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추진기관 탱크내 극저온 추진제의 온도 상승에 대한 연구
임석희(Seok-Hee Lim),베르샤드스키(Bershadskiy. V. A.),정영석(Young-Suk Jung),조기주(Kie-Joo Cho),오승협(Seung-Hyub Oh) 대한기계학회 2006 대한기계학회 춘추학술대회 Vol.2006 No.6
This study has considered the definition of temperature increase in the cryogenic propellant at the development stage of propulsion system. From the analysis of known theoretical model for calculation and the consideration of possible heat and mass transfer mechanism on the full-scale tank, methodical characteristics of calculation-experimental for estimation of key parameters of temperature rise and thermal stratification have been formulated with application of sub-scale tank modeling and imitation of operation environment of propellant supplying system.
Optimal Conditions for Thermal Control of LOX using GHe Bubbling Method
Young-Suk Jung(정영석),Seok-Hee Lim(임석희),Gyu-Sik Cho(조규식),Kie-Joo Cho(조기주),V.A. Bershadskiy(베르샤드스키),Seung-Hyub Oh(오승협) 대한기계학회 2006 대한기계학회 춘추학술대회 Vol.2006 No.6
In this paper, the algorithm for calculating the thermophysical parameters of LOX in tank at the step of LOX thermal conditioning system using GHe bubbling during pre-launch operation is presented. The algorithm is based on a physical-mathematical models which integrally consider the characteristics and intensity of heat and mass transfer in LOX of the propellant tank and the experimental models which are used for the description of intensity of heat and mass transfer and the change of composition of gas and liquid phases in LOX. With the developed algorithm, the transient analysis of thermal conditioning system is executed on each condition as a temperature of injected GHe and pressure of tank, and the optimal conditions are proposed for an efficient thermal conditioning system using GHe bubbling.
헬륨 버블링 방법을 이용한 액체 추진제 로켓 추진제 탱크의 가압 시스템 분석
정영석(Young Suk Jung),임석희(Seok Hee Lim),조기주(Kie Joo Cho),베르샤드스키(V. A. Bershadskiy) 대한기계학회 2005 대한기계학회 춘추학술대회 Vol.2005 No.11
This paper presents an analysis method to predict the temperature of LOX(liquid oxygen) and He(helium) contents in LOX at prepressurization and main pressurization stages using GHe(Gas He) bubbling method for propellants feeding system in rocket. With presented analytical method in this paper, variation of temperature and He contents in LOX are predicted at prepressurization and main pressurization stages in case that GHe bubbling method is used in pressurization system of the 2nd stage. Computer simulations are accompanied in conditions of temperature(288K) and mass flowrate(0.02㎏/sec) of injected GHe at prepressurization stage and in conditions of controlled pressure of tank(4bar) and fixed mass flowrate of fed LOX to engine at main pressurization stage.
Young-Suk Jung(정영석),Kie-Joo Cho(조기주),Seok-Hee Lim(임석희),Gyu-Sik Cho(조규식),Seung-Hyub Oh(오승협),Bershadskiy V.A(베르샤드스키) 대한기계학회 2005 대한기계학회 춘추학술대회 Vol.2005 No.5
In this paper, The optimum design method of temperature and velocity of the pressurization gas to minimize weight of propellant tank pressurization system on system design of propellant feed system of the liquid propellant rocket was suggested. We considered the influences of parameters of pressurization gas on the efficiency of the thermodynamic processes in the tank and on the design of components as gas tank, heat exchanger and diffuser. We have developed the program for determination of the optimum value of temperature and velocity of pressurization gas at the entrance of tank.