• Journal of the Korea Society for Simulation
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• v.15 no.3
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• pp.49-60
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• 2006

We propose a method to use a state transition model so that the sensing object can be distinguished through classification of signal patterns sensed by a sensor array. Focusing on the design of the model that is able to distinguish the sensed object more exactly, we present an idea in which the modeling elements, 'states' and 'transitions' are defined as each same-sized angle intervals into which the angle interval $(-\frac{\pi}{2},\frac{\pi}{2})$ is divided and the angle differences between adjacent signal values on sampling signal value sequence value sequence sensed from the sensor array in the uniform time interval, respectively. In addition we show the usefulness of our model through experiments.

• Proceedings of the Materials Research Society of Korea Conference
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• 2003.11a
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• pp.215-215
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• 2003

현재 이용되고 있는 위상 변위 마스크, 즉 Cr 계열의 마스크나 MoSiON 마스크는 DUV지역에서 낮은 굴절률을 갖는다. 그 겯과 마스크의 두께가 90 nm 이상이 되고, 웨이퍼에서 패턴 형성 시 에러율이 증가하게 된다. 본 연구에서는 DUV 지역에서 굴절률이 높을 것이라고 예상되는 Zr과 Hf의 oxide를 위상 변위 마스크 물질의 선정하고 각 물질의 전자 상태와 천이 상태를 분석하여 위상변위 마스크로써의 이용가능성을 연구하자 한다. 상온에서 Zr, Hf oxide의 안정한 구조는 cubic 구조와 monoclinic 구조이다. 현재 cubic 구조의 Zr, Hf oxide에 대한 전자 상태는 연구가 많이 되어 있는 반면 monoclinic 구조에서의 전자상태 연구는 미흡하다. 본 연구에서는 monoclinic 구조를 이용하여 Zr, Hf oxide의 클러스터 모델을 제작하였다. 제작된 클러스터 모델에 대하여 DV-X$\alpha$ 계산법을 적용, 기저상태의 전자상태를 계산하였다. 그리고 각 모델에서 Zr L-edge, Hf L-edge 그리고 O K-edge의 천이상태를 연구하여, 기저 상태의 전자상태와 천이상태를 연구하여 광학 성질과의 연관성을 연구하고자 하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.5
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• pp.100-109
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• 2003

A performacne simulation model of the PT6A-62 turboprop engine using the $SIMULINK^R$ was proposed to predict transient and steady state behaviors. The $SIMULINK^R$ has several advantages such as user-friendliness due to the GUI(Graphic User Interfaces) and ease in the modification of the computer program. The $SIMULINK^R$ model consists of subsystems to represent engine gas path components such as flight initial subsystem, compressor subsystem, burner subsystem, compressor turbine subsystem, power turbine, exhaust nozzle subsystem and integrator subsystem. In addition to subsystems, there are search subsystems to find an appropriate operating point by scaling from the 2-D components look-up table, Gasprop Subsystem to calculate the gas property precisely. In case of steady state validation, performance results analyzed by the proposed $SIMULINK^R$ model were agreed well with the analysis results by the commercial GASTURB program. Moreover in validation of the transient model, it was found that performance simulation results by the proposed model were reasonable agreement with analysis results by the well-proved computer program using FORTRAN.

• Journal of the Korean Institute of Intelligent Systems
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• v.18 no.3
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• pp.367-372
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• 2008

In this paper we proposed a model of a fault diagnosis expert system with high reliability to compare identical well-functioning motors. The purpose of the survey was to determine if any differences exit among these identical motors and to identify exactly what these differences were, if in fact they were found. Using measured data for many identical brushless dc motors, this study attempted to find out whether normal and fault can be classified by each other. Measured data was analyzed using the State Transition Model (STM). Based on a proposed STM method, the effect of a different normal state is minimized and the detection of fault is improved in identical motor system. Experimental results are presented to prove that STM method could be a useful tool for diagnosing the condition of identical BLDE motors.

