• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.6
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• pp.23-33
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• 2004

MDO framework, which provides multidisciplinary system design and optimization environment, requires integration of the analyses codes developed at various computer languages and operating systems, integration of CAD and DBMS, and development of complex GUI. Emphases must be given to the software modification and upgrades in conjunction with the analysis code addition and MDO method implementation. In this study, techniques about system integration and analysis code interface have been studied extensively, and the database design and communication methods which can handle the MDO methods like MDF and CO have been studied. Using the dedicated MDO framework developed for the air vehicle design, the multidisciplinary fighter aircraft wing design has been performed to demonstrate the efficiency and usefulness of the software. Optimum wing configuration is derived using the gradient-based optimization methods within thirty design iterations.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.10
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• pp.947-953
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• 2008

MDO(Multidisciplinary Design and Optimization) framework can be an integrated environment or a system, which is for synthetic and simultaneous analysis and design optimization in various design fields of aerospace systems. MDO framework has to efficiently use and integrate distributed resources such as various analysis codes, optimization codes, CAD tools, DBMS and etc. in heterogeneous environment, and to provide graphical and easy-to-use user interfaces. Also, its development method can be changed by design objects and development environment. In this paper, we classify MDO frameworks into three types according to the development environments: Single PC-based, PLinda-based and Web Services-based MDO framework. And, we compare and analyze these frameworks.

• Journal of Korea Foundry Society
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• v.17 no.6
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• pp.552-559
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• 1997

주조방안설계를 위한 pre-processor, main-solver 그리고 post-processor로 구성된 통합 응고해석 시스템을 개발하였다. Pre-processor는 퍼스널 컴퓨터에서 사용되는 상용 CAD 프로그램인 AutoCAD를 사용하였다. Main-solver는 주조과정중의 충진거동을 해석한 유동해석 프로그램과 3차원 열전달 응고해석을 통합하여 냉각수 시스템으로 제어되는 금형 반복주조법에서의 응고양상을 해석할 수 있다. Post-processor는 cavity내의 용탕충진거동, 주형내의 온도분포, 응고시간등을 3차원 그래픽으로 처리할 수 있게 설계하였다. 개발된 시스템의 현장적용 가능성을 검증하기 위하여 대형주강 밀하우징, 자동차휠 주조용품, 밸브블럭등의 시제품의 열유동해석에 적용하였다. 본 연구에서 개발된 CastDesigner는 중소기업형 주조현장에서 PC용 CAD/CAE system 구축을 통한 최적주조방안 설계용 열유동해석 프로그램으로 사료된다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.34-37
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• 2009

The present study presents a numerical methodology for early conceptual trade-off study between propulsive performance, cooling efficiency, weight and size, in which combustion and cooling precesses in regeneratively cooled rocket thrust chamber are interactively simulated. To address the capabilities and reliability of the design tool, some application results are given involving contour design, performance analysis, and wall cooling prediction as well as a systematic design evaluation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.1
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• pp.75-84
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• 2021

The authors had presented two previous papers[1,2] on Helicopter/Rotorcraft develoment in Europe and US. Meanwhile, the next generation rotorcrafts, currently under development in US and Europe, have new configurations (tilt-rotor, coaxial, compound) of rotor-type vertical takeoff/landing rotorcrafts to overcome the disadvantages of traditional helicopters. For developing these new types of rotorcrafts, the upgraded conceptual design/comprehensive programs are required. In US and Europe, they are already developing new program tools with their technologies and database obtained during more than last half centuries. For us, many academia, research institutes and industrial engineers have experienced and developed core technologies on rotorcrafts (aerodynamics, structural analysis, flight dynamics, and noise analysis etc.) comparable to US and Europe during last couple of decades of developing helicopters and various configurations of rotorcrafts. In this paper, the pros and cons of conceptual design/comprehensive tools currently used in US and Europe have been summarized. Furthermore, the possibilities and problems to develope our own design and analysis tools have been studied.

