단일추진제 위성추력기 내 연소기 및 노즐 유동 해석Analysis of Combustor and Nozzle for Monopropellant Satellite Thruster

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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.
Publisher
한국연소학회
Issue Date
2010-06
Language
Korean
Citation

한국연소학회지, v.15, no.2, pp.12 - 18

ISSN
1226-0959
URI
http://hdl.handle.net/10203/94590
Appears in Collection
AE-Journal Papers(저널논문)
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