• Journal of the Korean Institute of Gas
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• v.9 no.3 s.28
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• pp.27-31
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• 2005

The membrane to be applied inside of the LNG storage tank is provided with corrugations to absorb thermal contraction and expansion caused by LNG temperature and pressure changes. It is very important to measure their thermal strains under LNG temperature by analytical and experimental stress analysis of the membrane. We have developed a stress measurement system using strain gages and measured the strain during cooldown and storing the LNG. We also analyzed the measured data by comparison with the FEM data.

• Journal of Energy Engineering
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• v.21 no.4
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• pp.393-397
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• 2012

In this study, an organic Rankine cycle(ORC) for gas engine waste heat recovery for industry has been constructed and a performance analysis test has been carried out. Shell & tube style heat exchanger has been equipped on an engine exhaust manifold in order to absorb heat of engine exhaust gas into the working fluid(refrigerant R134a). Under 60 kW of engine power output, about 63 kW of engine exhaust gas heat was discharged and the proportion of heat recovered was 68~73% while 43~46 kW of heat was absorbed into working fluid. Consequently rated power output of ORC was 4.6 kW while the ratio of rated power output to engine exhaust gas heat was 7.3%.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.321-326
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• 2006

Vitiated air heater which could supply air of 700K and 6 bar was designed conceptually for the firing test on the ground of the air breathing propulsion engines. This vitiated air heater consists of premixer with air and excessive gas oxygen, mixing head, combustor with gas passage, convergent-divergent nozzle and diffuser. the fuel was natural gas and/or liquefied natural gas. Through computational fluid dynamics, each component of the air heater was analyzed and flame-holding after ignition was investigated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.505-509
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• 2011

The combustion chamber and nozzle of a liquid rocket engine should be protected from the high temperature combustion gas generated by the chamber. An upper-stage nozzle extension has a large expansion ratio, therefore, The light-weight refractory materials have been used since the weight impact on the launcher performance is crucial. Gas film cooling and ablative cooling methods were used before, but were not applicable nowadays. Radiative cooling method with niobium alloy, Ni-based superalloy and ceramic based composite has been used to this day.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.613-617
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• 2011

Korea Aerospace Research Institute has been designed and manufactured various thurst nozzles of the scramjet engine for optimized configuration. The test campaign for thurst nozzle characteristics was performed at T4 free-piston shock tunnel in University of Queensland, Australia. Total 8 kinds of thrust nozzles and 2 kinds of side walls were manufactured for this campaign. In this paper, the design and specification of thrust nozzles was reported. Based on the static pressure distribution of the engine and pitot pressure distributions at nozzle exit, The positive net thurst was observed with baseline case of the test campaign.

• Journal of the Korean Institute of Illuminating and Electrical Installation Engineers
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• v.21 no.1
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• pp.19-27
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• 2007

In this paper, we develope and implement a TFT-LCD cell defects detection algorithm using morphology. To detect the bright line or dark line defects and the bright pixel or dark pixel defects of the TFT-LCD cells, we determine the shape of the morphology operators considering the shape characteristics of the TFT-LCD sub pixels. Using dilation, erosion, and the subtraction operators, we extract gray level defects information. Then, we apply the optimal threshold method which shows the best results in terms of several criteria. Finally, we determine the defects using labelling method. From various experiments using TFT-LCD panels, the proposed algorithm shows superior results.

• Korean Journal of Air-Conditioning and Refrigeration Engineering
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• v.17 no.1
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• pp.39-46
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• 2005

The present study concerns an experimental study of a R-22 heat pump system consisted of liquid and liquid heat exchangers. The test was performed for various systems of a single-, tandem-, and two stage-cycle at the same environmental conditions of temperature. Various experiments of the heat pump system were peformed to compare the heating capacity and COP, when the outdoor temperature is near $-15^{\circ}C$ and the indoor temperature is $20^{\circ}C.$ As the results of the present study, the system of Tandem(parallel) cycle showed the best heating performance, while the discharge temperature of refrigerant was too high. In case of the system of two stage cycle, the performance characteristics were significantly improved by employing the inter cooler.

• Proceedings of the Materials Research Society of Korea Conference
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• 2011.05a
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• pp.37.2-37.2
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• 2011

반도체공정에서 Photo-lithography는 특정 광원을 사용하여 구현하고자 하는 패턴을 기판상에 형성하는 기술이다. 이러한 Photo-lithography 공정에서는 패턴이 형성되어 있는 마스크가 핵심적인 역할을 하며 반도체소자의 전체적인 성능을 결정한다. 이에 따라 Photo-lithography용 마스크에 사용되는 Blank 마스크는 Defect의 최소화 및 우수한 평탄도 등의 조건들이 요구되고 있다. 이러한 Blank 마스크 재료로 광원을 효율적으로 투과시키는 성질이 우수하고 다른 재료에 비해 열팽창계수가 작은 석영기판이 사용되고 있다. 석영 기반의 마스크는 UV Lithography에서 주로 사용되고 있으며 그 밖에 UV-NIL (Nano Imrpint Lithography), EUVL (Extreme Ultra Violet Lithography) 등에도 이용되고 있다. 석영기판을 가공하여 Blank 마스크로 제작하기 위해 석영기판의 Lapping/Polishing 등이 핵심기술이며 현재 일본에서 전량 수입에 의존하고 있어, 이에 대한 연구의 필요성이 절실한 상황이다. 본 연구에서는 Blank 마스크제작을 위한 석영기판의 Polishing 공정에 사용되는 Ceria Slurry의 특성 연구 및 이에 따른 연마평가를 실시하였으며 첨가제의 조건에 따른 pH/Viscosity/Stability 등의 물리적인 특성을 관찰하여 석영기판 Polishing에 효율적인 Ceria slurry의 최적조건을 도출했다. 또한, 조건에 따른 Slurry의 정확한 분석을 위해 Zeta Potential Analyzer를 이용하여 연마입자의 크기 및 Zeta Potential에 대한 평가를 실시한 후 연마제와 석영기판의 Interaction force를 측정하였다. 상기 실험에 의해 얻어진 최적화된 연마 공정 조건하에서 Ceria slurry를 사용하여 연마평가를 실시함으로써 Removal Rate/Roughness 등의 결과를 관찰하였다. 본 연구를 통해 반도체 photo mask 제작을 위한 Ceria slurry의 주요특성을 파악하고 석영기판의 Polishing에 효율적인 조건을 도출함으로써 Lithography 마스크를 효율적으로 제작할 수 있을 것으로 예상된다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.75-81
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• 2006

The propulsion system of KSLV-I second stage is engine with high expansion ratio and its starting altitude is high. To verify the performance of engine before the launch in the ground, high altitude test facility to simulate its operating condition is necessary. This material is about the concept design of high altitude simulation test facility for second stage engine. And it will be the basis for the construction of test facility and the test of engine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.365-368
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• 2009

A new concept of a small thruster for altitude control of a micro/nano class satellite is developed, which utilizes the pulsed laser energy. As the laser-based thruster does not require burning of any fuel, it gives promise of small satellite design criteria, namely light weight and cost effectiveness. In this paper, we develop gel-type material for generating strong plasma plume for enhancing thrust for propulsion. Moreover, we quantify the level of thrust via the momentum coupling coefficient measured by the pendulum system. We discover that the driving force is significantly improved via the gel-typed propellant for laser ablation.