• 생명과학회지
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• 제28권11호
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• pp.1277-1284
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• 2018

본 연구에서는 효모염색체내에 다양한 유전자 발현 cassette를 도입하기 위해 Cre/loxP system을 가진 repeated yeast integrative plasmid (R-YIp)를 구축하였다. R-YIp는 반복적으로 형질전환체를 선별할 수 있는 selective marker (CgTRP1)와 loxP 서열, 그리고 integration을 위한 목적서열을 함유하고 있어 같은 염색체의 동일한 위치에 여러 개의 유전자 발현 cassette를 도입하는 것이 가능하다. 따라서 xylan/xylose 대사에 관련된 endoxylanase (XYLP), ${\beta}$-xylosidase (XYLB), xylose reductase (GRE3) 그리고xylitol dehydrogenase (XYL2)의 효모염색체내에 도입을 시도하였다. 먼저 XYLP, XYLB, GRE3그리고 XYL2 유전자의 효율적인 발현을 위한 promoter를 선별하기 위해 pGMF-GENE과 pAMF-GENE plasmid를 구축하였고, 각 유전자들의 발현에 GAL10 promoter가 적합함을 확인하였다. 다음으로 GAL10p-GENE-GAL7t cassette를 가진 pRS-GENE plasmid (R-YIp)를 구축하여, 반복적 integration 과정과 selective marker의 제거를 통해 각각의 R-YIps를 효모 7번염색체에 순차적으로 도입하였다. R-YIp system을 통해 효모염색체내에 도입된 유전자들은 모두 안정적으로 발현되었고, 활성형의 재조합효소를 생산함을 확인할 수 있었다. 따라서 다수의 외래유전자를 효모염색체내 도입함에 있어 selective marker와 숙주세포 선택의 한계를 R-YIp system을 통해 어느 정도 극복할 수 있을 것이라 기대한다.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2006년도 제33회 KOSCO SYMPOSIUM 논문집
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• pp.151-155
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• 2006

The large amount of energy is consumed in a process for keeping the high temperature melting pool. For this reason, in addition to the wastes input to keep the high temperature melting pool, it is necessary for an auxiliary fuel and LOx to throw into the melting pool. So in this study, using a new melting furnace system, the experiments to keep the melting pool with minimal energy without throwing an auxiliary fuel and LOx was carried out. Also it is hoped that the results of the experiment will be available to analyze keeping a melting pool and behavior in a melting furnace.

• International Journal of Aeronautical and Space Sciences
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• 제16권2호
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• pp.254-263
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• 2015

In this study, numerical simulations are carried out to investigate the dynamic SGS model effects in a Kerosene-LOx coaxial swirl injector under high pressure conditions. The turbulent model is based on large-eddy simulation (LES) with real-fluid transport and thermodynamics. To assess the effect of the dynamic subgrid-scale (SGS) model, the dynamic SGS model is compared with that of the algebraic SGS model. In a swirl injector under supercritical pressure, the characteristics of temporal pressure fluctuation and power spectral density (PSD) present comparable discrepancies dependant on the SGS models, which affect the mixing characteristics. Mixing efficiency and the probability density (PDF) function are conducted for a statistical description of the turbulent flow fields according to the SGS models. The back-scattering of turbulent kinetic energy is estimated in terms of the film thickness of the swirl injector.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2012년도 제45회 KOSCO SYMPOSIUM 초록집
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• pp.33-35
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• 2012

This study has been mainly motivated to numerically model the supercritical mixing and combustion processes encountered in the liquid propellant rocket engines. In the present approach, turbulence is represented by the extended k-e model. To account for the real fluid effects, the propellant mixture properties are calculated by using generalized cubic equation of state. In order to realistically represent the turbulence-chemistry interaction in the turbulent nonpremixed flames, the flamelet approach based on the real fluid flamelet library has been adopted. Based on numerical results, the detailed discussions are made for the effects of swirl number on flame structure of supercritical kerosene/LOx double swirl coaxial injector.

