Scale-Up Validation of Hydrogen Peroxide/High-Density Polyethylene Hybrid Rocket with Multiport Solid Fuel

Yun, Yongtae; Huh, Jin Woo; Kim, Young-il; Heo, Seonuk; Kim, Hyuntak; Kwon, Sejin

doi:10.2514/1.a34707

Cited by 7 publications

(4 citation statements)

References 18 publications

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“…The development of turbulence was taken into account by setting the turbulence model to SST k-ω. Ethylene(C 2 H 4 ) was used instead of a paraffin-based fuel [17] and a 10-step C 2 H 4 reaction mechanism was adopted [42], which is shown in Table 2. Oxygen was employed as the oxidizing agent.…”

Section: Model Description and Precision Estimatesmentioning

confidence: 99%

“…Therefore, research has focused on improving the regression rates. The use of complex single-port structures and multiport fuel grains have proven effective in increasing regression rates of fuel grains [15][16][17][18][19][20]. At a constant oxygen mass flow rate, there is an antagonism between the rise rate of regression and enhancement of flux enhancement, which often involves employing multiport structures to augment the burning surface.…”

Section: Introductionmentioning

confidence: 99%

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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: Model Description and Precision Estimatesmentioning

confidence: 99%

Section: Introductionmentioning

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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show abstract

“…However, the development of scalable regression rate formulations [50], better understanding and theoretical investigation of the scale effect [51], and the increasing overall availability of data on HREs is leading to more successful scaling efforts, such as upscaling from low-pressure and low-mass flow to a larger scale for paraffin [52,53], upscaling from 2.5 kN to 40 kN on the CAMUI-Cascaded Multistage Impinging-Jet [54] (see Figure 2), and multi-port upscaling from 250-2500 kN with only 2.6-8.4% error [55]. Two other considerations for large-or full-scale applications need to be briefly discussed as well.…”

mentioning

confidence: 99%

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

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Hybrid rocket propulsion, first demonstrated by the Russian GIRD-09 rocket in 1933, combines liquid oxidizer and solid fuel for thrust generation. Despite numerous advantages, such as enhanced safety, controllability, and potential environmental benefits, hybrid propulsion has yet to achieve its full potential in space applications. In recent years, the research on hybrid propulsion has gained enormous momentum in both academia and industry. Recent accomplishments such as the altitude record for student rockets (64 km), the launch of the first electric pump-fed hybrid rocket, and a successful 25 s hovering test highlight the potential of hybrid rockets. However, although the hybrid community is growing constantly, industrial utilizations and in-space validations do not yet exist. In this work, we reassess the possibilities of hybrid rocket engines by presenting potential fields of applications from the literature. Most importantly, we identify the technical challenges that hinder the breakthrough of hybrid propulsion in the space sector and evaluate the technologies and approaches necessary to bridge the gaps in hybrid rocket development.

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“…Additionally, more research on eco-friendly solid rocket boosters is necessary to curb dangerous lower atmosphere pollution in addition to research on eco-friendly liquid fuels (Cican & Mitrache, 2017;Yun et al, 2021; see also Murachman et al, 2013). Kerosene can be converted into paraffin wax and used as a more environmentallyfriendly solid fuel, and although this research does not directly investigate paraffin wax, the results could have implications in this field as well due to the chemical similarities between solid paraffin wax and liquid kerosene (Akhter & Hassan, 2021).…”

mentioning

confidence: 99%

To Infinity and Beyond: An Optimization Study of Kerosene and Hydrogen Peroxide Bipropellant Fuels

Kline

Rennix²,

Gutzler³

2022

J Stud Res

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Currently, hydrazine fuels are grossly inefficient in terms of environmentally friendliness and handling costs. Hydrogen peroxide (H2O2) and kerosene bipropellants have recently shown promise as a fuel that is similar in efficiency to hydrazine yet superior in cost and environmentally friendliness. Previous research on H2O2/kerosene bipropellants view environmentally friendliness, cost effectiveness, and fuel efficiency separately, making comparison between these properties difficult. This research uses calorimetry to provide a new method of quickly and precisely finding optimal ratios of fuels in bipropellants. For different ratios of fuel, efficiency was measured by finding the fuel mixture’s specific energy, environmentally friendliness was measured by finding the fuel mixture’s efficiency per carbon released into the atmosphere, and cost effectiveness was measured by finding the fuel mixture’s efficiency per unit fuel cost. The Cobb-Douglas function was used to optimize for multiple fuel properties at the same time: environmentally friendliness and efficiency, cost effectiveness and efficiency, and environmentally friendliness and cost effectiveness. These double optimizations brought new properties of H2O2/kerosene bipropellant fuels to light, notably that the optimal ratio of fuel for environmentally friendliness coincides with the optimal ratio for fuel efficiency, and the bipropellant remains efficacious in terms of efficiency even while operating at the optimal quantity for cost effectiveness. In short, these findings reaffirm H2O2 and kerosene bipropellants as great potential candidates for an eco-friendly and cost effective replacement of hydrazine because of their unique potential to remain environmentally friendly even at optimally efficient ratios.

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Scale-Up Validation of Hydrogen Peroxide/High-Density Polyethylene Hybrid Rocket with Multiport Solid Fuel

Cited by 7 publications

References 18 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

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

To Infinity and Beyond: An Optimization Study of Kerosene and Hydrogen Peroxide Bipropellant Fuels

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