• Title, Summary, Keyword: propellant tank

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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 the Spherical Satellite Propellant Tank With Respect to the Change of Location of the Lug and Tank Wall Thickness (지지부 위치와 벽면 두께변화에 따른 구형 인공위성 추진제 탱크의 강도해석)

  • 한근조;장우석;안성찬;심재준;전형용
    • Journal of the Korean Society for Precision Engineering
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    • v.15 no.3
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    • pp.31-37
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    • 1998
  • The structure of satellite consists of six parts which are control system, power system, thermal control system, remote measurement command system, propellant system and thrust system. In these parts, propellant system consists of propellant tank and thrust device. What we want to perform is optimum design to minimize the weight of propellant tank. In order to design optimal propellant tank, several parameters should be adopted from the tank geometry like the relative location of the lug and variation of the wall thickness. The analysis was executed by finite element analysis for finding optimal design parameters. The structure was divided into three parts consisting of the initial thickness zone, the transitional Bone, and the weak zone, whose effects on the pressure vessel strength was investigated. Finally the optimal lug location and the three zone thickness were obtained and the weight was compared with the uniform thickness vessel.

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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.

지지부 위치와 벽면 두께변화에 따른 구형 인공위성 추진제 탱크의 강도해석

  • 한근조;전언찬;김중완;안성찬;심재준
    • Proceedings of the Korean Society of Precision Engineering Conference
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    • pp.528-532
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    • 1997
  • The structure of satellite was of six parts of control system, power system, thermal control system, remote measurement command system, propellant system and thrust system. In these parts, propellant system consists of propellant tank and thrust device. What we want to perform is optimum design to minimaize the weight of propellant tank. In order to design optimal propellant tank, several parameters should be adopted form the tank geometry like the relative location of the lug and variation of the wall thickness. So the analysis was executed by finite element analysis for finding optimal design parameters. The structure was devided into 3 parts, the initial thickness zone, the transitional zone, and the weak zone,whose effects on the pressure vessel strength was investigated. Finally the optimal lug location and the three zone thickness were obtained and the weight was compared with the uniform thickness vessel.

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Measurement of Damping Ratio of Fuel Sloshing in a Baffled Liquid Propellant Tank of KSR-III Rocket (KSR-III 로켓의 액체 연료 탱크 내에서 발생하는 슬로싱 현상의 배플에 의한 감쇄율 측정)

  • Park, Soon-Hong;Yoo, Joon-Tae;Yi, Yeong-Moo
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • pp.172-175
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    • 2002
  • Sloshing of fuel in a liquid propellant tank is an important part of the dynamic and the stability analysis of the rocket. Baffles are installed in a propellant tank to reduce the instability due to sloshing. Multi degree of spring-mass-damper model was used to model sloshing of fuel in an axisymmetric tank. The natural frequencies and damping ratios are estimated. In order to verify the estimated natural frequencies and damping ratios, tests are performed for the real propellant tank of KSR-III with single ring baffle. Results of fuel sloshing analysis are compared with those of tests.

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Measurment of Damping Ratio of Fuel Sloshing in Baffled Liquid Propellant Tank of KSR-III Rocket (KSR-III 로켓의 액체 연료 탱크 내에서 발생하는 슬로슁 현상의 배플에 의한 감쇄율 측정)

  • Park, Soon-Hong;Yoo, Joon-Tae
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • pp.323.2-323
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    • 2002
  • Sloshing of fuel in a liquid propellant tank is an important part of the dynamic and the stability analysis of the rocket. Baffles are installed in a propellant tank to reduce the instability due to sloshing. Multi degree of spring-mass-damper model was used to model sloshing of fuel in an axisymmetric tank. The natural frequencies and damping ratios are estimated. In order to verify the estimated natural frequencies and damping ratios, tests are performed for the real propellant tank of KSR-III with single ring baffle. Results of fuel sloshing analysis are compared with those of tests.

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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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    • 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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Experimental Study on Cryogenic Propellant Circulation using Gas-lift (Gas-lift를 이용한 극저온 추진제의 재순환 성능에 대한 실험)

  • Kwon, Oh-Sung;Lee, Joong-Youp;Chung, Yong-Gahp
    • 유체기계공업학회:학술대회논문집
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    • pp.551-554
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    • 2006
  • Inhibition of propellant temperature rising in liquid propulsion rocket using cryogenic fluid as a propellant is very important. Especially propellant temperature rising during stand-by after filling and pre-pressurization can bring into cavitation in turbo-pump. One of the method preventing propellant temperature rising in cryogenic feeding system is recirculating propellant through the loop composed of propellant tank, feed pipe, and recirculation pipe. The circulation of propellant is promoted through gas-lift effect by gas injection to lower position of recirculation pipe. In this experiment liquid oxygen and gas helium is used as propellant and injection gas. Under atmospheric and pressurized tank ullage condition, helium injection flow-rate is varied to observe the variation of recirculating flow-rate and propellant temperature in the feed pipe. There is appropriate helium injection flow-rate for gas-lift recirculation system.

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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.

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.