• Tribology and Lubricants
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• 제26권6호
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• pp.322-328
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• 2010

An inter-propellant seal (IPS) for 75 ton class thrust turbopump was tested. Leakage characteristics were presented with a given range of pressure difference under cryogenic as well as room temperature conditions. For cryogenic tests, liquid nitrogen was used as analogic fluid of liquid oxygen (LOX) while water was used instead of kerosene for room temperature condition. Test results showed that IPS had satisfactory leakage performance. Additionally endurance test was conducted to prove the life time of manufactured IPS and the tested IPS had successfully survived during required life time, 2100 seconds.

• Tribology and Lubricants
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• 제24권6호
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• pp.349-354
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• 2008

An inter-propellant seal (IPS) for high thrust turbopump is designed. With given operating conditions and requirements, the inter-propellant seal is designed to satisfy the leakage characteristics which is less than 0.1% of normal flow rate of pumps. A numerical analysis is developed to predict the leakage flow rate. The results show that the maximum leakage of LOX and kerosene are less than 0.1% of normal flow rate of pumps, respectively. Based on the numerical analysis results, the detail of IPS is performed. Finally a prototype of IPS is manufactured to perform sets of performance tests in the near future.

• 한국추진공학회지
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• 제5권4호
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• pp.67-74
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• 2001

국가우주개발 중장기 계획에 의거, 인공위성 발사체 독자 개발에 필요한 필수기술을 확보하기 위하여 액체추진제 로켓엔진 개발의 필요성이 대두되었으며, 이에 따라 한국항공우주연구원은 과학로켓 3호(KSR-III)에 적용하기 위한 액체추진기관을 개발하고 있다. 이러한 목적으로 kerosene/LOx를 사용하며 13톤급의 추력을 낼 수 있는 시제엔진이 설계, 제작되었으며 이 엔진에 대한 연소시험이 실시되었다. 본 연구에서는 액체로켓 시제엔진 시험을 위한 일련의 시험절차와 시험방법을 소개하며, 시험을 통하여 획득한 정특성자료 및 동특성자료에 대하여 분석하였다.

• 대한구순구개열학회지
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• 제11권2호
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• pp.65-70
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• 2008

Cleft lip and/or palate are common birth defects in humans and the causes including multiple genetic and environmental factors are complex. Combinations of genetic, biochemical, and embryological approaches in the laboratory mice are used to investigate the molecular mechanisms underlying normal craniofacial development and the congenital craniofacial malformations including cleft lip and/or palate. Both forward and reverse genetic approaches are used. The forward genetic approach involves identification of causative genes and molecular pathways disrupted by uncharacterized mutations that cause craniofacial malformations including cleft lip and/or cleft palate. The reverse genetic approach involves generation and analyses of mice carrying null or conditional mutations using the Cre-loxP mediated gene targeting techniques.

• 항공우주기술
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• 제12권1호
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• pp.81-86
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• 2013

본 연구에서는 다양한 발사체 추진기관 공급계 배관 자재 중 STS 300 계열의 금속보다 강도가 높고 용접성이 우수할 것이라고 판단되는 21-6-9 합금소재를 이용하여 산화제 주배관의 시편을 제작 하였다. 제작된 시편은 내압 시험을 수행하여 요구되는 내압 강도를 유지할 수 있는지를 확인하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.211-215
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• 2004

For design of cryogenic propellant feeding system, one of the main requirements is to meet temperature requirement for satisfying turbo-pump NPSH requirement. In this paper improved method of estimating the thermal stratification in liquid oxygen tank is presented to help design. In the case of liquid rocket using turbo-pump, the inner pressure of liquid oxygen tank is maintained low, so vaporization of liquid oxygen is generally occurred. In this paper, inner process of LOX tank is analyzed by two phase flow modeling. The vaporization rate and required helium mass is investigated.