with nine acrylonitrile-butadiene-styrene helical blades. A paraffin-based fuel was embedded between adjacent blades. Two modifications of the helical structure framework were researched. One mirrored the helical blades, and the other periodically extended the helical blades by perforation. A laboratory-scale hybrid rocket engine was used to investigate combustion characteristics of the fuel grains at an oxygen mass flux of 2.1-6.0 g/(scm2). Compared with the composite fuel grain with periodically extended helical blades, the modified composite fuel grains exhibited higher regression rates and a faster rise of regression rates as the oxygen mass flux increased. At an oxygen mass flux of 6.0 g/(scm2), the regression rate of the composite fuel grains with perforation and mirrored helical blades increased by 8.0% and 14.1%, respectively. The oxygen-to-fuel distribution of the composite fuel grain with mirrored helical blades was more concentrated, and its combustion efficiency was stable. Flame structure characteristics in the combustion chamber were visualized using a radiation imaging technique. A rapid increase in flame thickness of the composite fuel grains based on the modular unit was observed, which was consistent with their high regression rates. A simplified numerical simulation was carried out to elucidate the mechanism of the modified modular units on performance enhancement of the composite hybrid rocket grains.
分类号二类
WOS关键词ENHANCEMENT
资助项目National Natural Science Foundation of China
WOS研究方向Engineering
语种英语
WOS记录号WOS:001210872100001
资助机构National Natural Science Foundation of China
其他责任者Lin, Xin ; Wang, Zezhong
源URL[http://dspace.imech.ac.cn/handle/311007/95058]  
专题力学研究所_高温气体动力学国家重点实验室
作者单位1.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China
2.Chinese Acad Sci, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China;
3.North Univ China, Sch Environm & Safety Engn, Taiyuan 030051, Peoples R China;
推荐引用方式
GB/T 7714		 Pan JJ,Lin X,Wang ZZ,et al. Regression Rate and Combustion Efficiency of Composite Hybrid Rocket Grains Based on Modular Fuel Units[J]. AEROSPACE,2024,11(4):18.
APA 潘俊杰.,林鑫.,王泽众.,王若岩.,吴坤.,...&余西龙.(2024).Regression Rate and Combustion Efficiency of Composite Hybrid Rocket Grains Based on Modular Fuel Units.AEROSPACE,11(4),18.
MLA 潘俊杰,et al."Regression Rate and Combustion Efficiency of Composite Hybrid Rocket Grains Based on Modular Fuel Units".AEROSPACE 11.4(2024):18.

入库方式： OAI收割

来源：力学研究所

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