• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.155-158
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• 2007

As a secondary stage of the liquid rocket engine development test, turbopump-gas generator powerpack tests are being performed. The schematics of the test hardware and the test facility for the TP+GG coupled test are presented. The results of a preliminary test results for the verification of the propellant supply system of the test facility are also presented. Based on the preliminary tests results, the verification of the propellants supply systems of the facility system was performed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.15-18
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• 2008

This study fulfilled analysis of startup characteristics of Turbo pump unit-Gas generator open loop test from the viewpoint of simulation. The test results were investigated and the calculated results were compared to test results. The curve for RPM developing predicted by simulation agreed well with test result. The slope of transient combustion pressure of gas generator correspond with test result.

• Journal of the Korean Institute of Gas
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• v.10 no.4 s.33
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• pp.1-5
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• 2006

With the rapid increase in gas consumption, the role of pipelines as a transportation means of natural gas is increasing. In general, when natural gas is being transported in pipelines, some liquid mainly from formation of condensate is introduced and this phenomenon makes operational problems more complex in the gas industry. Thus, an appropriate method is necessary for predicting the effect of presence of gas condensate on operational efficiency. In this study, a statistical model was developed using an integrated single- and two-phase flows concept. Using this model, the effects of the incipient point of gas condensate and its quantity on outlet pressure were analyzed. Also, the effect of variations of flow regimes in two-phase region on outlet pressure after the incipient point was analyzed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.2-3
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• 2002

일반적으로 연소과정에서 발생한 고온고압의 연소가스로 인하여 액체추진기관의 연소실 및 노즐 벽면 그리고 추진기관 후방부위에 대류열전달(Convective heat transfer)과 복사열전달(Thermal radiative heat transfer)이 발생하는 것으로 알려져 있으며, 액체추진기관에서 발생하는 복사열전달 현상은 재생냉각장치의 열입력량 예측 및 발사체의 추진기관 후방부위에 탑재되는 전자장이 및 구조물의 열적환경(Thermal environmental phenomena)을 분석하는데 매우 중요하다. 이에 본 연구에서는 노즐 후방부위에서 발생하는 복사열전달량(Radiative heat transfer rate)을 측정하고 연소압(Chamber pressure)과 혼합비(Mixture ratio)에 따른 영향을 파악하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.97-103
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• 2011

This paper describes the main considerations for the development of engine emergency protection system and applications to preliminary engine development tests. Emergency protection system performed its role without failure to shutdown test very quickly for the prevention of development of malfunctioning of test articles, which protected test articles and test facility in all abnormal situation occurred during preliminary engine development test program. This results will be used for the development of engine emergency protection system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.62-65
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• 2009

This study for prediction of startup characteristics for 30 tonf liquid rocket engine TP-GG-CC coupled test was performed on the basis of the previous TP-GG test and prediction results. For determining the valve sequence the startup analysis was performed by the specified program for several main valve time and the adequate valve sequence for startup could be obtained.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.178-182
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• 2007

This paper reviews on the LRE health monitoring and emergency protection system to protect test object engine system and engine test facility, in case of various fault occurrence at LRE testing. General composition and major technical consideration of LRE health monitoring system and emergency protection system are reviewed. Moreover, some application of LRE health monitoring/emergency protection system to development test of major LRE component such as turbopump testing, gas generator and combustion chamber test are reviewed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.676-677
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• 2010

In Naro Space Center, Naro launch vehicle launched 2 times. Launch pad for Naro launch vehicle in Naro space center equipped propellant feeding facility for operating launch process. This paper studied development process and operating method for liquid oxygen filling system of cryogenic propellant systems in launch pad propellant feeding facility.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1171-1175
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• 2017

Cryogenic helium gas is used as the pressurant for the oxidizer pressurization of DR(Damper Receiver) sphere in the PSD(Pogo Suppression Device) system and liquid oxygen is used as the oxidizer for the propellant in Korea Space Launch Vehicle-II. The helium gas is stored in pressurant cylinders inside the cryogenic liquid oxygen tank and liquid oxygen is stored in the oxidizer tank. In this study, the performance test of PSD liquid oxygen drain valve for KSLV-II was considered.

• Journal of the Korean Vacuum Society
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• v.1 no.3
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• pp.332-335
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• 1992

초고진공 시스템에 있어서 시스템을 대기압으로 바람을 넣은 후 정상상태로의 신 속한 원상회복을 위하여 건조질소 통풍(venting) 장치를 고안 제작하였다. 이 장치는 액체 질소 저장통, 증발기 및 여과기로 구성되어 있다. 이 장치에 의한 통풍효과와 다른 방법에 의한 통풍효과를 가스 방출률 측정을 통하여 정성적으로 비교 분석하였을 때, 본 장치가 가 장 낮은 가스 방출률과 가장 빠른 진공회복을 보여주었다.