• Proceedings of the KAIS Fall Conference
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• 2012.05b
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• pp.671-673
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• 2012

본 연구에서는 상용 엔진 해석프로그램인 GT-Power를 이용하여 디젤엔진의 성능을 개선 개발을 위한 일차원 성능해석 모델을 개발하였다. 개발된 일차원 엔진 성능모델을 통하여 엔진의 출력, 토크 및 연비등을 검토하였다. 향후 터보챠져를 장착한 엔진개발에 사용이 가능하도록 터보매칭을 할 수 있는 모델을 추가하였으며, 향후 디젤엔진의 실험결과와 비교를 통하여 엔진 모델을 지속적으로 보완할 예정이다.

• Fire Science and Engineering
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• v.24 no.4
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• pp.33-40
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• 2010

A numerical model considering the vapor pressure and the creep models, in the form of a analytical program, for tracing the behavior of high strength concrete (HSC) members exposed to fire is presented. The two stages, i.e., spalling procedure and fire resistance time, associated with the thermal, moisture flow, creep and structural analysis, for the prediction of fire resistance behavior are explained. The use of the analytical program for tracing the response of HSC member from the initial pre-loading stage to collapse, due to fire, is demonstrated. The validity of the numerical model used in this program is established by comparing the predictions from this program with results from others fire resistance tests. The analytical program can be used to predict the fire resistance of HSC members for any value of the significant parameters, such as load, sectional dimensions, member length, and concrete strength.

• Proceedings of the Korea Water Resources Association Conference
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• 2019.05a
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• pp.88-88
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• 2019

컴퓨터 성능향상과 수치해석기법의 발달로 인해 Navier-Stokes 방정식에 기초한 수치모델을 활용한 3차원 유동/파동장 해석이 증가하고 있는 추세이다. 그러나 아직까지 Navier-Stokes 방정식 모델의 계산부하를 PC에서 소화하기에는 무리가 따른다. 게다가 실험실 스케일을 벗어나, 실제 현장을 계산영역으로 설정할 경우에는 계산량이 엄청나게 증가하게 된다. 이것을 극복하기 위해서는 반듯이 병렬계산을 수행하여야 한다. 본 연구에서는 계산부하가 큰 Navier-Stokes 방정식 기반의 3차원 수치모델 LES-WASS-3D를 활용한 대용량 병렬계산체계를 구축한다. 나아가 3차원 정밀 또는 광역의 유동/파동장 해석에 있어서 병렬계산체계의 성능과 적용성을 검토한다. 현재 보급되고 있는 PC들은 모두 멀티프로세서가 장착됨으로 손쉽게 병렬계산을 수행할 수 있다. 그러나 정밀 또는 광역해석을 위해서는 대용량 병렬계산 컴퓨터가 요구된다. 따라서 본 연구에서는 보조프로세서를 장착한 공유메모리 환경의 고성능 병렬계산체계를 구축한다. 나아가 포트란 기반의 순차코드로 구축된 기존 3차원 Navier-Stokes 방정식 모델 LES-WASS- 3D를 병렬코드로 변환한다. 병렬계산 성능 및 적용성을 검토하기 위한 수치해석을 수행한다. 이상의 과정을 통해 본 연구에서 구축한 병렬계산체계의 성능 및 적용성을 확인할 수 있었다. 그리고 3차원 유동/파동장 해석에 있어서 정확도 향상뿐 아니라, 계산영역을 확장할 수 있는 계기가 마련되었다. 또한 유동/파동 해석보다 많은 계산시간이 필요한 지형변동 해석에도 충분히 적용될 수 있다고 판단된다.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.76-82
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• 2003

To guarantee the proper functions of a satellite in the extreme space environment, the several test models are developed generally. There are advantages that the design and the analysis of Flight Model(FM) can be validated through these test models, and the functional reliabilities can be increased by reflecting the modifications on the final design of FM. The integration and test of Structure & Thermal Model(STM) of KOMPSAT, being currently developed, have been completed. In this paper, the processes of design and analysis of the STM propulsion system, one of the KOMPSAT modules, are described.

