• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.1
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• pp.86-91
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• 2008

An integrated multidisciplinary analysis and design system plays a critical role in the preliminary design of an aircraft. In this work a system based on the CATIA is developed for multidisciplinary computational design; aerodynamics, elasticity, and radar frequency stealth. Common data base of geometry and rectangular grids is generated and used for aerodynamic and structural analysis, while derivative triangular grids are generated for the RCS calculation. The panel method (PANAIR), FEM (NASTRAN), and PO technique are used for aerodynamic, structural, and RF stealth computations, respectively, and several additional algorithms are developed for the effective communication of the common data.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.8
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• pp.34-41
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• 2005

A parallel computing technique was applied to large scale structure analysis or aerodynamic design and it is a essential element in reducing the huge computation time for large scale design problem. We can use a many computers for reducing the analysis time of multidisciplinary design optimization. But previous MDO frameworks can not support a parallel design process technique so still existing which calls an analysis program continuously. In this paper, We developed a MDO framework(MLR) which supports a parallel design process to solve sequential analysis call. Finally, three sample cases are presented to show the efficiency of design time using the suggested MDO framework.

• Aerospace Engineering and Technology
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• v.12 no.2
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• pp.24-29
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• 2013

A spacecraft radiator is a thermal control method to eject internally dissipated heat into the space generated from operation of unit boxes. The efficiency of thermal design may be improved by optimizing radiator design. In this paper, the optimization approach method of node-based radiator design was suggested which is to combine numerical thermal analysis with optimization algorithm. This method has meaning that it can be used practically to implement the spacecraft radiator design regardless of thermal analysis and optimization algorithm software and maintain the same basic concept of an ordinary radiator design approach based on node division of a thermal model. The overall analysis framework with thermal analysis and optimization algorithm would be presented.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.8
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• pp.27-35
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• 2003

Geometric modeling tool and analysis tool of shell surface have been developed in the different environments and purposes. Thus they cannot be naturally fitted to each other for the integrated design and analysis. In the present study, an integrated framework of geometric modeling, analysis， and design optimization is proposed. It is based on the common representation of B-spline surface patch. In the analysis module, a geometrically-exact shell finite element is implemented. In shape optimization module, control points of the surface are selected as design variables. For the computation of shape sensitivities, semi-analytical method is used. Sequential linear programming(SLP) is adopted for the shape optimization of surfaces. The developed integrated framework should serve as a powerful tool for the geometric modeling, analysis, and shape design of surfaces.

• Journal of the Korean Society for Precision Engineering
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• v.15 no.12
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• pp.236-243
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• 1998

퍼지 이론과 계산기하학적 수법에 의한 자동요소 생성법, 해석코드 및 상용 솔리드 모델러를 유기적으로 통합한 자동화된 설계시스템을 개발하였다. 본 시스템은 여러 가지 복합현상과 관련된 실제 구조물에 대한 설계기능을 갖고 있다. 정전장 해석, 변형해석 및 모드해석 등과 같은 해석하고자 하는 물리적인 현상에 의존한 형상모델이 자동적으로 유한요소모델로 변환되어 해석을 수행한다. 또한 신경망의 기능을 도입, 통합시킴으로써 설계해의 영역을 유용하게 제시하여 준다. 개발한 시스템은 정전 마이크로머쉰의 성능 평가에 적용하여 그 효용성을 검증하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.12
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• pp.1121-1128
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• 2007

MDO(Multidisciplinary Design and Optimization) can be applied for design of complex systems such as aircraft and SLV(Space Launch Vehicle). MDO System can be an integrated environment or a system, which is for synthetic and instantaneous analysis and design optimization in various design fields. MDO System has to efficiently use and integrate distributed resources such as various analysis codes, optimization codes, CAD, DBMS, GUI, and etc. in heterogeneous environments. In this paper, we present Web Services-based MDO System that integrates resources for MDO using Globus Toolkit and provides organic autonomous execution using automation technique such as Workflow system and agent. And also, it provides collaborative design environment through web user interfaces.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.7
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• pp.685-692
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• 2009

This paper dealt with the development of the Framework for Multidisciplinary Design Optimization for the rotorcraft design concept and the building process of KHP(Korea Helicopter Project) - SDM(Simulation Data Management) system to manage various analysis data, which are used in the rotorcraft development phase. KHP-SDM RMDO(Rotorcraft Multidisciplinary Design Optimization) framework, which applied optimization modules of KHP-SDM and integrated the developed Multidisciplinary analysis modules, was constructed in the KHP-SDM. The results of the rotorcraft conceptual design using KHP-SDM RMDO showed that the framework was evaluated to be successfully constructed.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.38 no.4
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• pp.289-309
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• 2014

A rotor blade is an important device that converts kinetic energy of wind into mechanical energy. Rotor blades affect the power performance, energy conversion efficiency, and loading and dynamic stability of wind turbines. Therefore, considering the characteristics of a wind turbine system is important for achieving optimal blade design. This study examined the general blade design procedure for a wind turbine system and aero-structure design results for a 2-MW class wind turbine blade (KR40.1b). As suggested above, a rotor blade cannot be designed independently, because its ultimate and fatigue loads are highly dependent on system operating conditions. Thus, a reference 2-MW wind turbine system was also developed for the system integrated load calculations. All calculations were performed in accordance with IEC 61400-1 and the KR guidelines for wind turbines.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.14 no.2
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• pp.151-157
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• 2001

iTOP(integrated-design Tool Of Plant)은 철골공장을 대상으로 한 모델링, 구조해석, 후처리, 부재설계, 구조계산서, 구조도면 및 물량산출에 이르는 일련의 과정을 유기적으로 통합한 시스템이다. 크레인 주행도를 주요 인터페이스 도구로 이용하고 \"크레인 하중조건\"이라는 개념을 새로이 도입함으로써, 각 크레인의 주행 범위 및 하중 옵션을 경우별로 설정할 수 있도록 하였다. 이에 따라 크레인거더의 설계 및 해석하중의 계산이 효과적으로 이루어지고, 제반 데이터에 따른 크레인 하중조합의 산정은 완전히 자동화되었다.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2004.05a
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• pp.224-224
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• 2004

제품 개발 초기 단계에서 제품의 개념을 신속하게 구체화하여 제품의 기능, 구성, 부품 간 관계, 치수 및 간단한 형상들을 정의한 후, 검증(해석 및 실험)을 통해 가장 최적화된 설계 결과를 얻는다. 그러나 이 과정에서 일반적으로 설계 정보를 바탕으로 해석을 수행하기 위한 모델을 새롭게 생성해야 하는 문제가 있다. 또한 설계 변경이 발생하는 경우에는 도면을 다시 작성하고 해석 모델이 재생성 및 부품 생성을 위하여 데이터 입력을 다시 해야 한다. 이러한 문제는 선박의 초기 설계 및 해석 분야에서도 발견할 수 있다.(중략)