• Title/Summary/Keyword: 추진제탱크

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위성 발사체 추진제 가압용 열교환기 기초 설계

  • 이희준;한상엽;정용갑;길경섭;하성업;김병훈
    • Bulletin of the Korean Space Science Society
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    • 2004.04a
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    • pp.74-74
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    • 2004
  • 액체추진제를 사용하는 위성 발사체의 경우 추진제탱크에 저장된 추진제를 추력을 발생하는 연소실에 공급하기 위하여 헬륨 등의 가압제를 사용한다. 본 연구에서는 액체추진제 로켓엔진의 산화제인 극저온의 액체산소를 저장하고 있는 탱크 내부에 설치된 별도의 탱크에 저장된 극저온/고압의 헬륨을 고온으로 열팽창 시켜 추진제 탱크로 재유입하여 추진제를 가압하는 시스템에 사용되는 가압제 열팽창용 열교환기의 개발을 위한 기초 설계를 수행하였다. (중략)

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Basic Model for Propellant Tank Ullage Calculation (추진제탱크 얼리지 해석을 위한 기본모델)

  • Kwon, Oh-Sung;Cho, Nam-Kyung;Cho, In-Hyun
    • Aerospace Engineering and Technology
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    • v.9 no.1
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    • pp.125-132
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    • 2010
  • Estimation of pressurant mass flowrate and its total mass required to maintain propellant tank pressure during propellant outflow is very important for design of pressurization control system and pressurant storage tank. Especially, more pressurant mass is required to maintain pressure in cryogenic propellant tank, because of reduced specific volume of pressurant due to heat transfer between pressurant and tank wall. So, basic model for propellant tank ullage calculation was proposed to estimate ullage and tank wall temperature distribution, required pressurant mass, and energy distribution of pressurant in ullage. Both test and theoretical analysis have been conducted, but only theoretical modeling method was addressed in this paper.

Stress Analysis of Pressurization Type Propellant Tank in the Satellite (인공위성용 능동가압형 추진제 탱크의 응력 해석)

  • 한근조;심재준;최진철
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 1997.11a
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    • pp.21-21
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    • 1997
  • 인공위성용 추진제 탱크를 개발하기 위해 여러 설계인자를 설정하여 각 인자가 탱크벽면에 미치는 응력분포 영향을 구하고, 또한 최적의 인자 값을 구하기 위해 각 인자의 변화에 따라서 구조해석을 수행하였다. 탱크 지지부 위치와 탱크 벽면 두께 변화에 따른 탱크 벽면에 미치는 응력분포 영향을 고찰하기 위해 1/4 모델을 설정하였고, 연료배출구의 위치변화(경사각돈)에 따른 응력분포는 1/2 모델을 설정하여 해석을 하였다. 탱크에 작용하는 하중은 연료압력에 의해 발생하는 정하중(350 psi)을 가하며 또한, 발사 시 발사체로부터 전달되는 최대동하중(llg)을 고려하였다. 그리고, 탱크가 인공위성에 장착될 때에 발생하는 다양한 장착조건에 대해서 구조해석을 수행하였고, 추진제 배출구 각도가 $0^{\circ}$ 에서 $25^{\circ}C$까지 변화할 때 탱크 벽면에 미치는 응력분포 영향을 구했다. 그래서 각 조건에서 구한 상당응력분포와 인자의 최적 값은 추진제 탱크를 설계하기 위한 기초적인 자료로 활용하고자 한다.

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Flow Visualization and Calculation at the Outlet of Propellant Tank Pressurizing Gas Injector (추진제탱크 가압용 인젝터 출구에서의 유동가시화 및 해석)

  • Kwon, Oh-Sung;Han, Sang-Yeop;Kwon, Ki-Jung;Chung, Yong-Cahp
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.1
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    • pp.73-79
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    • 2010
  • Propellant tank pressurizing gas injector is used in the pressurization system of liquid propellant rocket to reduce incoming gas velocity and distribute the gas in the tank. Temperature distribution in the propellant tank ullage is varied according to the gas injector shape, and it has influence on the required pressurant gas and thermal phenomena in the tank. In this paper, diffuser type gas injector was studied to make the ullage have stratified temperature distribution. Injected gas flow at the outlet of prototype diffuser was visulized using particle image velocimetry method and it was compared with the results of calculation. Calculation was well agreed with measurement and was used as an inlet condition of propellant tank ullage calculation.

Calculation of pressurization efficiency of cryogenic propellant tank (극저온 추진제탱크 가압효율 계산)

  • Kwon, Oh-Sung;Kim, Byung-Hun;Kil, Gyoung-Sub;Han, Sang-Yeop
    • Aerospace Engineering and Technology
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    • v.12 no.2
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    • pp.83-90
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    • 2013
  • In this paper, the energy flows related to cryogenic propellant tank ullage were understood and pressurization efficiency of the tank was calculated using propellant feeding test data with the help of calculation program. The related energy flow terms and calculation method of each terms were described. Three test data of different tank pressure and incoming pressurant temperature were used. Under the test conditions, the pressurization efficiency was low in the range of 13.9%~19.3%. The proportion of energy loss to the incoming pressurant energy was in the range of 55.2%~67.6%. The energy loss to the propellant tank wall was the biggest one. If the temperature of incoming pressurant was the same, the rates of each energy flows to the incoming energy were almost the same regardless of the propellant tank pressure. The collapse factor of propellant tank was calculated using test data, and the relation of it to the heat loss rate was observed.

