• 방재와보험
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• s.122
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• pp.36-44
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• 2007

BP 텍사스 시티의 석유정제소의 화재폭발은 2005년에 가장 많은 인명의 손실을 끼친 유동화자산의 화재폭발사고로서 15인의 생명을 앗아가고 200여 명의 사람을 다치게 하였다. 트럭 한 대의 역화(내연기관의 부정폭발)에서 시작된 점화원은 이성질체화시스템(ISOM) 대기암 통기구에서의 가연성 탄화수소 액체와 증발 기체를 발화시켰다. 화학안전위원회는 그 사고를 조사 및 검토한 후 BP사가 모든 면에서 기계적인 결함과 함께 안전성이 불완전하였음을 발견하였다. 본 고는 저자들이 미국화학안전위험조사위원회에 제출한 이들의 조사보고서를 번역 게재한 것이다.

• Proceedings of the Korean Fiber Society Conference
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• 2002.04a
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• pp.470-473
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• 2002

나일론 6은 유연한 분자사슬로 구성된 고분자이지만 분자간에 많은 수소결합을 형성 하고 있기 때문에 비교적 높은 용융온도를 가지고 있으나 연신성이 좋지 않고 고탄성의 섬유를 얻기가 어려우며 상온 및 저온에서의 내충격성도 취약하다고 알려져 있다[1]. 나일론 6의 이러한 단점은 각종 산업용소재로 이용할 경우 많은 문제점을 유발하게 되어 이를 극복하기 위한 연구들이 시도되고 있다. 그중 나일론 6에 액체암모니아나 요드 등을 이용하여 가소화 하거나 용제를 사용함으로써 해결하고자 하는 연구들이 진행되어 왔었다[2,3]. (중략)

• Proceedings of the Korea Air Pollution Research Association Conference
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• 2000.11a
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• pp.255-256
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• 2000

휘발성 유기화합물(Volatile Organic Compounds : VOCs)은 각종 산업체에서 많이 사용되고 있는 용매와 화학 및 제약공장 플라스틱의 건조공정에서 배출되는 유기가스 등까지 매우 다양하며, 저비점 액체연료, 파라핀, 올레핀, 방향족 화합물등 우리 생활주변에서 흔하게 사용되는 탄화수소류들이 거의 VOCs이다. 이러한 VOCs를 제어하기 위하여 폭넓은 제어기술의 연구 및 개발이 진행되고 있다. (중략)

• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.3
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• pp.17-24
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• 2016

The reacting flows of gaseous hydrogen/liquid oxygen 2D coaxial shear injector with varying recess length are numerically analyzed. The standard ${\kappa}-e$ model and laminar flamelet model are adopted for the steady turbulent combustion with the ideal and real gas equations. As the recess length increases, the recirculating region in the combustion chamber expands and the vorticity is intensified. Also, the variations of temperature, products, and pressure are strongly related to the recess length. The results show that an efficient combustor can be obtained by the introduction of the recessed injector.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.303-306
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• 2008

After the successful flight test of X-43A, U.S. Airforce is developing missile-type X-51A SED (Scramjet Engine Demonstrator-Wave Rider). X-51A using PWR (Pratt and Whitney Rocketdyne) X-1 hydrocarbon fueled scramjet engine will have a ground test in 2008 and flight test in 2009. Technologies established though the X-51A program will be transferred to DARPA's Falcon program developing HTV (Hypersonic Test Vehicle)-3X and HCV (Hypersonic Cruise Vehicle). Present paper is an overview of propulsion core technologies of X-51 such as regenerative cooling of engine structures and combustion using liquid/supercritical JP-7 fuel.

