• Aerospace Engineering and Technology
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• v.11 no.2
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• pp.109-116
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• 2012

A vent-relief valve performs as a safety-valve assembly for liquid propellant feeding system of space launch vehicle, which relives pressurant propellant tanks during the filling and the flight. At vent mode, valve is opened and closed by driving pneumatic pressure, and at relief mode, valve is automatically operated to set relief pressure. In this study, we have analyzed a basic layout of vent-relief valve which is designed using foreign LVs(Saturn) to satisfy requirements of Korean Space Launch Vehicle. The simulation model of vent-relief valve is designed by using the AMESim code to verify design parameters and evaluate pneumatic behaviors of valve. In this study, we performed dynamic characteristic simulations on design parameters. And we could predict opening/closing time and pressures, operating performances on design parameters. Using this results, we could suggest detail design and boundary conditions of design.

• KSBB Journal
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• v.11 no.4
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• pp.405-410
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• 1996

This paper discussed the dispersion effect according to the geometrical variation of an internal-loop spparatus by the method of pulse injection of a tracer. The Bodenstein number, which is the dimensionless group characterizing the effect of dispersion, was decreased with increasing the superficial gas velocity in the 50L and the 500L apparatus. But, in the 5L apparatus, the Bodenstein number was increased with increasing the superficial gas velocity in the range of 0 to 2cm/sec but above that range the rate of increase was dropped down to give a constant value because of the phenomenon of gas disengagement. The principle of similarity based on dimensional analysis was applied to design a pilot scale internal-loop apparatus. The effect of dispersion was examined in three different internal-loop apparatus to give the following correlation with major geometric and fluid dynamic properties as variables. B0=4.4014ReG0.117 ReL-0.0065(Hr/Dr)0.76(Dd/Dr)-0.76

• Transactions of the Korean hydrogen and new energy society
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• v.22 no.4
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• pp.534-545
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• 2011

This paper describes the evaluation of kinetic parameters for pyrolysis and carbon char oxidation of residual oil. The non-isothermal pyrolysis of residual oil was carried out with TGA (Thermo-Gravimetric Analyzer) at heating rate of 2, 5, 10 and $20^{\circ}C/min$ up to $800^{\circ}C$ under N2 atmosphere. The first order and nth order pyrolysis models were used to fit the experimental data, and the nth order model was turned out to follow the experimental data more precisely than the first order model. For carbon char oxidation experiment, TGA and four heating rates used in pyrolysis experiment were also adapted. The kinetic parameters for the residual carbon char particle were obtained with three char oxidation model, that is, volume reaction, grain and random pore model. Among them, the random pore model described the char oxidation behaviour quite well, compared to other two models. The non-linear regression method was used to obtain kinetic parameters for both pyrolysis and carbon char oxidation of residual oil.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.1
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• pp.114-123
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• 2002

A supersonic rocket plum flowfield of kerosene/liquid-oxygen based propulsion system has been analysed using the Reynolds-averaged Navier-Stokes equations coupled with a 9-species 14-reaction finite-chemistry model. The result were compared with chemically frozen flow solution to investigate the effect of finite-rate chemistry on the plume flowfield. The computations were performed using a commercial CFD software, FLUENT 5. The finite-rate chemistry solution exhibited higher temperature caused by the reactions within the nozzle. All the chemical reactions within the plum were dominated only in the shear layer and behind the barrel shock reflection region where the temperatures are high and the effect of finite-rate chemical reactions on the flowfield was found to be insignificant. However, the present plume computation including the finite-rate chemical reaction within the plume has revealed major reactions occurring in the plum and their reaction mechanisms.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.3
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• pp.258-263
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• 2012

In this paper the Chemical Propulsion Subsystem of COMS is briefly explained and some telemetries acquired by a series operations of CPS during the Launch and Early Operation Phase of COMS are presented. The pressure and temperature of pressurant tank telemetries are compared with the results of the developed computer program. The changes in pressure are due to the two major phases. The first one is the initialization phases of CPS composed of the venting phase to vent the helium gas in the pipe network from the downstream of the propellant tanks to the thrusters for safety, the priming phase to fill the vented pipe network with oxidizer and fuel respectively and then the pressurization phase to pressurize the ullage of propellant tank to regulated pressure. And the other is the apogee engine firings in which COMS CPS is in the orbit raising phase to use helium as a pressurant to keep the pressure of propellant tank as the liquid apogee engine get fired until COMS reached to the target orbit. This program can be applicable to prepare basis design data of the next Geostationary Satellite CPS.

• Clean Technology
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• v.14 no.4
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• pp.287-292
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• 2008

In this study, computer simulation works have been performed for the capture process of the $CO_2$ and $H_{2}S$ gases contained in the effluent stream using methanol aqueous solution. In order to increase the solubilities of the $CO_2$ and $H_{2}S$ in the methanol aqueous stream, the operating pressure of the absorber was raised to 30 bar and the feeding temperature of the solvent was lowered to $-20^{\circ}C$ by using refrigeration cycle. NRTL liquid activity coefficient model was used to estimate the liquid phase nonidealities for methanol and water. Soave-Redlich-Kwong equation of state was used for the vapor phase nonidealities. Henry's law option was also used to calculate the solubilities of the supercritical noncondensible gases into the methanol aqueous solvent stream.

