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http://dx.doi.org/10.6108/KSPE.2015.19.3.047

A Preliminary Configuration Design of Methane/Oxygen Bipropellant Small-Rocket-Engine through Theoretical Performance Analysis  

Bae, Seong Hun (Department of Mechanical Engineering, Pukyong National University)
Jung, Hun (Department of Mechanical Engineering, Graduate School, Pukyong National University)
Kim, Jeong Soo (Department of Mechanical Engineering, Pukyong National University)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.19, no.3, 2015 , pp. 47-53 More about this Journal
Abstract
Design parameters required for Methane/oxygen bipropellant small-rocket-engine were derived through a theoretical performance analysis. The theoretical performance of the rocket engine was analyzed by using CEA and optimal propellant mixture ratio, characteristic length, and optimal expansion ratio were calculated by assuming chemical equilibrium. A coaxial-type swirl injector was chosen because of its outstanding atomization performance and high combustion efficiency compared to other types of injector and also a bell nozzle with 80% of its full length was designed. The rocket engine configuration with 1.72 MPa of chamber pressure, 0.18 kg/s in total propellant mass flow, and O/F ratio of 2.7 was proposed as a ground-firing test model.
Keywords
Bipropellant; Liquid Methane; Liquid Rocket Engine; Swirl Coaxial Injector;
Citations & Related Records
Times Cited By KSCI : 2  (Citation Analysis)
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