• Title/Summary/Keyword: 액체추신 로켓

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Thermal Analysis of Prelaunch Transients in Cryogenic Oxidizer Tank of Liquid Propulsion Rocket (발사대기 중인 액체추진 로켓의 극저온 산화제 탱크 내 비정상 열해석)

  • Kim, Kyoung-Hoon;Ko, Hyung-Jong;Kim, Kyoung-Jin;Cho, Kie-Joo;Oh, Seung-Hyub
    • Journal of the Korean Society of Propulsion Engineers
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    • v.12 no.4
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    • pp.33-41
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    • 2008
  • The prelaunch thermal transients in the cryogenic oxidizer tank of liquid propulsion rocket subjected to uniform heat flux from outside are numerically analyzed through thermodynamic equations and heat and mass transfer relations. The prelaunch stage is assumed to be composed of five idealized sub-stages including pressurization process by helium gas injection. The Peng-Robinson equation of state is utilized in the lumped analysis of ullage gas. The liquid region is divided into a number of horizontal layers of uniform properties to account for the thermal stratification. The computational result for the typical case shows that the temperature rise of liquid oxidizer is less than 1K and the adsorbed helium into the liquid is approximately 10g.