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Analysis of Combustor and Nozzle for Monopropellant Satellite Thruster  

Lee, Sung-Nam (KAIST 항공우주공학과 대학원)
Baek, Seung-Wook (KAIST 항공우주공학과)
Kim, Su-Kyum (한국항공우주연구원 위성 열/추진 팀)
Yu, Myoung-Jong (한국항공우주연구원 위성 열/추진 팀)
Publication Information
Journal of the Korean Society of Combustion / v.15, no.2, 2010 , pp. 12-18 More about this Journal
Abstract
A numerical analysis was performed to predict the thermo-fluid dynamic characteristics of hydrazine monopropellant reaction in the thruster combustor and nozzle. A 1-D porous model was introduced to simulate catalytic reaction by iridium in the combustor while 2-D axisymmetric analysis was applied to predict the nozzle flow. The chemical species and temperature variations were predicted by changing the injection pressure and mass flow rate and their results were validated by comparison with limited experimental data. The thrust variation with injection pressure could be estimated using the current 1-D combustor modeling.
Keywords
Onopropellant; Thruster; Hydrazine; Iridium catalyst; AUSM+;
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