Abstract
A preliminary design method and genetic algorithm were used to design a methane-fuel rocket combustor that can be beneficial for next-generation rocket engines. The O/F ratio, aspect ratio of the cooling channel, number of cooling channels, and mass flux of coolant were considered as design variables. A Monte Carlo simulation was conducted and the correlation tendency between the design variables and objective parameters were identified using random variables. Two methods for variable application and two types of objective functions were compared for optimization, namely, addition type and multiplication type functions with all variables and restricted variables. The multiplication type of the objective function with restricted variables presented the best optimization results.
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Recommended by Guest Editor Joo-Ho Choi
Min Son received his B.S. and M.S. degrees in Aerospace and Mechanical Engineering from Korea Aerospace University in 2010 and 2012, respectively. After graduation, he started his Ph.D. program in Aerospace and Mechanical Engineering at the same university in 2012. His research focuses on optimal design method of liquid rocket combustor, inner flow visualization of a solid rocket motor, pulse detonation phenomenon and spray combustion of liquid rocket injector, especially a pintle injector.
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Son, M., Koo, J., Kim, B. et al. Design optimization of a methane-fuel rocket combustor with a genetic algorithm. J Mech Sci Technol 29, 1457–1463 (2015). https://doi.org/10.1007/s12206-015-0318-4
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DOI: https://doi.org/10.1007/s12206-015-0318-4