• Composites Research
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• v.30 no.1
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• pp.52-58
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• 2017

This paper presents the optimum design methodology for composite wing structure which automatically calculates the safety margin using optimization framework integrating failure modes. Particularly, its framework is possible to optimize sizing procedure to prevent failure mode which has the greatest effect on reducing the sizing time of composite structure. The main failure mode was set as the first ply failure, buckling failure mode, and bolted joint stress field, and the margin was calculated to minimize the weight. The design variable is a laminate sequence database and the responses are strain, buckling, bolted joint stress field. The objective function is the mass of the wing structure. The results of buckling analysis were compared using the finite element model to verify the robustness and reliability of Composite Optimizer.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.6
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• pp.519-526
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• 2009

This paper describes a research result of a external shape optimization study to maximize the range of the guided missile with canards and tailfins in atmospheric flight. For this purpose, the external shape optimization program which can enhance the range of a missile was developed, incorporated with the trajectory analysis and the optimization technique. In the trajectory analysis part, Missile DATCOM which utilizes the semi-empirical method was directly connected to the trajectory code to supply the aerodynamic coefficients efficiently at every time step. In the gliding flight trajectory after apogee, a maximum $C_L/C_D$ trim condition calculation module was attached under the assumption of the missile continuously flying at maximum $C_L/C_D$ condition. In the optimization part, a Response Surface Method(RSM) was adopted to reduce the computing time.

• Journal of the Korean GEO-environmental Society
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• v.20 no.1
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• pp.43-49
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• 2019

In this paper, we introduced phase optimization techniques in the Soil-Nail design to optimize the reinforcement required for each grade level. The optimal design results at the maximum slope height were further amplified to allow for phase optimization of the horizontal spacing of the Nail in accordance with the change in the height of the slope. The limit equilibrium analysis was performed by step-by-step sloping height, and the safety factor exceeded when the horizontal spacing of four days was fixed. The process of optimization was effectively carried out by densifying the required reinforcement depending on the slope elevation. Also limited to reflect the axial force of the nail into the reinforcement details.Using the method, the members' strength was reflected. When phase optimization technique is applied for each slope height by calculating the stiffening precision, it is judged that it will be more economical to optimize horizontal intervals by effectively reducing the repeated reinterpretation process that satisfies the reference safety ratio for each slope height.

• Proceedings of the Computational Structural Engineering Institute Conference
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• 2009.04a
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• pp.157-160
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• 2009

멀티 피직스 시스템은 구동을 수치적으로 해석하기 위하여 두 개 이상의 연성이 되어 있는 물리계를 고려해야하는 시스템을 일컫는다. 대표적인 예로 기계 분야에서 현재까지 많이 연구되어 왔던 열탄성(Thermal/Structure)과 유체/구조 연성(Fluid/Structure)시스템을 들 수 있다. 또한 현재 차세대 성장산업으로 많은 관심이 집중되고 있는 의료기기나 지능형 자동차와 로봇 등에서 사용되는 다양한 센서와 엑추에이터 등도 특별한 예로 들 수 있다. 특히, 한 개의 물리계 해석으로 시스템 해석이 가능한 기존의 일반적인 기계 시스템과는 달리 MEMS 등의 초소형 시스템은 시스템의 거동을 수치적으로 계산하기 위하여 여러 물리계의 연성을 고려해야 한다는 점에서 대표적인 다물리계 시스템의 예로 들 수 있다. 이렇게 우리생활에 밀접하게 쓰이고 있는 멀티 피직스 시스템은 단일 물리계 시스템과 비교하여 엔지니어의 경험에 의존하여 설계(Design)하기가 어려운 특성이 있다. 이에 이 연구 논문에서는 이런 멀티 피직스 시스템을 해석하고 최적화 하기위한 노력을 소개한다.

• Proceedings of the KAIS Fall Conference
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• 2009.12a
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• pp.511-514
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• 2009

현재 일반적으로 사용되는 300cc 소형엔진 기화기의 최적화 및 성능 향상을 위하여 유동해석을 수행하였다. 베르누이의 정리를 기본으로, 성능을 발휘하는 주요 설계인자인 기화기 내부의 벤튜리 튜브의 각도, 길이 등을 변수로 하여 유동해석을 수행하였다. 그 결과를 분석하여 최적화된 모델을 제시하였다. 결론적으로, 유동 해석을 바탕으로 기존 사양 대비 향상된 성능의 모델을 제시하였다. 유동해석을 통해 기화기 내부의 벤튜리관에 곡면(Rounding)처리를 적용함으로 기화기에서 소모되는 흡기저항을 줄여 펌핑로스를 저감활수 있음을 확인하였다. 펌핑로스의 저감은 엔진 연비의 향상과 엔진토크에 긍정적 효과로 작용할 것으로 기대된다. 벤튜리관의 출구 각도를 감소시킴으로 박리를 개선하여 Dead Volume을 줄임으로서 기존 모델에 대비하여 원활해진 유동의 흐름을 얻을 수 있었다. 이는 흡기유량을 증대시키고 엔진출력을 상승시키는 효과로 작용할 것으로 예상된다.

