Study on the dynamic numerical simulation of flow and combustion in hybrid rocket motors based on a discrete phase model

Meng, Xiangyu; Gao, Jingfei; Tian, Hui; Niu, Xiaoting; Chen, Ruikai; Cai, Guobiao

doi:10.1016/j.actaastro.2023.12.006

Cited by 4 publications

(7 citation statements)

References 31 publications

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“…The combustion reaction flow inside the spiral star-shaped grain has a high Reynolds number, and the realizable k –ε turbulent model can simulate the flow state well. , The realizable k –ε turbulent model is adopted in the simulation and can be described as follows: ∂ ∂ t false( ρ k false) + ∂ ∂ x false( ρ k v x false) + ∂ r ∂ r false( ρ k v r false) = ∂ ∂ x true( α μ eff ∂ k ∂ x true) + ∂ r ∂ r r true( α μ eff ∂ k ∂ r true) + G k − ρ ε ∂ ∂ t false( ρ ε false) + ∂ ∂ x false( ρ ε v x false) + ∂ r ∂ r r false( ρ ε v r false) = ∂<...…”

Section: Simulation Models and Experimental Setupmentioning

confidence: 99%

“…The combustion reaction flow inside the spiral star-shaped grain has a high Reynolds number, and the realizable k−ε turbulent model can simulate the flow state well. 2,40 The realizable k−ε turbulent model is adopted in the simulation and can be described as follows:…”

Section: Setupmentioning

confidence: 99%

“…The combustion reaction flow inside the spiral star-shaped grain has a high Reynolds number, and the realizable k –ε turbulent model can simulate the flow state well. , The realizable k –ε turbulent model is adopted in the simulation and can be described as follows: where the effective viscosity μ eff = μ = μ t , μ represents the viscosity coefficient, μ t = ρC k k 2 /ε denotes the turbulent viscosity coefficient, and G k is the generation of turbulence kinetic energy.…”

Section: Simulation Models and Experimental Setupmentioning

confidence: 99%

See 2 more Smart Citations

Combustion Characteristics of Vat-Photopolymerized Fuels with a Spiral Star Port for Hybrid Propulsion

Chen,

Fu,

Yang

et al. 2024

Langmuir

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Despite hybrid rocket motors offering distinct advantages over solid or liquid rocket motors, their low regression rate and insufficient combustion efficiency remain significantly unimproved. This study focuses on the effects of the helix lead on the regression rate distribution and combustion efficiency of vat-polymerized fuel grains with a spiral star port for a hybrid rocket. Both experimental and numerical investigations were conducted to study the combustion characteristics and regression rate distribution of three-dimensional (3D) print grains. Spiral star grains with varying helix leads of 60, 90, and 120 mm were fabricated using light-curing 3D printing technology. A 3D simulation model was developed to obtain the temperature distribution, species mass distribution, and combustion efficiency. Furthermore, firing tests were performed on a two-dimensional radial hybrid combustion test stand to measure the regression rate. Digital image processing of computed tomography images was used to determine the regression rate. Simulation results indicated that the spiral star grain port helps to improve the combustion efficiency compared with those seen with round tube and straight star port grains. With an increase in the axial distance, the flame zone gradually shrinks, and the smaller the helix lead, the faster the shrinkage. At a mass flow rate of 1.50 g/s for oxygen, the regression rate of the spiral star grains is significantly higher than that of the straight star grain and the conventional round tubular grains, and the regression rate gradually increases with a decrease in the helix lead. This finding is expected to solve the problem of the low regression rate of solid fuels with spiral star pore-shaped grains prepared by the light-curing 3D printing method.

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Section: Simulation Models and Experimental Setupmentioning

confidence: 99%

Section: Setupmentioning

confidence: 99%

“…The combustion reaction flow inside the spiral star-shaped grain has a high Reynolds number, and the realizable k –ε turbulent model can simulate the flow state well. , The realizable k –ε turbulent model is adopted in the simulation and can be described as follows: where the effective viscosity μ eff = μ = μ t , μ represents the viscosity coefficient, μ t = ρC k k 2 /ε denotes the turbulent viscosity coefficient, and G k is the generation of turbulence kinetic energy.…”

Section: Simulation Models and Experimental Setupmentioning

confidence: 99%

See 1 more Smart Citation

Combustion Characteristics of Vat-Photopolymerized Fuels with a Spiral Star Port for Hybrid Propulsion

Chen,

Fu,

Yang

et al. 2024

Langmuir

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show abstract

“…where U, S, and V represent the orthogonal modes of the flame series and their corresponding mode energy and time coefficients, T is the transpose of a matrix. λ = S 2 (7) where λ represents the eigenvalue.…”

Section: Radiation Luminescencementioning

confidence: 99%

“…The hybrid rocket engine (HRE) is progressively emerging as a compelling propulsion system with significant potential for development and commercial viability [1][2][3][4][5]. In comparison with conventional liquid or solid rocket engines, the HRE offers the benefits of adjustable thrust, enhanced safety protocols, environmental friendliness, ease of repeated ignition, and low manufacturing cost [6][7][8][9]. However, the following issues with HRE are still unresolved: the different phases of the propellants and the diffuse combustion characteristics result in the low combustion efficiency of fuel grains [10][11][12][13].…”

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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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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3D printed hybrid rocket fuels with μAl core-shell particles coated with polyvinylidene fluoride and polydopamine: Enhanced combustion characteristics

Chen,

Fu,

Yang

et al. 2024

Defence Technology

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Study on the dynamic numerical simulation of flow and combustion in hybrid rocket motors based on a discrete phase model

Cited by 4 publications

References 31 publications

Combustion Characteristics of Vat-Photopolymerized Fuels with a Spiral Star Port for Hybrid Propulsion

Combustion Characteristics of Vat-Photopolymerized Fuels with a Spiral Star Port for Hybrid Propulsion

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

3D printed hybrid rocket fuels with μAl core-shell particles coated with polyvinylidene fluoride and polydopamine: Enhanced combustion characteristics

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