• Journal of Hydrogen and New Energy
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• v.10 no.3
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• pp.151-157
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• 1999

The development of hydrogen vehicles has been actively progressed in the developed countries such as U. S., Japan and Germany. The most important technology of using hydrogen fuel is to develope a compatible storage tank with respect to the fossil fuel tank. Among many storage methods, the liquid hydrogen is the most desirable state because of the lowest volume and weight. The metal hydride tank is too heavy and the compressed hydrogen tank is too bulky. Because of these reasons, it is the principal purpose to analyze the theoretical heat transfer for designing and manufacturing an actual $LH_2$ tank. The insulation methods of the room between inner and outer vessel are non-vacuum, vacuum, vacuum with MLI(Multi-Layer Insulation). According to the results of the numerically calculated heat leak through the walls of the $LH_2$ tank, the vacuum insulated tank has 20 times and the MLI tank has 5616 times less heat leak than the non-vacuum tank.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.13-16
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• 2007

Fuel cell was used as a propulsion system for unmanned aerial vehicles (UAV) in the present study. Fuel cell propulsion system are an ideal alternative power source with high energy density for high-endurance UAV. Fuel cell power system provides UAV up to five times the energy densiη of existing batteries. Sodium borohydride, stored in liquid state, was selected as a hydrogen source. Hydrogen generation system consists of catalytic reactor, pump, fuel cartridge, and separator. Hybrid power management system (PMS) between fuel cell and lithium-polymer ba야ery was developed. Motor, pump, and fans， operated on battery power controlled by feedback signals of fuel cell system. Battery was recharged by surpuls powr of fuel cell.

• Korean Journal of Air-Conditioning and Refrigeration Engineering
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• v.9 no.3
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• pp.389-400
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• 1997

A thermodynamic cycle analysis is performed for refrigerator-precooled Linde-Hampson hydrogen liquefiers, including catalysts for the ortho-to-para(o-p) conversion. three different configurations of the liquefying system, depending upon the method of the o-p conversion, are selected for the analysis. After some simple and justifiable models are introduced, a general analysis program to predict the liquid yield and the figure of merit(FOM) is developed with incorporating the commercial computer code for the hydrogen properties. The discussion is focused on the effect of the two primary design parameters-the precooling temperature and the high pressrure of hydrogen. When the precooling temperature is in the range between 45 and 60 K, the optimal high pressure for the maximal liquid yield is found to be in the range between 100 to 140 bar, regardless of the o-p conversion. However, the FOM can be maximized at slightly smaller values of high pressures. It is remarkable to observe that the lower precooling temperatures are favorable since both the liquid yield and the FOM can be obtained without compressing hygrogen to extremely high pressures.

• Journal of Hydrogen and New Energy
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• v.13 no.3
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• pp.190-196
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• 2002

Ni/MH 박막전지의 전극으로 사용될 수 $Mg_{2}Ni$박막을 스퍼터링방법으로 제조하였다. $Mg_{2}Ni$합금박막은 Mg, Ni타?을 이용하여 동시에 스퍼터링함으로서 제조하였다. KOH 액체전해질 및 $Ni(OH)_2$전극을 이용하여 전기화학실험을 하였다. $Mg_2Ni$ 박막의 초기 싸이클 특성에 미치는 열처리 효과를 조사하기 위하여, $200-550^{\circ}C$로 변화시키면서 진공중에서 열처리를 하였다. 열처리온도가 $300^{\circ}C$ 이하에서는 초기방전용량이 증가하였으며, $400^{\circ}C$ 열처리시에는 활성화시의 방전용량이 약 160mAh/g으로 가장 크게 나타났다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.397-400
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• 2008

Traditional propellants which have a hypergolic characteristic have a high performance but also have disadvantages of toxicity and complex handling requirement. In order to replace these propellants, one of the alternatives is hydrogen peroxide which generates high temperature oxygen and water vapor after catalytic reaction. In this paper, autoignition characteristics of kerosene by decomposed hydrogen peroxide were investigated to perform fundamental research for designing a thruster using hydrogen peroxide and kerosene propellants. Contraction ratio, whether flame holder exists or not, and feeding pressure of propellants were selected as variables. From the experiments for different mixture ratio, we confirmed the ignition stability is strongly affected by a feeding pressure of propellants.