• Journal of the KSME
• /
• v.30 no.1
• /
• pp.9-16
• /
• 1990

CIM기술은 기업체 지원형 및 국산화형 생산기술과 더불어 필수적이고 상호 보완적인 산업기술이 고 또한 첨단제품기술 및 원천과학기술과의 연계가 가능한 접속(interface) 기술이다. 동시에 이의 연구개발은 다분야 공동참여적인 (multi-disciplinary) 기술적 배경을 필요로 하며 산업계 연구 수 행과 종속적이고도 이원적인 연구 체제가 필요하다. CIM기술개발의 예로서 제품 설계에서부터 설계의 해석 및 평가, 금형 설계, 공장 설계, 가공, 사상 및 측정. 검사까지의 과정과 생산통제를 포함하는 제반 생산 행위를 컴퓨터를 이용하여 생산 정보를 통합 제어함으로써 합리적인 금형 생산을 위한 사출 금형의 모델 플랜트를 소개하였다. 이 모델 플랜트는 설계, 공정 설계/NC, 연마, 측정. 검사, 시스템 통제의 5개 스테이션으로 구성되며, 각 스테이션에서의 중단위 통합 모델이 테스트되었다. 향후, 스테이션 간의 정보 흐름이 완전히 통합되면 금형업체는 물론 많은 제조업체에서의 광범위한 CIM기술 활용이 기대된다.

• Proceedings of the Korean Information Science Society Conference
• /
• 2008.06b
• /
• pp.547-552
• /
• 2008

여러 분야를 고려해야 하는 항공기나 자동차와 같은 대형기기의 설계에서 순차적 설계는 효과에 비하여 시간과 비용이 비효율적이며, 이러한 비효율성을 해결하기 위해 다분야 최적설계(MDO) 기법이 필요 하게 되었다. 비행체 설계는 시간이 지날수록 그 중요성이 커지고 있고, 설계 시 설계 전 분야를 통합하며 분석 할 수 있는 통합 환경이 요구되고 있다. MDO 기법을 이용한 비행체 설계는 이기종 분산 컴퓨팅 능력을 제공해야하고 각 분야의 데이터 공유를 통한 효율적 관리 및, 설계 최적화 도출을 제공하며 이기종의 환경을 고려해야 하므로, 분산 컴퓨팅 기술을 요구한다. 그리드 환경은 그리드 미들웨어를 중심으로 많은 분산 컴퓨팅 자원을 효율적으로 활용하고 다양한 분야의 문제들을 풀기 위한 고성능 환경을 제공하는 기술이다. 본 논문에서는 각 설계자원을 통합하기 위해 Globus toolkit ver.4(GT4)를 그리드 미들웨어로 사용하였고, 이들을 쉽고 효율적으로 이용하기 위한 PSE포탈을 제시한다.

• Transactions of the Korean Society of Automotive Engineers
• /
• v.20 no.6
• /
• pp.1-8
• /
• 2012

Multidisciplinary design optimization (MDO) for a suspension component of the vehicle front suspension was performed in this research. Shapes and thicknesses of the subframe were optimized to satisfy multi-disciplinary design requirements; weight, fatigue, crash, noise, vibration, and harshness (NVH), and kinematic and compliance (K&C). Analyses procedures of the performance disciplines were integrated and automated by using the process integration and design optimization (PIDO) technique, and the integrated and automated analyses environments enabled various types of analytic design methodologies for solving the MDO problem. We applied an approximate optimization technique which involves sequential sampling and metamodeling. Since the design variables for thicknesses should be dealt as discrete variables. the evolutionary algorithm is selected as optimization technique. The MDO problem was formulated three types of problems according to the order of priorities among the performance disciplines, and the results of MDO provided design alternatives for various design situations.

• Journal of Platform Technology
• /
• v.6 no.3
• /
• pp.31-37
• /
• 2018

Recently, the platforms for open science are being developed for helping researchers and scientists who are interested in convergence studies. This paper is focused on deriving a design method for an integrated architecture for knowledge infrastructure in science and technology and to set up the integration level of details and association between data and services in the integrated architecture. To facilitate the open science in research lifecycle, reconstructing individual services into modular and independent function blocks needs to be reusable and interoperable. The proposed design methodology is used for manipulating a service integration for the convergence service of S&T(Science and Technology) knowledge infrastructure. It can support to seamlessly access computing resources and the research results including artifacts digitally enabled scholars, researchers, and engineers participating in multidisciplinary collaborations.