• Aerospace Engineering and Technology
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• v.4 no.1
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• pp.86-94
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• 2005

This paper shows the results of design, analysis, manufacturing and test performed to develop the CTU(Command Telemetry Unit) EQM(Engineering Qualification Model). According to the key requirement specifications, the logics and circuits of each board are designed. In order to validate designs, some worst case, part stress, reliability, FMECA, radiation environment and launch environment analyses are performed. After manufacturing and assembling all boards, all functions of CTU EQM are verified through the functional test, environmental test and ETB test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.219-224
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• 2012

In this work, a steady-state performance modeling and off-design performance analysis of the 2-spool separate jet turbofan engine named BR715-56 which is a power plant for the narrow body commercial aircraft is carried out for engine performance behaviors investigation and condition monitoring using a commercial code MATLAB/SIMULINK. Firstly, the engine component maps of fan, high pressure compressor, high pressure turbine and low pressure turbine are generated from similar component maps using the scaling method, and then the off-design performance simulation model is constructed by the mass flow matching and the work matching between components. The model is developed using SIMULINK, which has advantages of easy steady-stare and dynamic modelling and user friendly interface function. It is found that the off-design performance analysis results using the proposed model are well agreed with the performance analysis results by GASTURB at various operating conditions.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.2
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• pp.150-157
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• 2014

Li-Ion battery is used in the most satellites now due to advantages such as weight, thermal dissipation and self discharge compared to the previous generations of electrochemical batteries. The performance analysis model of the Li-Ion battery is needed to aid the design of new satellite electrical power subsystem. This paper develops the performance analysis model of the Li-Ion battery to apply to the electrical power subsystem design and energy balance analysis on geostationary orbit. The analysis model receives the satellite bus power, solar array power and battery temperature and gives the battery voltage, charge and discharge currents, taper index, state of charge and power dissipation. The results from the performance analysis are compared and analyzed with the flight data to verify the model. The compared results show satisfactory without significant difference with the flight data.

• Journal of KIISE:Computer Systems and Theory
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• v.26 no.7
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• pp.847-862
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• 1999

본 논문에서는 유한버퍼의(finite-buffered) 동기화된(synchronous) 큐잉모델(queueing model)을 이용하여 명령어들간의 병렬성, 분기명령의 빈도수, 분기예측(branch prediction)의 정확도, 캐쉬미스 등의 파라미터들을 고려하여 프로세서의 명령어 실행율을 예측하며 캐쉬의 성능과 파이프라인 성능간의 관계를 분석할 수 있는 새로운 해석적 모델을 제안하였다. 해석적 모델은 모델의 타당성을 검증하기 위해서 시뮬레이션을 수행하여 얻은 결과와 비교하였다. 해석적 모델과 시뮬레이션을 비교한 결과 대부분 10% 오차 내에서 일치하였다. 본 연구를 통하여 얻은 해석적 모델을 사용하면 시뮬레이션에서는 드러나지 않는 성능제약의 원인에 대한 명확한 규명이 가능하기 때문에 성능향상을 위한 설계자료를 얻을 수 있으며, 시스템 성능 밸런스를 위한 캐쉬와 비순차이슈 파이프라인 성능간의 관계에 대한 정확한 분석이 가능하다.Abstract This research presents a novel analytic model to predict the instruction execution rate of superscalar processors using the queuing model with finite-buffer size and synchronous operation mode. The proposed model is also able to analyze the performance relationship between cache and pipeline. The proposed model takes into account various kinds of architectural parameters such as instruction-level parallelism, branch probability, the accuracy of branch prediction, cache miss, and etc.. To prove the correctness of the model, we performed extensive simulations and compared the results with the analytic model. Simulation results showed that the proposed model can estimate the average execution rate accurately within 10% error compared to simulation results. The proposed model can explain the causes of performance bottleneck which cannot be uncovered by the simulation method only. The model is also able to show the effect of the cache miss on the performance of out-of-order issue superscalar processors, which can provide an valuable information in designing a balanced system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.401-405
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• 2010

An efficient performance model for scramjet engines has been proposed for scramjet performance design. In supersonic air intake design, the compression angles of the wedge were determined to maximize the total pressure recovery of the intake based on Oswatisch criterion. Both combustion models of chemical equilibrium and finite-rate chemistry model are implemented, and compared each model with the results by Starkey for Waverider engine configuration. Finally, the performance model of concern has been confirmed by conducting performance analysis with hypothetical mission profile and design conditions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.326-330
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• 2011

Development and validation of performance analysis model for dual combustion ramjet engines has been performed. A typical performance model for hypersonic intake flow and supersonic mixing and combustion was demonstrated; Taylor-Maccoll equation for coaxial intakes and a quasi-one dimensional reacting flow analysis with CEA chemical equilibrium for supersonic combustion. The results, thermodynamic data of intake and supersonic combustor were validated with CFD numerical results.