• Journal of the Korea institute for structural maintenance and inspection
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• v.26 no.5
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• pp.43-48
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• 2022

In order to evaluate the seismic performance of the modular expansion joint known for its large expansion allowance and remarkable durability, this study conducts seismic response analysis and seismic simulation test. The bridge selected for the seismic response analysis is a cable stayed bridge with main span length of 1,000m. Three artificial earthquake were generated with respect to the design response spectra of the Korean Standards (KS), AASHTO LRFD and Eurocode, and applied to the selected bridge. The seismic simulation tests reproduced the artificial earthquakes using dynamic hydraulic actuators in the longitudinal and transverse directions. The test results verified the durability and safety of the expansion joint in view of its seismic behavior since abnormal behavior or failure of the expansion joint was not observed when the artificial earthquake waves were applied in the longitudinal direction, transverse direction and both directions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1997.11a
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• pp.23-23
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• 1997

다목적으로 활용할 수 있는 분리축 방식의 터보축 엔진 개발을 위한 정상상태 해석 프로그램의 개발과 함께 동일 형식의 가스터빈엔진 시험장치를 이용한 실험을 통해 프로그램의 해석결과와 비교, 그 타당성을 입증하였다. 실험에 이용된 시험장치는 1단 원심형 압축기, Can형 연소기, 1단 Radial형 압축기 터빈 및 동력터빈으로 구성되어 있으며 출력은 3상 교류발전기를 통해 획득된다. 해석에 사용된 주요 구성품의 성능곡선은 시험장치 제작자로부터 획득된 자료를 이용하였으며, 경우에 따라 시험장치를 이용한 실험을 통하여 보정하였다. 시험장치를 이용한 실험결과를 프로그램 해석결과와 비교한 결과, 시험장치의 운용제한에 의해 실제 자동영역이 제한되기는 했으나, 압력비, 출력 등 주요 변수들에서 10% 미만의 오차를 보였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.153-156
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• 2008

Ignition and combustion performance of a gas-turbine engine were changed by various high-altitude condition. A goal of this study is to make the small test facility to simulate high-altitude condition. To perform the low pressure condition, a diffuser was used in various diffuser front of primary nozzle pressure. To perform the low temperature, heat exchanger was used in various mixture ratio of cryogenic air and ambient temperature air. The experimental result shows that high-altitude conditions can be controled by diffuser front of primary nozzle pressure and mixture ratio of cryogenic air and ambient temperature air.

• Proceedings of the Korean Vacuum Society Conference
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• 2000.02a
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• pp.179-179
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• 2000

음극의 크기에 따라 발생된 전자빔 전류가 도파관 영역에서 공간 전하 한계 전류를 초과할 경우 형성되는 가상 음극 (Virtual Cathode)을 이용한 축 방향으로의 고출력 마이크로파 발생 및 진단에 관한 연구를 수행하였다. 먼저 실험에 앞서 전산모사를 통해 결과를 예측하고 실험을 통해 확인하는 순으로 하였다. 전산 모사는 2-1/2차원 Partical-In-Cell(PIC) 코드인 "MAGIC"을 사용하여 축 방향으로 진행하는 새로운 개념의 가상 음극발진기를 모사하고, 정확한 경과를 얻기 위해 강렬한 상대론적 전자빔 발생 장치인 "천둥"( 최대 전압 600kV, 최대 전류 70KA, 60ns)을 사용하여 전산 모사에 넣어줄 전류값을 얻었다. 음극의 반지름이 2.5cm 일 때 전파되는 최대 출력이 약 800MW인 마이크로파가 발생되었고, 이때 출력변환 효율이 약 30%임을 전산모사를 통하여 알 수 있었다. 또한 전파하는 전기장의 축방향 성분(Ez)의 반지름 방향에 대한 분포 특성을 통하여 주된 전파 모드가 TM01와 그 상위모드의 조합으로 이루어졌음을 알았고 이때 기대되는 동작 진동수는 5~7 GHz임을 전산 모사 결과로부터 알 수 있었다. 실험을 통해서도 음극의 크기가 2.5cm 때, 최대 출력이 약 520MW인 마이크로파를 발생하였고, 이 때 출력 변환 효율은 약 8%이고, 방전 사진을 통해서 주된 동작 모드가 TM01와 그 상위모드의 조합으로 이루어졌음을 알았고, 이때 주된 출력 진동수는 5~6 GHz임을 알 수 있었다.는 5~6 GHz임을 알 수 있었다.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.20 no.10
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• pp.100-106
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• 2019

