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

doi:10.3390/aerospace11040262

	Regression Rate and Combustion Efficiency of Composite Hybrid Rocket Grains Based on Modular Fuel Units
	Pan JJ(潘俊杰)1,2; Lin X(林鑫)2 ; Wang ZZ(王泽众)2 ; Wang RY(王若岩)2,3; Wu K(吴坤)2; Liang, Jinhu1 ; Yu XL(余西龙)2,3
Corresponding Author	Lin, Xin([email protected]) ; Wang, Zezhong([email protected])
Source Publication	AEROSPACE
	2024-04-01
Volume	11 Issue:4 Pages:18
Abstract	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.
Keyword	modular unit modification regression rate combustion efficiency hybrid rocket engine
DOI	10.3390/aerospace11040262
Indexed By	SCI
Language	英语
WOS ID	WOS:001210872100001
WOS Keyword	ENHANCEMENT
WOS Research Area	Engineering
WOS Subject	Engineering, Aerospace
Funding Project	National Natural Science Foundation of China
Funding Organization	National Natural Science Foundation of China
Classification	二类
Ranking	1
Contributor	Lin, Xin ; Wang, Zezhong
Citation statistics
Document Type	期刊论文
Identifier	http://dspace.imech.ac.cn/handle/311007/95059
Collection	高温气体动力学国家重点实验室
Affiliation	1.North Univ China, Sch Environm & Safety Engn, Taiyuan 030051, Peoples R China; 2.Chinese Acad Sci, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China; 3.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China
Recommended Citation 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.Rp_Au:Lin, Xin, Wang, Zezhong
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.

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