• Fire Science and Engineering
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• v.33 no.5
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• pp.13-18
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• 2019

In this study, the soot formation characteristics of Jet-A1 liquid fuel droplet flames were investigated by measuring the soot concentration under atmospheric conditions similar to the working environment of the Korea Space Launch Vehicle (KSLV) To obtain the desired atmospheric conditions, the oxygen concentration in the combustion chamber was maintained at 30% and the pressure was varied between 0.1 and 0.06 MPa. The full-field light extinction technique was used to measure the concentration of soot particles generated by applying the identical to 2-mm-diameter Jet-A1 fuel droplets. The soot concentration of the Jet-A1 droplet flames was the highest in the nitrogen-substituted atmosphere and the lowest in the carbon dioxide-substituted atmosphere, despite the pressure. the pressure was decreased the measured soot concentrations reduced as a function of Pⁿ.

• Journal of the Korean Applied Science and Technology
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• v.31 no.1
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• pp.143-150
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• 2014

Recently, supercritical fluid process has been widely used in material synthesis and processing due to their remarkable properties such as high diffusivity, low viscosity, and low surface tension. Supercritical carbon dioxide is the most attractive solvent owing to their characteristics including non-toxic, non-flammable, chemically inert, and also it has moderate critical temperature and critical pressure. In addition, supercritical carbon dioxide would dissolve many small organic molecules and most polymers. In this study, we have prepared the poly (ethylene oxide)/clay nanocomposites using supercritical fluid as a carbon dioxide. Commercialized Cloisites-15A and Cloisites-30B used in this study, which are modified with quaternary ammonium salts. The nanocomposites of polymer/clay were characterized by XRD, TGA and DSC. Poly (ethylene oxide)/clay nanocomposites by supercritical fluid show higher thermal stability than nanocomposites prepared by melt process. In addition, supercritical fluid process would be increased dispersibility of the nanoclay in the matrix.

• Proceedings of the Korean Institute of Surface Engineering Conference
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• 1999.05a
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• pp.102-102
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• 1999

6Mo급 슈퍼 스테인리스강의 내식성은 여러 환경에서 여러 가지의 부식 시험 방법을 통해서 확띤되어 왔다. 이 합금이 보이는 탁월한 내식성 때문에 해수 설비 계통,정유 설비,원자력 발전소의 열교환기 등의 중요 재료로서 그 사용 용도가 급격히 증가하고 있다. 그런데 방사선의 영향을 받게 되는 설비에 금속 재료가 사용되는 경우,특히 경수로의 노내 구조물, 액체 금속로의 열교환기, 핵융합로의 제1벽 재료 등 에서는 합금 원소가 방사성 환경에 의하여 제거되는 현상이 나타난다. 따라서 본 연구에서는 이러한 상황을 미리 재료 제조 차원에서 모사하여 탄소량과 질소량의 함량 을 달리 한 6Mo급 슈퍼 스테인리스강을 제조하여 미세 조직, 기계적 성질 및 부식 특성의 변화에 대하여 연구하였다. 진공 고주파 유도 용해로를 이용하여 탄소량과 질소량이 각기 변화된 슈퍼 스테인리스강을 용해 한 뒤 아르곤 가스 분위기에서 $1180^{\circ}C$로 soaking하고 열간 압연을 행하였다. 열간 압연으로 표변에 생성된 산화 스케일을 불산과 질산의 혼합 용액으로 제거한 뒤 냉간 압연을 행하였다. 이 냉연 판재에 대하여 $1150^{\circ}C$로 소둔하여 각 실험에 사용하였다. 광학 현미경을 이용하여 미세 조직의 변화를 관찰하였으며, 상온과 고온($520^{\circ}C$)에서 인장 시험을 행하였으며, 경도 측정을 행하였다. 또한 양극 분극 시험과 비등 질산 침지 시험 및 비등 40% NaOH 용액에서의 일정 연신율 시험을 행하 였다. 탄소 함량이 증가할수록 항복 강도 및 인장 강도는 증가하고 있으며 연신율은 감 소하는 일반적인 경향을 보였으며 비등 질산 시험에서는 탄소량에 관계없이 매우 우수한 내식성을 쁘였다. 또한 비등 상태의 40% NaOH 용액에서의 응력 부식 균열 시험 결과, 탄소량이 증가할수록 부식 저항성이 증가하고 있는 것으로 평가되었다. 한 편 질소량이 증까할수록 결정립이 미세화되었으며 경도값이 상승하였다. 이들 합금 에 대한 양극 분극 시험 결과, 질소량의 변화가 탄소량의 변화보다 내식성에 큰 영향 을 미치고 있음을 알 수 있었다.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.1
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• pp.35-45
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• 2005

Numerical study is carried out to investigate the effects of chemistry and thermal radiation on the rocket plume flow field at various altitudes. Navier-Stokes equations for compressible flows were solved by a fully-implicit TVD code based on the finite volume method. An infinitely fast chemistry module for hydrocarbon mixture with detailed thermo-chemical properties and a thermal radiation module for optically thick media were incorporated with the fluid dynamics code. The plume flow fields of a kerosene-fueled rocket flying at Mach number zero at sea-level, 1.16 at altitude of 5.06 km and 2.90 at 17.34 km were numerically analyzed. Results showed the plume structures at different altitude conditions with the effects of chemistry and radiation. It is understood that the excess temperature by the chemical reactions in the exhaust gas may not be ignored in the view point of propulsion performance and thermal protection of the rocket base, especially at higher altitude conditions.