액체 추진제 로켓엔진의 혼합비 안정기 Mixture Ratio Stabilizer for Liquid Propellant Rocket Engine

In this paper, stabilizer which maintains the mixture ratio of gas generator of LRE has been introduced. Design criterion for the ideal performance of stabilizer was derived. Significant parameters on the performance of stabilizer were identified through mathematical model and gas generator system analysis. Also, simulation and test results of the gas generator system showed fair agreement, thus proving the validity of the mathematical model of the stabilizer.
Publisher
한국항공우주학회
Issue Date
2008-07
Language
KOR
Citation

한국항공우주학회지, v.36, no.7, pp.703 - 711

ISSN
1225-1348
URI
http://hdl.handle.net/10203/87458
Appears in Collection
AE-Journal Papers(저널논문)
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