Numerical investigations of hybrid rocket engines

Paper presents the results of numerical studies of hybrid rocket engines operating cycle including unsteady-state transition stage. A mathematical model is developed accounting for the peculiarities of diffusion combustion of fuel in the flow of oxidant, which is composed of oxygen-nitrogen mixture....

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Bibliographic Details
Published in:Acta astronautica 2018-03, Vol.144, p.363-370
Main Authors: Betelin, V.B., Kushnirenko, A.G., Smirnov, N.N., Nikitin, V.F., Tyurenkova, V.V., Stamov, L.I.
Format: Article
Language:English
Subjects:
Aerodynamics
Airplane engines
Chemical reactions
Combustion
Computer simulation
Deceleration
Diffusion
Diffusion rate
Fluidized bed combustion
Fuel regression
Fuels
Hybrid rocket
Hybrid rocket engines
Mathematical models
Organic chemistry
Oxygen
Regression analysis
Regression rate
Rocket engines
Rockets
Solid fuel
Supersonic
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Summary:Paper presents the results of numerical studies of hybrid rocket engines operating cycle including unsteady-state transition stage. A mathematical model is developed accounting for the peculiarities of diffusion combustion of fuel in the flow of oxidant, which is composed of oxygen-nitrogen mixture. Three dimensional unsteady-state simulations of chemically reacting gas mixture above thermochemically destructing surface are performed. The results show that the diffusion combustion brings to strongly non-uniform fuel mass regression rate in the flow direction. Diffusive deceleration of chemical reaction brings to the decrease of fuel regression rate in the longitudinal direction.
ISSN:0094-5765
1879-2030
DOI:10.1016/j.actaastro.2018.01.009