• Journal of the Korean Institute of Landscape Architecture
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• v.50 no.2
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• pp.102-115
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• 2022

The purpose of this study is to present types of design concept based on the specificity of landscape design, and to derive a theoretical framework for the landscape design concepts by analyzing the design concepts appearing in urban park design competitions. Through literature review, five types of landscape design concepts were categorized into value and vision, analysis and interpretation, form and structure, program and element, and process and operation. Using this framework, the design concepts shown in 96 works submitted to 18 domestic and overseas urban park design competitions were analyzed. The results of the analysis are summarized as follows. First, due to the complexity of contemporary urban parks, design concepts are presented as mixtures of main concepts and secondary concepts in multiple layers. Second, it was identified that design concepts of 'form and structure' were used the most in urban park designs, followed by the 'program and element' concepts. The 'value and vision' and 'analysis and interpretive' concepts are introduced as third and fourth. Third, the reason that the 'form and structure' concept is widely used as main and secondary concepts is judged to be because the form of a space, which is the key result of the design, has an important influence on the identity of the design. Fourth, the reason that the 'program and element' concept type is widely introduced is that urban park design has a stronger planning aspect to produce programs during the design process, compared with other design fields where programs are usually given in advance. Lastly, it is difficult to see that the properties of the site solely affect the type of design concept, because a design concept is the result of a complex and creative process in which a designer subjectively interprets the objective characteristics of the site and project, and given design guidelines can affect the type of design concept.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.34 no.12
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• pp.1843-1848
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• 2010

This paper presents an analysis of the design hypothesis of integration of parts from the viewpoint of axiomatic design. In parts integration, parts with the same functions are integrated into a single part. For the analysis, a motor actuator of an outside rear-view mirror with the type of an uncoupled design was used. The parts within the actuator are checked for determining the possibility of integration, by adopting the design hypothesis of integration of parts. The design hypothesis of integration of parts is based on a type of coupled design. However, the type of incomplete coupled design that resembles the type of an uncoupled design would be better than the type of a coupled design.

• Proceedings of the Korean Nuclear Society Conference
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• 1998.05a
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• pp.699-706
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• 1998

한국원자력연구소에서는 원자력중장기연구의 일환으로 한국형 표준원전을 모의하는 종합열수력실증실험을 계획하고 있으며, 현재 실험장치에 대한 척도해석(Scaling Analysis), 예비해석(Scoping Analysis) 및 개념설계를 수행하고 있다. 본 논문에서는 영광 3/4호기를 대상으로 척도해석을 통하여 실험장치를 개념설계하고, 저온관 6인치 소형냉각재 상실사고에 대하여 예비해석을 수행한 결과를 보여준다. 개념설계된 실험장치는 높이비가 참조원자로와 동일하고, 체적비가 1/200이다. 실험장치의 개념설계는 이상유동에 대한 3단계 척도법을 적용하였으며, 개념설계의 타당성을 입증하기 위해 RELAP5/MOD3.1 코드를 사용하여 정상상태 및 저온관 6인치 소형냉각재 상실사고시 계통의 거동을 예비 계산하였다. 실험장치에 대한 예비해석결과 사고 거동이 참조원자로와 잘 일치하는 것으로 나타났다. 또한 수평관 및 주냉각재펌프의 척도기준이 사고의 진행과정에 영향을 미치는 중요한 인자로 밝혀졌다

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.10
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• pp.877-886
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• 2016

A validation study is conducted for the conceptual design and performance analysis of UH-60A Black Hawk in order to establish the conceptual design and performance analysis techniques for conventional helicopters using a single main rotor and a tail rotor. As a tool for conceptual design and analysis, NDARC(NASA Design and Analysis of Rotorcraft) is used for the present study. The conceptual design for UH-60A is successfully validated as compared with the target values. Then, various performance analyses in hover and forward flight are conducted for the UH-60A model obtained from the present design work, and they are compared well with the wind tunnel test, flight test, and previous analyses using various analysis tools. Through this validation work, the conceptual design and performance analysis techniques for the conventional helicopter are appropriately established.

