• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.281-285
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• 2007

The flow characteristics in the thruster should be analyzed considering its geometry and the pressure ratio to estimate its performance and etc. This paper suggests the computational result of an axisymmetric real nozzle for the altitude control of a satellite to find out the application limit that the assumption of continuum mechanics holds. The steady non-reacted compressible flow field in the unstructured grid system is computed and analyzed with varying the environmental pressure (or the degree of vacuum) under the fixed pressure ratio in a real thruster of which the area ratio of exit to throat is 56. The assumption of the continuum mechanics is not approved when the environmental pressure is reduced less than $10^{-3}$ atm.

• Journal of the Korea Computer Graphics Society
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• v.16 no.4
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• pp.35-40
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• 2010

Due to the distribution of digital camera, many work for photo management has been studied. However, most work use a sequential grid layout which arranges photos considering one criterion of digital photo. This interface makes users have lots of scrolling and concentrate ability when they manage their photos. In this paper, we propose a clustering method based on a temporal sequence considering their color similarity in detail. First we cluster photos using Cooper's event clustering method. Second, we makes more detailed clusters from each clustered photo set, which are clustered temporal clustering before, using maximal clique finding algorithm of interval graph. Finally, we arrange each detailed dusters on a user screen with their overlap keeping their temporal sequence. In order to evaluate our proposed system, we conducted on user studies based on a simple questionnaire.

• Journal of the Korea Society for Simulation
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• v.20 no.4
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• pp.149-155
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• 2011

This paper presents simulations of advance evacuation analysis using a cellular automata model for passenger behavior in an emergency of passenger ship. The proposed cellular automata model divides the space in a uniform grid called "cell." Each passenger is located in a cell and moves to another cell according to a set of local rules assumed to be associated with the individual and crowd behaviors of the passengers. To verify the usefulness of the proposed cellular automata model, 11 tests, all of which are specified in International Maritime Organization Maritime Safety Committee/ Circulation 1238 (IMO MSC/Circ. 1238), were implemented, and it was confirmed that all the requirements of these tests had been met.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.3
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• pp.1-9
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• 2005

The interaction between hypersonic free stream and side jet flow at high altitudes is investigated by using the direct simulation Monte Carlo (DSMC) method. In order to alleviate the difficulty associated with the large density difference between the free stream and the side jet flow and to simulate the two flows simultaneously, a weighting factor technique is applied. For validation, the corner flow over a pair of plates perpendicularly attached is calculated with and without a side jet, and the results are compared with experiment. For a more realistic configuration, the flow past a blunted cone cylinder shape is solved. The leeward or windward jet is injected into the free stream and the effect on the aerodynamic force and moment is observed at various flow angles. The lambda shock effect and the wake structure are studied in terms of the surface pressure differential. A higher interaction between the free stream and the side jet flow is observed when the side jet is injected in the windward direction.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.4
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• pp.287-294
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• 2007

A static aeroelastic analysis for supersonic aircraft wing equipped with external store under the wing lower surface is performed using computational fluid dynamics (CFD) and computational structural technology(CST) coupling methodology. Two mapping algorithms, which are the pressure mapping algorithm and the displacement mapping algorithm, are used for CFD/CST coupling. A three-dimensional unstructured Euler code and finite element analysis program are used to calculate the flow properties and the structural displacements, respectively. The coupling procedure is repeated in an iterative manner until a specified convergence criterion is satisfied. Static aeroelastic analysis for a typical supersonic flight wing is performed and final converged wing configuration is obtained after several iterations.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2007.06a
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• pp.387-387
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• 2007

기능성 나노소자를 구현할 수 있는 나노 소재로 0차원 구조의 양자점(quantum dot)과 1차원 구조의 양자선 및 나노선(nanorod)이 제안되고 있다. 나노선의 경우 나노스케일의 dimension, 앙자 제한 효과, 탁월한 결정성, self-assembly, internal stress등 기존의 벌크형 소재에서 발견할 수 없는 새로운 기능성이 나타나고 있어서 바이오, 에너지, 구조, 전자, 센서 등의 분야에서 활용되고 있다. 현재 국내외적으로 널리 연구되고 있는 나노선으로는 Si 및 Ge, $SnO_2$, SiC, ZnO 등이 있으며 특히, ZnO는 우수한 물리적 전기적 특성과 함께 나노선으로의 합성이 비교적 쉬워 주목받고 있는 재료이다. ZnO의 합성방법으로는 thermal CVD, MOCVD, PLD, wet-chemistry 등 다양한 방법이 사용되고 있다. 특히 MOCVD 법은 수직 정렬된 ZnO 나노막대를 합성하기가 매우 용이하다. 본 실험에서는 자체개발된 MOCVD 장비를 이용한 일차원 ZnO 나노선을 성장하였다. 이러한 ZnO 나노선의 성장은 사파이어 기판과 실리콘 기판 위에서 이루어졌으며 기판의 종류와 격자상수 불일도에 따른 상이한 성장과정을 온도에 따른 나노선 성장에서 관찰할 수 있었다. 사파이어 기판의 경우, 240도의 온도에서는 박막형상을 지닌 ZnO가 온도가 320도 이상으로 상승하면서 나노선으로 변함을 보였고, 실리콘 기판의 경우 380도 이상에서 기울기률 가진 나노선을 관찰하였으며, 420도에서는 나노선을 관찰 할 수 없었다. 또한 PL 장비를 이용한 PL 강도와 성장과정을 연관하여 생각하였을 때, 나노선의 기물기가 PL 강도비과 연관성을 가진다는 것을 측정을 통해 확인하였다.