Ground and high altitude simulated combustion experiments were conducted using a liquid rocket engine with hydrogen peroxide and kerosene as the propellant. A ground and high altitude simulated combustion test facility was constructed by installing a high altitude model diffuser and TMS (Thrust Measuring System) on a vertical combustion test bench. The thrust characteristics according to altitude were investigated using the combustion test equipment. The diffuser was designed on a 1:4.8 scale to verify the characteristics of the high diffusing diffuser and starting pressure. The cold flow tests were conducted using nitrogen gas, and the performance characteristics and starting characteristics of the scale down diffuser were verified. A diffuser and TMS were installed on the vertical combustion test bench, and the thrust correction equations for the system resistance were derived. The thrust correction equations were derived from the step test and vacuum step test before the actual hot firing test. Nozzles with an operating altitude of 10km were designed. Hot firing tests were conducted to analyze the thrust characteristics according to the operating altitude changes. The actual thrust was calculated using each correction equation with the thrust value measured by the TMS.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.553-556
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• 2009

In this study, ignition tests of a gas turbine combustor were performed to evaluate an ignition loop at low temperature condition. An experimental setup was constructed to simulate low temperature condition with a heat exchanger using dry ice as a coolant. Various low temperature conditions could be created by controlling the amount of air though the heat exchanger. The results showed that ignition limit decreased with air temperature.

• Proceedings of the Korean Nuclear Society Conference
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• 1997.05a
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• pp.617-622
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• 1997

격납건물내 소격실에서의 수소혼합 정도를 파악하고 격실내 균일한 혼합을 좌우하는 인자의 영향을 분석하기 위하여 소규모 혼합실험을 수행했다. 본 연구에서는 해석적으로 수립된 3차원 혼합 모델의 검증을 위하여 3차원 모사가 가능하도록 실험 장치를 구성하였다. 격납용기 내에서 수소 생성의 주원인이 되는 노심으로부터의 수소거동을 분석하기 위한 기초 실험(실험 A)과 안전주입 탱크 격실에서의 수소거동을 분석하기 위해 원형 혼합 chamber를 구상했다. 기초실험 A에서는 혼합 chamber내 축 방향으로 대칭적인 오리피스형 장애물을 설치하고 실험했고 안전주입 탱크 격실을 모사한 실험 B는 영광 3&4호기를 바탕으로 축소시켜 안전주입탱크 격실내 존재하는 두충과 안전 주입 탱크 사이의 틀을 통한 혼합체의 거동을 분석했다. 실험결과 오리피스형 장애물을 설치한 기초실험에서는 원형 띠모양의 장애물이 혼합체의 거동에 큰 영향을 주지 않는 것이 관측됐지만 안전주입탱크격실 실험에서는 격실내 장애물로 존재하는 두충이 혼합체의 거동에 큰 영향을 주는 것이 관측됐다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.827-829
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• 2011

Vacuum facility is required for high altitude space environment test to develop satellites or space launch vehicles. We, at Chungnam, National University, developed turbo molecular pump vacuum test facility up to $1.0{\times}10-6$ torr to simulate 200 km altitude environment. In this paper, we present some preliminary vacuum performance test results.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.2
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• pp.1-8
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• 2015

Dual pulse rocket motor is a variant of solid rocket motor with two propellant grain separated by a pulse separation device. The major performance of such a rocket motor is influenced by the change in the hole area of pulse separation device to nozzle throat area ratio. In this study, we performed flow analysis to investigate the internal flow characteristics according to the pulse separation device hole area to nozzle throat area ratio change. Gases used flow analysis were used combustion gas of HTPB/AP composite propellant and nitrogen gas. Flow analysis results of the dual pulse rocket motor were validated by comparison with experimental results of pneumatics. Commercial CFD code ANSYS FLUENT 14.5 is used in this study to simulate flow analysis.

• Proceedings of the Korean Radioactive Waste Society Conference
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• 2005.11a
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• pp.134-142
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• 2005

The experimental setups for flow visualization and processes identification in laboratory scale (so cal led Flow Lab.) has developed to get ideas and answer fundamental questions of flow and migration in geologic media. The setup was made of a granite block of $50{\times}50cm$ scale and a transparent acrylate plate. The tracers used in this experiments were tritiated water, anions, and sorbing cations as well as an organic dye, eosine, to visualize migration paths. The migration plumes were taken with a digital camera as a function of time and stored as digital images. A migration model was also developed to describe and identify the transport processes. Computer simulation was carried out not only for the hydraulic behavior such as distributions of pressure and flow vectors in the fracture but also for the migration plume and the elution curves.