• 기계와재료
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• v.22 no.3
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• pp.120-129
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• 2010

획기적으로 선명한 영상의 구현, 휴대 용이성 및 정확한 온도분포의 구현이 가능한 초점면 배열 방식의 적외선 검출기는 탐지도 및 분해능 향상을 위해 액체질소 온도수준의 극저온냉각을 요구한다. 냉동기의 저온부에 적외선 검출기를 직접 부착하는 일체형 스터링 극저온냉동기는 효율적인 적외선 검출기의 냉각이 가능할 뿐 만 아니라, 소형/경량화가 용이하여, 기동 및 휴대용 열상장비용 극저온냉각을 위해 많이 활용되고 있다. 적외선 검출기 냉각용 즉저온냉동기는 다양한 열/진동/충격/전자파 등의 운용환경조건에서 검출기를 액체질소 온도수준으로 냉각/유지할 수 있어야 하며, 안정적인 시스템의 운용을 위한 충분한 신뢰성이 확보되어야 한다. 본 고에서는 민군 겸용기술사업을 통해 국내에서 개발된 열상장비 냉각용 일체형 스터링냉동기의 기술적 특징 및 환경/신뢰성 시험 결과를 소개하고자 한다.

• 유체기계공업학회:학술대회논문집
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• 2005.12a
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• pp.348-353
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• 2005

A cryogenic test facility has been developed to perform inducer and pump tests using liquid nitrogen. Performance tests of a turbopump in the maximum 50ton-thrust class can be performed with cryogenic fluid in the facility which operates at a temperature around $-196^{\circ}C$ with the rotational speed up to 30,000rpm. To verify the reliability of the cryogenic pump test facility, hydraulic performance tests of an inducer were accomplished, and their results were compared with the result from a water test The results confirm the reliability of the cryogenic test facility, and it is expected to contribute for on-going development of a turbopump for liquid rocket engines.

• The KSFM Journal of Fluid Machinery
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• v.9 no.4 s.37
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• pp.20-26
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• 2006

A cryogenic test facility has been developed to perform inducer and pump tests using liquid nitrogen. Performance tests of a turbopump in the maximum 50ton-thrust class can be performed with cryogenic fluid in the facility which operates at a temperature around -196oC with the rotational speed up to 30,000rpm To verify the reliability of the cryogenic pump test facility, hydraulic performance tests of an inducer were accomplished, and their results were compared with the result from a water test. The results confirm the reliability of the cryogenic test facility, and it is expected to contribute for on-going development of a turbopump for liquid rocket engines.

• Transactions of the Korean hydrogen and new energy society
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• v.34 no.5
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• pp.549-554
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• 2023

In this paper, three kinds of studies have been completed to obtain highly purified carbon dioxide having more than 7N purity as an electronic grade quality. PRO/II with PROVISION release January 2023 from AVEVA company was used, and Peng-Robinson equation of the state model with Twu's alpha function was selected for the modeling of the cryogenic distillation process. When using LN2 cold heat, we can obtain highest recovery of carbon dioxide as a bottom product for a cryogenic distillation column.

• Journal of the KSME
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• v.56 no.7
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• pp.51-54
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• 2016

이 글에서는 티타늄 합금의 절삭가공 시 공구수명을 향상시키기 위해 적용하는 액체질소를 사용한 극저온가공에서, 공구의 냉각 균일성을 향상시키기 위한 방법으로 극저온간접냉각(Indirect cryogenic cooling) 방식을 소개한다.

• Proceedings of the Korean Radioactive Waste Society Conference
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• 2008.11a
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• pp.25-26
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• 2008

• Proceedings of the Korean Vacuum Society Conference
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• 2006.02a
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• pp.48-48
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• 2006

• Proceedings of the Korean Radioactive Waste Society Conference
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• 2009.06a
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• pp.53-54
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• 2009

• Superconductivity and Cryogenics
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• v.6 no.2
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• pp.42-46
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• 2004

금속 테이프 위에 초전도층을 박막형태로 증착시켜서 제조되는 고온초전도 선재인 coated conductor (CC)는 powder-in-tube 공정으로 제조되는 1세대 고온초전도 선재에 비해 액체 질소 온도에서 높은 임계 전류 밀도와 우수한 자장 특성을 가지면서 더 경제적으로 제조 가능하기 때문에 액체질소온도에서 작동 가능한 초전도전력기기 개발에 반드시 필요한 부분으로 인식되고 있다. 최근 국내외적으로 다양한 증착 방법을 사용하여 전력기기 응용이 가능한 장선의 CC 제조공정을 개발하려는 연구가 활발히 진행되고 있다. 특히 외국의 경우 이미 CC 선재의 상업화를 위해 기업체가 중심이 되어 집중적인 연구 개발이 이루어지고 있다.(중략)

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.4
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• pp.333-342
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• 2016

Liquid rocket propulsion is a system that produces required thrust for satellites and space launch vehicles by using chemical reactions of a liquid fuel and a liquid oxidizer. Monomethylhydrazine/dinitrogen tetroxide, liquid hydrogen/liquid oxygen and RP-1/liquid oxygen are typical combinations of liquid propellants commonly used for the liquid rocket propulsion system. The objective of the present study is to investigate useful design and performance data of liquid rocket engine by conducting a numerical analysis of thermochemical reactions of liquid rocket propellants. For this, final products and chemical compositions of three liquid propellant combinations are calculated using equilibrium constants of major elementary equilibrium reactions when reactants remain in chemical equilibrium state after combustion process. In addition, flame temperature and specific impulse are estimated.