A novel framework for liquid propellant engine’s cooling system design by sensitivity analysis based on RSM and multi-objective optimization using PSO
Advances in Space Research（2021）
Abstract
•The developed equation can predict with significant accuracy.•That total heat flux can be optimized by up to 6%.•The existing cooling system indicates pressure drop can be optimized up to 7 bars.•The percentage error between the prediction and the confirmatory result are ~3%.
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Key words
Multi-objective optimization,Liquid Propellant Engine (LPE),Cooling system,Sensitivity analysis,Response Surface Method (RSM)
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