• Proceedings of the Computational Structural Engineering Institute Conference
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• 2011.04a
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• pp.345-348
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• 2011

구조요소의 설계에서 유한요소해석은 매우 효과적인 방법이다. 이 방법은 시험 수행에 드는 시간과 비용을 줄여준다. 그러나 공정 과정과 환경에 의하여 생기는 입력 물성치들의 변화 때문에 우리는 유한요소해석의 결과를 전적으로 믿어서는 안 된다. 따라서 유한요소해석의 신뢰성을 증명하는 것은 매우 중요하다. 본 연구에서는 현장에 축적된 피로 수명 시험 데이터를 바탕으로 유한요소해석을 이용하여 피로수명 파라미터를 역 추정 하는 연구를 수행하였다. 베이지안 접근법을 이용하여 불확실성 피로 수명 파라미터의 사후분포를 구하였고, 마코프체인몬테카를로(Markov Chain Monte Carlo) 기법을 이용하여 역 추정된 파라미터의 샘플 데이터를 생성하였다. 얻어진 샘플 데이터를 기반으로 새로운 형상의 스프링에 대한 피로 수명을 예측한다. 신뢰성 기반 형상 최적화(RBDO)는 서스펜션 코일 스프링의 요구수명을 만족시키기 위하여 수행된다. 또한 크리깅 근사 모델은 유한요소해석의 연산 량 감소를 위해 이용한다.

• Composites Research
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• v.30 no.5
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• pp.297-302
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• 2017

Finite element analysis of T-beam laminate structure under bending-torsional loading was conducted to prevent the delamination which is the major failure behavior on laminated composites. Three-dimensional preform, which is that fabric is braided through thickness direction, is suggested from the laminate analysis. The analysis aimed to optimize the fiber ratio in laminated composites. After it is suggested that guideline for design of T-beam structure using commercial software ANSYS Composites PrePost. The results show that strength of T-beam structure is increased 21.6% when the fiber density along with beam length direction is two times bigger than transverse direction. It is expected that development of high strength T-beam structure using designed three-dimensional preform.

• Journal of Korean Society of Steel Construction
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• v.12 no.3 s.46
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• pp.317-328
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• 2000

The objective of the research is to develop an algorithm for the optimum design of two-dimensional braced steel frames using an advanced analysis, which considers both material and geometric nonlinearties. Since both nonlinearties are considered in analysis process, Optimum design algorithm which does not require to calculate K-factor is presented. A multi-level discrete optimization technique with two parameters that uses the information of structural system and separate member has been developed. The structural analysis is performed by the relined plastic-hinge method which is based on zero-length plastic hinge theory. Optimization problem are formulated by AISC-LRFD code. The feasibility, validity and efficiency of the developed algorithm is demonstrated by the results of the braced steel frame.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.7
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• pp.716-726
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• 2010

In this research, design optimization of an aircraft wing has been performed using the fully automated Multidisciplinary Design Optimization (MDO) framework, which integrates aerodynamic and structural analysis considering nonlinear structural behavior. A computational fluid dynamics (CFD) mesh is generated automatically from parametric modeling using CATIA and Gambit, followed by an automatic flow analysis using FLUENT. A computational structure mechanics (CSM) mesh is generated automatically by the parametric method of the CATIA and visual basic script of NASTRAN-FX. The structure is analyzed by ABAQUS. Interaction between CFD and CSM is performed by a fully automated system. The Response Surface Method (RSM) is applied for optimization, helping to achieve the global optimum. The optimization design result demonstrates successful application of the fully automated MDO framework.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.30 no.2
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• pp.153-158
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• 2017

In this paper, we take into account topology optimization problems considering spatial randomness in the material property of elastic modulus. Based on 88 lines MATLAB Code, Monte Carlo analysis has been performed for MBB(messerschmidt-$b{\ddot{o}}lkow$-blohm) model using 5,000 random sample fields which are generated by using the spectral representation scheme. The random elastic modulus is assumed to be Gaussian in the spatial domain of the structure. The variability of the volume fraction of the material, which affects the optimum topology of the given problem, is given in terms of correlation distance of the random material. When the correlation distance is small, the randomness in the topology is high and vice versa. As the correlation distance increases, the variability of the volume fraction of the material decreases, which comply with the feature of the linear static analysis. As a consequence, it is suggested that the randomness in the material property is need to be considered in the topology optimization.