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A Study on the Cyclogram for the Firing Test of KSR-III Liquid Rocket Engine  

한영민 (한국항공우주연구원)
조남경 (한국항공우주연구원)
박성진 (한국항공우주연구원)
이수용 (한국항공우주연구원)
이대성 (한국항공우주연구원)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.6, no.3, 2002 , pp. 19-27 More about this Journal
Abstract
The sequence of the propellant supply for ignition of a liquid rocket engine combustor is very important in the reliable and safe operation of the engine. The ignition sequence of KSR-III main engine was briefly described and the measuring parameters and their reliability determining ignition sequence were examined in this paper. The filling time of the engine propellant manifolds and the valve open/close time were reviewed to obtain the exact and reliable time of the propellant supply to the combustor. The combustion characteristics of the engine at starting were discussed at different supply lead of propellant. Finally, the hot firing test results with cyclogram determined by measuring parameters were presented.
Keywords
Liquid Rocket; Cyclogram; Flow Rate; Dynamic Pressure;
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