• Proceedings of the Korean Vacuum Society Conference
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• 2000.02a
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• pp.168-168
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• 2000

Yamada 등의 덩어리 증착에 관한 연구 이후 낮은 기판 온도에서 결정성이 뛰어난 금속박막성장(thin film growth)을 얻을 수 있는 방법으로 최근 덩어리 증착(cluster depositon) 방법에 관하여 많은 연구들이 진행되어 덩어리 충돌이 원자 충돌인 경우와 큰 차이를 보이는 결과를 얻었으며, 덩어리 증착시 기판 내부에 점결함(point defect)이 발생되지 않는다는 중요한 결과를 얻었다. 금속 덩어리를 사용한 금속박막성장은 높은 박막성장속도와 뛰어난 구조 재배열 효과를 얻을 수 있으며 기판의 격자 손상을 감소시키기 때문에 향후 나노미터 소자 개발에 응용성이 클 것으로 예상된다. 그러나 금속 덩어리와 금속 표면사이의 상호작용에서 발생되는 기본적인 역학(mechanism)은 분명하게 알려져 있지 않다. 지금까지 알루미늄 덩어리의 원자구조와 특성에 관한 연구는 수행되어졌지만 (4,5), 알루미늄 덩어리 증착에 관한 연구는 수행되지 않았다. 본 연구에서는 13~177개로 이루어진 큰 알루미늄 덩어리들의 증착에 관하여 Md(molecular dynamics) 방법을 사용하여 연구하였다. MD 시뮬레이션을 사용하여 덩어리 증착시 기판 표면과의 충돌 초기에 나타나는 덩어리 내부 원자들의 상관충돌효과(correlated collisions effect)에 의하여 덩어리 크기에 따른 증착현상과 여러 물리적 현상들을 관찰하였다. 덩어리 총 에너지가 증가할수록 기판의 최고 온도는 증가하며, 덩어리 크기가 클수록 상관충돌효과가 커지기 때문에 덩어리의 총 에너지에 다른 최고 증가 비율은 적어졌다. 시간에 따른 비정렬 원자수(disordered atom number) 비교를 통하여 덩어리가 클수록 구조 재배열이 더 잘 이루어진다는 것을 알 수 있었고, 원자당 에너지가 클수록 덩어리 원자들이 기판 내부로 더 깊이 들어갔고, 덩어리 크기가 클수록 상관충돌효과로 인하여 덩어리 원자들이 기판 내부로 더 깊이 들어가는 것을 알 수 있었고, 덩어리 크기가 클수록 상관충돌효과는 커지고 더욱 부드러운 증착이 이루어졌으며, 무엇보다도 덩어리 증착시 표면에서 구조 재배열이 잘 이루어지는 특징을 살펴볼 수 있었다. 이러한 알루미늄 덩어리를 생성하여 증착할 수 있을 경우, 뛰어난 재배열 효과를 이용하여 품질이 향상된 반도체 소자를 제조할 수 있을 것으로 사료된다.

• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.4
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• pp.77-86
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• 2016

A numerical analysis is performed to investigate the effect of a supply channel and jet hole arrangement on the heat flow characteristics of impingement jet. The jet holes in a supply channel are composed of a single or staggered array from the center of a leading edge channel. The software ICEMCFD is used to generate the structured grids for calculation domain and a CFD code CFX 15.0 to perform the simulation. The present solutions are validated by comparison with the experimental and numerical ones of others. A comparison of mass flow rates of impingement jets and Nusselt numbers on the impingement surface for the single or staggered arrays is made.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.5
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• pp.54-61
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• 2014

In this study, a plume exhausted from rocket nozzle is investigated by using an unstructured 2-dimensional axisymmetirc DSMC code at various altitude. The small back-pressure to total-pressure ratio($P_b/P_o$) and large $P_b/P_o$ represent low and high altitude condition, respectively. At low altitude, the plume shows a typical complicated structure (e.g. Mach disk) of underexpanded jet while the high altitude plume experiences plain expansion. The various features of exhaust plume is discussed including density, translational/rotational temperature, Mach number and Knudsen number. The results shows that even at 20 km altitude where the freestream Knudsen number is small as $1.5{\times}10^{-5}$, the transitional and rarefied flow regimes can occur locally within the plume. It confirms the necessity of DSMC computation at low altitude.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.1
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• pp.9-16
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• 2019

In the present study, to investigate flows around space launch vehicles at mid-high altitudes efficiently, a three-dimensional unstructured mesh Navier-Stokes solver employing a Maxwell slip boundary condition was developed. Validation of the present flow solver was made for a blunted cone-tip configuration by comparing the results with those of the DSMC simulation and experiment. It was found that the present flow solver works well by capturing the velocity slip and the temperature jump on the solid surface more efficiently than the DSMC simulation. Flow simulations of space launch vehicles were conducted by using the flow solver. Mach number of 6 at the mid-high altitude around 86km was considered, and the flow phenomena at the mid-high altitude was discussed.