• Journal of Energy Engineering
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• v.4 no.1
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• pp.52-58
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• 1995

석탄가스화 복합발전 플랜트의 시스템설계를 위한 engineering package의 체계 및 방법론에 대해 소개하였다. Engineering package는 플랜트 전체 개념설계 과정과 주요 공정을 구성하는 요소에 대한 설계/해석/시험 과정으로 나누어 진다. 개념설계과정은 설계목적과 제한조건을 충족시키도록 플랜트구성 설계, 정적/동적 시뮬레이숀, 요소별 설계사양 결정 및 Data Base Management System으로 이루어지며, 개념설계 과정의 한부분인 주요요소의 설계는 1차원 성능해석, 2/3차원 열유체해석 및 실험 그리고 구조, 진동 해석 등으로 구성되는 반복적 과정이다. 그러므로, 본 연구에서는 이러한 설계체계들의 개발전략을 설명하고, 현재 이루어진 추진결과에 대해 설명하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.6
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• pp.568-583
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• 2015

In this paper, the conceptual design procedure and results of Earth observation satellite through Multidisciplinary Design Optimization (MDO) are described. The conceptual design equations for major parameters are developed based on the established database of Earth observation satellite so far. The MDO conceptual design tool for Earth observation satellite was developed by applying the Collaborative Optimization (CO) architecture amongst several MDO architecture techniques available today. The objective for this research was set to minimize the total mass of satellite as well as satisfy all design constraints by utilizing the Sequential Quadratic Programming (SQP) algorithm. Eventually the effectiveness of MDO conceptual design tool was verified through proposing a comparison between the conceptual design results with MDO applied and the design specification of ASNARO-1 & IKONOS-2 Earth observation satellite.

• Journal of the Society of Naval Architects of Korea
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• v.35 no.4
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• pp.109-117
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• 1998

In a preliminary design available information is limited, so it makes attractive to rely on the design cases of existing ships to design new ships. In this paper a prototype of the case-based conceptual design system of a ship is developed to support systematically the design process. This system not only generates design candidates through a case indexing, but also determines the priorities of the candidates by using nearest neighbor matching algorithm. The final solution is presented through adaptation process. The validation of the system was examined and verified by applying to conceptual ship design stage.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.1
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• pp.16-24
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• 2012

In this study, two-stage hypersonic scramjet vehicle was designed for the flight condition of Mach number 6. In order to launch at sea level, two stage concept was applied. The first stage of the vehicle is solid rocket-powered and is mounted under the second stage. The second stage is powered by scramjet propulsion system and gas wings. The suggested mission scenario is to deliver 0.2 ton payload to the range of 2,000 km. For the first step of conceptual design, trajectory of air vehicle was calculated by 3-DOF trajectory code. Based on the result of trajectory code, scramjet engine design and mass estimation were performed by non-equilibrium nozzle flow code and NASA's HASA model, respectively. In order to find best solution, all steps of designing process was iterated until they was reached.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.309-317
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• 2011

In this study, two-stage hypersonic scramjet vehicle was designed for the flight condition of Mach number 6. In order to launch at sea level and Mach number 0, two stage concept was applied. The first stage of the vehicle is rocket-powered and is mounted under the second stage. The second stage is scramjet-powered propulsion system and has wing. The suggested mission scenario is to deliver 0.2 ton payload to the range less of 2000km. For the first step of conceptual design, trajectory of air vehicle was calculated by 3-DOF trajectory code. Based on the result of trajectory code, scramjet engine design and mass estimation were performed by non-equilibrium nozzle flow code and NASA's HASA model, respectively. In order to find best solution, all step of designing process was iterated until they were converged.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.9
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• pp.923-930
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• 2009

In this paper, we introduce a satellite conceptual design software which can be used for outlining a new satellite as well as for educational purpose. This software consists of three commercial tools: MATLAB, STK(Satellite Tool Kit), and Excel. The management of the design software is done by MATLAB which provides basic calculations, GUI(Graphical User Interface), Excel data base management, and STK control. STK, an orbital simulation software developed by AGI, takes a part of obtaining accurate orbital information of a satellite. Excel, a product of Microsoft, is used for the data base of previous satellites and for the saving place of temporary and final results of the software. The conceptual design of a satellite is to roughly estimate power system and mass. In the power system design, the sizes of solar array and battery are determined. Based on the database of existing satellites, we can estimate the subsystems's mass fraction of a target satellite. Design examples for Kompsat 1 and 2 are suggested for verification of the developed software.