• 한국실내디자인학회논문집
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• 제21권2호
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• pp.46-55
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• 2012

This study aims to analyze the design concepts of Libeskind's Jewish museums through their comparisons for figuring out his design intentions and characteristics in the realization process. Libeskind's realized four Jewish museums are chosen for this study. For more concrete study, their extracting and application process are also reviewed. The comparison of his museum designs can be good examples in that they show different design approaches on the same architectural type, Jewish museum, to tell their something in common from differences. He could realize his architectural thoughts and configuration methods made by experimental drawings for the first time as real buildings through a series of Jewish museum projects. The commonness of Libeskind's Jewish museums lie on their sharing design concept of Jewish 'history and memory', especially Holocaust, and realized as in contrast to surroundings and 'labyrinth' of spatial configuration to maximize spectator's experiences. As Libeskind regards museum architecture as a carrier of 'time and place', he tried to reflect surrounding context including places, cities, persons and events about museum programs. As a result, unprecedented museums which are not related to traditional museum systems about circulation and spatial configuration are suggested for users to experience Jewish life and history through architecture.

• 한국군사과학기술학회지
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• 제17권2호
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• pp.189-196
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• 2014

Automated design program using commercial process integration and optimization program was developed for conceptual design of fighter-class aircraft. Wind tunnel test data and performance analysis results were compared for the verification of analysis tool of this program, and the usefulness of the tool was found. After integration with radar cross section analysis tool, the correlation with configuration design variables of wing, tail and performance parameters was identified by design of experiment, and the optimized configuration for weight and RCS was derived from optimization of empty weight and average frontal RCS value. After parameter definition of fuselage, the program can be implemented for full aircraft configuration.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2004년도 추계학술대회
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• pp.430-434
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• 2004

Specifically designed mandrel is needed to expand tube of the heat exchanger with inner grooves. Configuration of the expanded tube depends upon the shape and feeding velocity of the mandrel. 3D simulation software LS-DYNA was used to obtain optimum design conditions of the mandrel. We show how configuration of the expanded tube varies with different design parameters such as the approaching angle, diameter , and the feeding velocity of the mandrel. Material property data for analysis were obtained through experiments with SHPB ( Split Hopkinson Pressure Bars ).

• 한국철도학회:학술대회논문집
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• 한국철도학회 2001년도 추계학술대회 논문집
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• pp.322-328
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• 2001

In the electric railway systems, it is very important that we should design the system configuration, location and power capacity of substation. This paper presents the results of system configuration and system design of the DC traction power supply for the test line of Light Rail Vehicle. The voltage fluctuation of train and the power capacity of substation are calculated by computer simulation using the nodal equation, K.C.L／K.V.L, Ohm's law and superposition theory.

• Journal of applied mathematics & informatics
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• 제12권1_2호
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• pp.307-312
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• 2003

In this paper, a special incidence structure is designed based on (v, k+1, 1)-configuration, a subset of symmetric balanced incomplete block design, where ν = k$^2$+ k + 1. The time complexity required for desinging this incidence structure is O(equation omitted).

• 한국항공우주학회지
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• 제42권6호
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• pp.478-487
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• 2014

개념설계는 복합시스템인 무인기의 성공적인 개발을 위해 가장 중요한 단계로써 간단한 성능해석과 형상설계가 수행된다. 개념설계 단계에서의 성능해석은 복잡한 해석도구를 사용하기 보다는 주로 경험식이나 통계적 데이터를 이용한 추세방정식을 사용한다. 무인기의 형상은 매우 다양하여 개념설계 단계에서 이러한 모든 항공기 형상을 고려하기에는 어려움이 있다. 본 연구에서는 무인기 개념설계를 위해 주요 성능변수에 대한 추세방정식을 도출하였고, 자주 사용되는 형상 선정을 위해 최대이륙중량 50-1,500kg 급의 중소형 무인기에 대한 데이터베이스를 구축하였다. 또한 주요 성능변수들에 대한 파라미터 분석을 수행하였으며, 이들 성능변수에 대한 상관도 분석결과에 따라 높은 상관도를 보이는 최대이륙중량과 날개폭을 기준으로 각 성능요소별 회귀분석을 수행하여 추세방정식을 도출하였다.

• International Journal of Aeronautical and Space Sciences
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• 제14권1호
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• pp.99-104
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• 2013

Configuration design, analysis, and wind tunnel test of a vane-type multi-function air data probe (MFP) was described. First, numerical analysis was conducted for the initial configuration of the MFP in order to investigate aerodynamic characteristics. Then, the design was modified to improve static and dynamic stability for better response characteristics. The modified configuration design was verified through wind tunnel tests. The test results are also used to verify the accuracy of the analytical method. The analytically estimated aerodynamic damping provided by the Navier-Stokes equation solver correlated well with the wind tunnel test results. According to the calculation, the damping coefficient estimated from ramp motion analysis yielded a better correlation with the wind tunnel test than pitch oscillation analysis.

• 대한기계학회논문집B
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• 제20권7호
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• pp.2356-2366
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• 1996

High-power electronic chips have been advanced to such an extent that the heat dissipation capability of a system design has become one of the primary limiting factors. Therefore, thermal design must be considered in the early stage of the electronic system development. In present paper, the results of an experimental study on the forced convection cooling are presented to evaluate cooling performance of an electronic cabinet which in generally used for telecommunication system. Temperatures and thermal resistances are applied to compare the heat transfer characteristics for various locations of a fan unit as well as various configuration of non-uniform powering modules. As a result, the optimal configuration of a fan unit and powering configuration is suggested for the effective thermal design of telecommunication system.

• 한국자동차공학회논문집
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• 제10권1호
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• pp.67-75
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• 2002

A study to investigate the influence of combustion chamber shape, especially piston top face configuration, on the combustion stability is presented with CFD analysis and single cylinder GDI engine test. Initial configuration of the piston bowl was designed with CFD analysis and further parametric studies of the design factors on the piston top face were carried out through the single cylinder GDI engine test. It was found that both the geometry of piston top face and the compression ratio have great influences on the combustion stability. Of interest is that the design factors of the GDI piston to prevent mixture diffusion out of the piston bowl have important roles for the stable combustion at the stratified mixture condition. Also the relationship between spray impingement and flow pattern in a GDI piston bowl should be considered to design an optimal bowl configuration for stable stratified combustion.

• Advances in aircraft and spacecraft science
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• 제9권1호
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• pp.17-37
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• 2022

This paper discusses an improved unmanned aerial vehicle, UAV, configuration characterized by telescopic booms to optimize the flight mechanics and fuel consumption of the aircraft at various loading/flight conditions.The starting point consists of a full-composite smaller UAV which was derived by a general aviation ultralight motorized aircraft ULM. The present design, named ToBoFlex, extends the two-booms configuration to a three tons aircraft. To adapt the design to needs relevant to different applications, new solutions were proposed in aerodynamic fields and materials and structural areas. Different structural solutions were reported. To optimize aircraft endurance, the innovative concept of Telescopic Tail Boom was considered along with two different tails architecture. A new structural configuration of the fuselage was proposed. Further consideration of hydrogen fuel cell electric propulsion is now being studied in collaboration between the Polytechnic of Turin and Prince Mohammad Bin Fahd University which could be the starting point of future investigations.