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Development of KSR-III Propulsion Feeding System  

이대성 (한국항공우주연구원)
조인현 (한국항공우주연구원)
정태규 (한국항공우주연구원)
강선일 (한국항공우주연구원)
김용욱 (한국항공우주연구원)
정영석 (한국항공우주연구원)
권오성 (한국항공우주연구원)
정동호 (한국항공우주연구원)
오승협 (한국항공우주연구원)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.6, no.4, 2002 , pp. 37-45 More about this Journal
Abstract
The development process of KSR-III propulsion feeding system is subscripted. The purpose of propulsion feeding system is to feed a certain amount of propellant from propellant tank to engine by the end of combustion. Pressure-fed liquid rocket, KSR-III has the unique characteristics of both pressure regulator and cavitation venturi as a passive flow control device. Main parameters of feeding system are confirmed by both water test and CFD(전산유체) technique. Flow control effect with venturi is confirmed by water test. Initial stabilization characteristic of pressure regulator is confirmed by real propellant test. And, to avoid the effect of resonance between rocket and feeding system, this article deal with POGO(포고) analysis to the feeding system.
Keywords
CFD; POGO;
Citations & Related Records
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  • Reference
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