Flame Dynamics in the Combustion Chamber of Hybrid Rocket Using Multiangle Chemiluminescence

Luo, Jiaxiao; Zhang, Zelin; Lin, Xin; Wang, Zezhong; Wu, Kun; Zhou, Gongxi; Zhang, Senhao; Li, Fēi; Yu, Xilong; Wu, Jie

doi:10.2514/1.b38955

Cited by 5 publications

(2 citation statements)

References 42 publications

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“…Interfaces were provided in the combustion chambers to connect pressure sensors. Further details can be found in our previous studies [30,35]. The engine was ignited by a torch-type igniter activated by gaseous methane and oxygen.…”

Section: Laboratory-scale Hybrid Rocket Enginementioning

confidence: 99%

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

Pan,

Lin,

Wang

et al. 2024

Aerospace

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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/(s·cm2). 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/(s·cm2), 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.

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Section: Laboratory-scale Hybrid Rocket Enginementioning

confidence: 99%

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

Pan,

Lin,

Wang

et al. 2024

Aerospace

Self Cite

View full text Add to dashboard Cite

show abstract

“…A high-speed camera (iX Cameras, i-Speed 220, London, UK) was used to acquire images of the combustion chamber flame with an exposure time of 2 ms and a frame rate of 1 kHz. A 430 nm narrowband filter was employed to reduce the light intensity transmitted through the optical fiber [31]. The field of view of the chamber flame is indicated by the dotted line frame in the lower part of Figure 2.…”

Section: Lab-scale Hybrid Rocket Enginesmentioning

confidence: 99%

Combustion Characteristics of a Swirl-Radial-Injection Composite Fuel Grain with Applications in Hybrid Rockets

Wang,

Lin,

Wang

et al. 2023

Aerospace

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The combustion characteristics of a swirl-radial-injection composite fuel grain were experimentally and numerically investigated. This composite grain permits swirl-radial oxidizer injection based on three hollow helical blades, each having a constant hollow space allowing uniform oxidizer injection into the main chamber along the axial direction. The oxidizer enters from channel inlets located along a hollow outer wall. This wall, together with the three blades, is fabricated as one piece from acrylonitrile-butadiene-styrene using three-dimensional printing. Paraffin-based fuel is embedded in the spaces between adjacent blades. Firing tests were conducted with gaseous oxygen as the oxidizer, using oxidizer mass flow rates ranging from 7.45 to 30.68 g/s. Paraffin-based fuel grains using conventional fore-end injection were used for comparison. Regression rate boundaries were determined taking into account the erosion of the oxidizer channels. The data show that the regression rate was significantly increased even at the lower limit. Images of the combustion chamber flame and of the exhaust plume were also acquired. The flame was found to be concentrated in the main chamber and a smoky plume was observed, consistent with the high regression rate. A three-dimensional simulation was employed. The present design was found to improve fuel/oxidizer mixing and combustion efficiency compared with a fuel grain using fore-end injection. Both the experimental results and numerical simulations confirmed the potential of this swirl-radial-injection fuel grain.

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Additively manufactured aluminium nested composite hybrid rocket fuel grains with breathable blades

Qu,

Lin,

Zhang

et al. 2023

Virtual and Physical Prototyping

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Flame Dynamics in the Combustion Chamber of Hybrid Rocket Using Multiangle Chemiluminescence

Cited by 5 publications

References 42 publications

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

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

Combustion Characteristics of a Swirl-Radial-Injection Composite Fuel Grain with Applications in Hybrid Rockets

Additively manufactured aluminium nested composite hybrid rocket fuel grains with breathable blades

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