• 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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• 2013.02a
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• pp.247-247
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• 2013

첨단 산업의 급속한 팽창에 기인한 대용량, 고진공 성능의 진공시스템 수요가 증대되고 있다. 이로써 고진공 펌프 국산화의 일환으로 터보분자 펌프 개발이 진행중에 있으며 터보분자 펌프의 특성평가시스템을 자체적으로 설계/제작하였다. 특성평가의 하나로 극한조건 조성, 실제 공정 모사 조건의 기계적 안정성, 공정 대응 내구성의 신뢰성을 단기간에 확보하기 위한것으로 파괴장치가 설계/제작 되었다. 본 연구에서는 400 L/s의 터보분자 펌프를 이용하였고, 다양한 공정 모사 조건하에서 torque, pressure, power, vibration, temperature 등의 특성 변화를 관찰하여 파괴장치의 검증과 신뢰성 확인 및 database를 확보하고자 한다.

• Proceeding of EDISON Challenge
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• 2016.11a
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• pp.63-67
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• 2016

본 연구에서는 극초음속 추진기관을 위한 고공환경 모사 설비 장치에서 시험부 안에 들어가는 시험 모델의 변수에 대해 고찰하였다. 시험부에 적용할 시험 모델을 대상으로 진행하고, 시험 모델 형상 변화에 따른 유동 특성을 파악하였다. 시험 모델에 대한 주요 변수는 폐색율, 각도, 받음각으로 설정하였으며, 해석은 EDISON_CFD에서 제공하는 정렬격자 기반 2차원 압축성 유동 범용 해석 SW로 진행하였다. 해석 결과를 통해 다양한 형상 변수에 따라 변화 되는 충격파 뒤의 압력층 두께를 확인 하였고, 압력층 두께가 두꺼워 질수록 시험 조건을 모사 할 수 없음을 확인하였다. 본 연구를 통해 형상 변수에 따른 극초음속 추진기관을 위한 고공모사설비에서 시험부에 적용될 시험 모델의 범위를 확인하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.431-432
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• 2008

In order to develop and inspect the electronic controller of propulsion system, It must emulate the electronic signal similar to actual signal. The applied signals on propulsion system are engine speed, turbine speed, various kinds of temperatue signal, pressure signal, LVDT/RVDT position signal and so forth. Contents are the development of emulator that simulate the electronic signals similar to actual signals.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.475-478
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• 2012

In this study, preliminary design of a high-altitude test facility (HATF) was performed to simulate the high-altitude environment using a rocket engine that liquid oxygen and kerosene were used as the propellant. Experimental facility consists of vacuum chamber, supersonic exhaust diffuser, heat exchanger, ejector and gas generator. The vacuum chamber was simulated and maintained high-altitude environmental pressure by supersonic exhaust diffuser. Combustion gas of the rocket engine was cooled by water at heat exchanger after that the mixed gas was emitted to the air by ejector. The ejector which was operated by the steam generator using 75% ethanol and liquid oxygen as propellants and water for steam maintains a vacuum condition.

• Journal of the Korean Society of Marine Environment & Safety
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• v.19 no.6
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• pp.666-673
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• 2013

This paper proposes the performance evaluation test of attitude heading reference system (AHRS) suitable for small high speed autonomous underwater vehicle(AUV). Although IMU can provides the detail attitude information, it is sometime not suitable for small AUV with short operation time in view of price and the electrical power consumption. One of alternative for tactical grade IMU is the AHRS based micro-machined electro mechanical system(MEMS) which can overcome many problems that have inhibited the adoption of inertial system for small AUV such as cost and power consumption. A cost effective and small size AHRS which incorporates measurements from 3-axis MEMS gyroscopes, accelerometers, and 3-axis magnetometers has been developed to provide a complete attitude solution for AUV and the attitude calculation algorithm is derived based the coordinate transform equation and Kalman filter. The developed AHRS was validated through various performance tests as like the magnetometer calibration, operating experiments using land mobile vehicle and flight motion simulator (FMS). The test of magnetometer calibration shows the developed MEMS AHRS is robust to the external magent field change and the test with land vehicle proves the leveling error of developed MEMS AHRS is below $0.5^{\circ}/hr$. The results of FMS test shows the fact that AHRS provides the measurement with $0.5^{\circ}/hr$ error during 5 minutes operation time. These results of performance evaluation tests showed that the developed AHRS provides attitude information which error of roll and pitch are below $1^{\circ}$ and the error of yaw is below $5^{\circ}$ and satisfies the required specification. It is expected that developed AHRS can provide the precise attitude measurement under sea trial with real AUV.

• 한국생태학회:학술대회논문집
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• 1998.05a
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• pp.46-46
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• 1998

• Progress in Medical Physics
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• v.15 no.2
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• pp.77-83
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• 2004

The commissioning of a model-based treatment planning system requires many parameters to fit the measured depth doses and transverse profiles. For the commissioning of the Pinnacle$^3$ system, through the Monte Carlo (MC) simulation, the necessary parameters, including the photon spectrum, contaminant electrons, off-axis softening and fluency of photons, were observed. Through the simulation the parameters contained valuable information, but the calculated results of the Pinnacle$^3$ using the MC-derived parameters showed discrepancies with those measured for the off-axis softening and the fluency of photons. Even though the MC calculation produces reasonable values for the commissioning, the thorough physical basis of the Pinnacle$^3$'s commissioning process is needed in order to directly use the MC derived parameters.

• 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.

• 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.