• Journal of Korea Society of Industrial Information Systems
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• v.7 no.4
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• pp.22-28
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• 2002

It has been reported that neural network with cyclic connections generates limit cycles. The dynamics of discrete time network with cyclic connections has been analyzed. But the dynamics of cyclic network in continuous time has not been known well due to its huge calculation complexity. In this paper, we study the dynamics of the continuous time network with cyclic connections and the effect of chaotic signal in the network for transitions between limit cycles.

• Journal of the Korean Institute of Gas
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• v.6 no.1 s.17
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• pp.81-85
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• 2002

This paper presents the calculation methods of liquid release rate in the transition region when hazardous materials leak from the pipeline due to an unwanted accident. For the laminar and turbulent flow region, liquid release rate from a pipeline can be calculated by using a commercial software or by using calculator based on the models(equations) suggested by Crowl and Louvar et al. However, there has been no corresponding model for the transition flow region. In this paper. we showed that the turbulent model may be used as an equation generally used in the transition region for conservative hazard analysis if safety factor $30\%$ is added to the value calculated by the turbulent model. In this regard, we first calculated the release rate from liquid pipeline in the transition region by using experimental data on Fanning friction factor depending on Reynolds number which Lap-Mou Tam et al. had introduced, then compared it with that of the laminar and turbulent models in transition region.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.5
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• pp.323-334
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• 2020

Since boundary layer transition has a significant impact on the aero-thermodynamic performance of hypersonic flight vehicles, capability of accurate prediction of transition location is essential for design and performance analysis. In this study, γ-Re_θt model is improved to predict transition of hypersonic boundary layers and validated. A coefficient in the production term of the intermittency transport equation that affects the transition onset location is constructed and applied as a function of Mach number, wall temperature, and freestream stagnation temperature based on the similarity numerical solution of compressible boundary layer. To take into account a Mach number dependency of transition onset momentum thickness Reynolds number and transition length, additional correlation equations are determined as function of Mach number and applied to Re_θc and F_length correlations of the baseline model. The suggested model is implemented to a commercial CFD code in consideration of practical use. Analysis of hypersonic flat plate and circular cone boundary layers is carried out by using the model for validation purpose. An improvement of prediction capability with respect to variation of Mach number and unit Reynolds number is identified from the comparison with experimental data.

• Proceedings of the IEEK Conference
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• 1998.06a
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• pp.26-29
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• 1998

비정치제도 위성통신링크에서는 지표상의 단말기, 지구국 등에 대한 상대적인 위성의 빠른 이동으로 인하여 도플러천이가 발생하며, 이는 이동위성통신 시스템 수신단의 성능을 약화시킨다. 본 논문은 비정지궤도 위성을 이용하는 통신링크 상에서 발생하는 도플러천이의 특성을 분석한다. 분석된 결과는 도플러천이에 대한 시뮬레이션 모델과 보상 알고리즘의 개발에 활용활 수 있을 것이다.

• Transactions of the Korean Society of Mechanical Engineers
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• v.13 no.6
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• pp.1257-1268
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• 1989

본 연구에서는 이에 천이와 난류모델을 첨가하여 층류 경계층이 천이를 거쳐 난류 경계층으로 발달해가는 전과정을 해석하려고 한다. 또, 이러한 부분 면파의 특성을 needle contact법에 의하여 측정 포물형이나 완전 Navier-Stokes 방정식을 사용함에 있어서 표면곡률항의 중요성을 보이며, 익형의 선단등 표면곡률이 중요한 영역에서도 적용가능한 수치적 방법을 제시한다.

• Journal of computational fluids engineering
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• v.19 no.2
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• pp.8-16
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• 2014

Two-dimensional prediction capability of several analysis codes, such as XFOIL, MSES, and KFLOW, is compared and analyzed based on computational results of airfoil flows. To this end the transition transport equations are coupled with the Navier-Stokes equations for the prediction of the natural transition and the separation-induced transition. Experimental data of aerodynamic coefficients are used for comparison with numerical results for the transitional flows. Numerical predictions using the transition transport model show a good agreement with experimental data. Discrepancies have been found in the prediction of the pressure drag are mainly caused by the difference in the far-field circulation correction methods.