• Proceedings of the Computational Structural Engineering Institute Conference
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• 2010.04a
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• pp.388-391
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• 2010

본 논문에서는 풍하중을 받는 구조물의 응답을 보다 적극적으로 저감시킴으로써 구조물의 안정성과 사용성을 개선하기위한 능동제어 알고리즘을 송도 자유무역 지구에 건설중인 포스코건설 사옥에 수치해석을 통해 적용하여 그 효과를 검증하였다. 수치해석에 의한 시뮬레이션 결과를 보면 최대 제어력이 제한이 된 비선형 제어기가 LQR 제어기와 등등한 제어효과를 가지고 있는 것으로 나타났으며, 제어력의 측면에서 본다면 비선형 제어기법이 더욱 유리한 것을 알 수 있다. 또한, 본 연구에서는 구조물과 질량형 제진장치의 상호작용을 고려하여 통합적으로 제진효과를 해석하고, 이를 바탕으로 제진장치를 설계할 수 있는 소프트웨어를 개발하였다. 구조물의 모드정보에 기초한 축소모델을 구축하고 제진장치의 설계 및 제진성능 평가를 수행하고 사용성을 평가하게 된다. 전체 소프트웨어는 질량형 제진장치의 설계프로그램과 질량형 제진장치의 종류별 대안설계결과를 등가감쇠비로 표현하여 비교평가하는 두 개의 모듈로 이루어져 있으며 전자는 비제어구조물 해석 모듈 및 TMD, TLD, TLCD, AMD를 대상으로 해석 및 설계를 수행하는 총 5개의 하부 모듈로 구성된다. 본 소프트웨어를 현재 TLCD가 설치되어 있는 인천 송도 국제업무지구의 주상복합건물에 적용하여 TMD, TLD, TLCD, AMD의 대안설계를 실시하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.4
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• pp.23-32
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• 2012

The present study is aimed to develop an integrated performance analysis approach for the application of a compressor with variable inlet guide vane (VIGV) and vairable stator vane (VSV) in a small turbofan engine. For the integrated analysis approach, an engine performance analysis program, NPSS and a computer program used for predicting of axial flow compressor performance based on stage stacking method, STGSTK were linked with an optimisation package, Isight. This enables off-design performance analysis for the turbofan engine with VIGV and VSV hence provides the capability to predict stable operation condition of the engine with acceptable surge margin.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.14 no.1
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• pp.57-64
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• 2001

일반적으로 기계부품의 설계는 부품의 설계, 해석, 그리고 시제품에 대한 성능변화를 통해서 수행된다. 이와 같은 방식의 설계는 여러 번의 시행착오에 따른 개발경비와 개발기간이 많이 소요되고 각 단계를 수행시킬 전문인력도 필요하므로 현재 산업현장에서 요구되는 신속하고 저렴한 제품개발에 적합하지 않다. 이를 해결할 수 있는 한 가지 방법으로 각 개발과정을 하나의 시스템에서 제어할 수 있는 통합시스템을 개발하는 것이다. 이런 통합시스템은 특정 제품에 대한 전용시스템이 될 가능성이 크지만 통합시스템을 구축하는 기법은 일반적인 제품들에 대해서도 적용이 가능하다. 본 논문에서는 자동차의 부품 중에서 좌석의 프레임 설계를 수행하는 통합시스템을 구축한다. 자동차 좌석은 법규에 규정되어 있는 강도와 강성을 만족해야 하므로 본 통합시스템에서는 정적조건 강도시험인 헤드레스트 테스트를 통해서 좌석을 설계한다. 그리고 통합시스템은 UNIX환경에서 C언어를 이용해 좌석 모델의 생성과 정적 성능평가를 수행할 상용프로그램들을 제어하며, 그래픽 환경은 Motif로 구현한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.2
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• pp.184-191
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• 2012

Aerodynamic analysis(DATCOM) and radar cross section(RCS) analysis(POFACETS) were integrated for the air-to-surface missile concept design using a design framework. The missile geometry was defined based on the CAD(CATIA) for synchronizing the manufacturing with design processes. Aero/RCS analyses were linked with the CAD process under the ModelCenter framework in order to receive the geometry data automatically. The missile design baseline configuration was selected from ROC(requirement of capability). Then the RCS minimization was performed subject to thelargerthebetter constraint of the missile lift-to-drag ratio. This study demonstrated that various design strategies can be performed efficiently about many missile configurations using this design framework in the missile conceptual design phase.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.13 no.1
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• pp.115-127
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• 2000

The purpose of this study is to propose the Design Object Model for implementation of an integrated structural design system for building structures. This study outlines the step-by-step development methodologies of the Design Object Model, which covers classification and modeling of the building design information. The Design Object Model has been efficiently developed through the proposed development methodologies. As a result, the Design Object Model has been proved to be efficient in design information management by representing the information from planning perspective, in recognition of structural member in space by the topology design object, and in representation of analysis s design information.