• 한국신재생에너지학회:학술대회논문집
• /
• 2011.05a
• /
• pp.60.1-60.1
• /
• 2011

본 연구에서는 풍력 터빈 블레이드의 다분야 통합 최적 설계를 위하여, 진동하는 비정상 공력하중에 의한 작동 수명을 고려한 최적화 과정을 수행하였다. 최적화 대상으로는 NREL의 1.5MW 급 풍력터빈을 baseline 으로 하였고, NREL의 FAST 프로그램을 이용하여 발전기의 정격 출력 및 블레이드에 작용하는 비정상 공력 하중 특성을 분석하였다. 최적화 수행 시 블레이드 형상의 효율적인 구현을 위해 형상모델링 함수를 이용하여 코드 길이와 트위스트 분포를 모델링하였다. 그리고 상용 MDO Framework 인 Piano를 이용하여 블레이드 루트부의 비정상 공력하중 조건을 완화시키는 최적화 설계를 수행하였다. 정격출력을 유지하면서도 Out of Plain 방향의 하중 조건을 개선하여 보다 긴 작동 수명을 기대할 수 있는 블레이드 형상을 설계하였다.

• Journal of the Korea Academia-Industrial cooperation Society
• /
• v.16 no.6
• /
• pp.3661-3666
• /
• 2015

The paper describes the integrated design system using MDO and approximation technique. In MDO related research, final target is an integrated and automated MDO framework systems. However, in order to construct the integrated design system, the prerequisite condition is how much save computational cost because of iterative process in optimization design and lots of data information in CAD/CAE integration. Therefore, this paper presents that an efficient approximation method, Adaptive approximation, is a competent strategy via MDO framework systems.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.30 no.1
• /
• pp.20-27
• /
• 2002

Aircraft design requires the intergration of several disciplines, inculding aerodynamics, structures, controls. To achieves advances in performance, each technology, or discipline must be more accurate in analysis and must be more highly intergrated. One of the important interdisciplinary interactions in mordern aircraft design is that of aerodynamics and structures. In this study, for increasing accuracy in each discipline's analysis, CFD for aerodynamic analysis and FEM for structurral analysis was used and, for considering important interdisciplinary interactions, aeroelastic effect was considered. As optimization algorithm, PBIL algorithm was used for global optima and was parallelized to alleviate the computational burden. The efficiency and accuracy of the present method was assesed by range maximiziation of reference of reference wing.

• Transactions of the Korean Society of Mechanical Engineers A
• /
• v.27 no.4
• /
• pp.499-506
• /
• 2003

The design cycle associated with large engineering systems requires an initial decomposition of the complex system into design processes which are coupled through the transference of output data. Some of these design processes may be grouped into iterative subcycles. In analyzing or optimizing such a coupled system, it is essential to determine the best order of the processes within these subcycles to reduce design cycle time and cost. This is accomplished by decomposing large multidisciplinary problems into several sub design structure matrices (DSMs) and processing them in parallel This paper proposes a new method for parallel decomposition of multidisciplinary problems to improve design efficiency by using the multi-objective genetic algorithm and two sample test cases are presented to show the effect of the suggested decomposition method.

• 한국전산유체공학회:학술대회논문집
• /
• 2010.05a
• /
• pp.78-82
• /
• 2010

An integrated multi-disciplinary design system plays a critical role in the preliminary design of an aircraft. In this paper such system is developed for the multi-disciplinary computation and design; aerodynamics elasticity, and radio frequency stealth. Common data base of geometry and structured grids is generated and used for aerodynamic, structural and eletromagnetics analysis. The Navier-Stokes CFD, FEM, and CEM technique are used for aerodynamic, structural, and RF stealth computations respectively.

• Aerospace Engineering and Technology
• /
• v.13 no.2
• /
• pp.150-159
• /
• 2014

This study provides a brief introduction to application of the computational fluid dynamics to domestic development of combustion devices for liquid-propellant rocket engines. Multi-dimensional flow analysis can provide information on the flow uniformity and pressure loss inside the propellent manifold, from which the design selection can be performed during the conceptual design phase. Multi-disciplinary performance analysis of the thurst chamber can also provide key information on performance-related design issues such as fuel film cooling and thermal barrier coating conditions. Further efforts should be made to develop numerical models to resolve the mixing and combustion characteristics of LOX/kerosene near the injection face plate.