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Determination of The Cryogenic Propellant Parameters at Pressurization of The Propulsion System Tank by Bubbling  

Bershadskiy Vitaly A. (한국항공우주연구원 해외유치과학자)
Jung, Young-Suk (한국항공우주연구원 추진기관체계팀)
Lim, Seok-Hee (한국항공우주연구원 추진기관체계팀)
Cho, Gyu-Sik (한국항공우주연구원 추진기관체계팀)
Cho, Kie-Joo (한국항공우주연구원 추진기관체계팀)
Kang, Sun-Il (한국항공우주연구원 추진기관체계팀)
Oh, Seung-Hyub (한국항공우주연구원 추진기관체계팀)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.10, no.4, 2006 , pp. 1-10 More about this Journal
Abstract
In this paper, a calculation method of the thermodynamic parameters of cryogenic propellant is proposed when a cryogenic propellant tank is pressurized by gaseous helium(GHe) bubbling. Temperature of cryogenic propellant and mass of dissolved GHe into propellant were analyzed at the various operation of pressurization of tile liquid oxygen(LOX) and hydrogen($LH_2$) tank using helium bubbling. It was evaluated how the GHe bubbling influences to the thermodynamic parameters of LOX and $LH_2$ with results of the analysis. With the proposed calculation method, It will be able to confirm the feasibility of GHe bubbling as a pressurization system of cryogenic propellant tank and to optimize the pressurization system using GHe bubbling.
Keywords
Propulsion System; Pressurization System; Bubbling; LOX; $LH_2$; GHe;
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