Investigation on Temperature Drop during Pressurant Discharging from Pressurant Tank of Liquid Rocket Propulsion System (I) (액체로켓추진시스템의 가압제 탱크에서 가압제 토출시 온도강하율에 대한 연구 (I))

  • Chung, Yong-Gahp;Kwon, Oh-Sung;Cho, Nam-Kyung;Han, Sang-Yeop;Cho, In-Hyun
    • Journal of the Korean Society of Propulsion Engineers
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    • v.11 no.2
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    • pp.54-61
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    • 2007
  • Propellant pressurization system in liquid rocket propulsion system plays a role supplying pressurant gas at a controlled pressure into the ullage space of propellant tanks. The most important design parameter for such propellant pressurization system is the temperature of pressurant gas fed from pressurant tank. Such pressurant is gaseous state, of which density is very sensitive to the temperature of pressurant. Generally for the propulsion system, which requires high thrust and is consisted of cryogenic propellant the pressurant is stored at high density and high pressure to reduce the weight of pressurant tanks, which are placed inside of cryogenic propellant tank. That is called cryogenic storage pressurization system. This study investigates the temperature variation of pressurant at the time when the pressurant is coming out of pressurant tank experimentally as well as numerically. Fluids used in this study are air and liquid oxygen as outer fluid and gaseous nitrogen and gaseous helium as pressurant respectively.

An Introduction to Mounting Methods and Applications of Propellant Tank for Space Vehicles (우주비행체용 추진제 탱크의 마운팅 방안 및 적용사례 소개)

  • Park, Jong-Chan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.11a
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    • pp.54-58
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    • 2006
  • There are many kinds of propellant tank for space systems, which should be designed and manufactured considering lots of conditions such as pressure of inside and outside, temperature and weight, etc. Among them, it is the one of the most important factors that the tanks could be designed to suspend and support the applied static and dynamic loads. Tank mounting, that installs and supports a tank in the structure, is a method that should be considered the rigid and tight jointing mechanism, including the manufacturing simplicity, the light weight and the economical budget. Methods and features for several propellant tank mountings are introduced in this paper with the applications for those in some foreign space program.

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Prediction of Pressurant Mass Requirement for Propellant Tank with Operating Condition Variation (운용조건 변화에 따른 추진제탱크 가압가스 요구량 예측)

  • Kwon, Oh-Sung;Han, Sang-Yeop;Cho, In-Hyun
    • Aerospace Engineering and Technology
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    • v.10 no.1
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    • pp.54-62
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    • 2011
  • The pressurant mass required for propellant tank pressurization with operating condition variation was estimated by using the numerical model already developed for this purpose. The model was applied to the concept design results of KSLV-II first stage oxygen tank. The supplied pressurant temperature, oxygen volumetric flow rate, and the ratio of length to diameter of the tank were selected as variables. The required pressurant mass and mass flow rate, collapse factor, ullage temperature distribution were predicted, and the results showed that the pressurant temperature had the largest effect on the amount of the required pressurant mass. The pressurizing efficiency of the propellant tank was calculated through analyzing energy distribution in the ullage. It was found that the gas-to-wall heat transfer in the ullage was dominant, and much of the pressurant energy was lost to tank wall heating.

The Way of Determinating the Optimal Parameters of the Propellant Tank Pressurization Gas in the Feeding System for Liquid Rocket Engine (액체로켓 추진기관의 추진제탱크 가압시스템 최적변수 설계 방법)

  • Bershadskiy V.A.;Cho Kie-Joo;Lim Seok-Hee;Jung Young-Suk;Cho Gyu-Sik;Oh Seung-Hyub
    • Journal of the Korean Society of Propulsion Engineers
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    • v.9 no.2
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    • pp.62-69
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    • 2005
  • The design method to calculate the main features of propellant tank pressurization system during the development procedure of propellant feed system of the liquid rocket engine was suggested. We have considered the influences of parameters of pressurization gas on the efficiency of the thermodynamic processes in the tank. The optimum value of temperature and velocity of pressurization gas at the entrance of tank are obtained by the suggested way.

Required Pressurant Mass for Cryogenic Propellant Tank with Pressurant Temperature Variation (가압가스 온도에 따른 극저온 추진제탱크 가압가스 요구량)

  • Kwon, Oh-Sung;Kim, Byung-Hun;Cho, In-Hyun;Ko, Young-Sung
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.12
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    • pp.1202-1208
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    • 2010
  • The prediction of the required pressurant mass for maintaining the pressure of propellant tanks during propellant feeding is an important issue in designing pressurization system. The temperature of pressurant fed into propellant tank is the critical factor in the required pressurant mass and is one of the most crucial design parameters in the development of pressurization system including designing the weight of pressurant tanks and the size of heat exchanger. Hence a series of propellant drainage tests by pressurizing propellant stored in a cryogenic propellant tank have been performed with measuring the temperature distribution inside ullage and the required pressurant mass according to the temperature condition of pressurant. Results shows that the required pressurant mass decreases as the temperature of pressurant increases. However, the rate of the actual pressurant mass to the ideal required pressurant mass increases.