• International Journal of Aeronautical and Space Sciences
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• 제18권3호
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• pp.403-413
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• 2017

Dual-point aerodynamic design optimization is conducted for DLR-F6 wing-body-nacelle-pylon configuration adopting an efficient surface mesh movement method for complex junction geometries. A three-dimensional unstructured Euler solver and its discrete adjoint code are utilized for flow and sensitivity analysis, respectively. Considered design conditions are a low-lift condition and a cruise condition in a transonic regime. Design objective is to minimize drag and reduce shock strength at both flow conditions. Shape deformation is made by variation of the section shapes of inboard wing and pylon, nacelle vertical location and nacelle pitch angle. Hicks-Henne shape functions are employed for deformation of the section shapes of wing and pylon. By the design optimization, drag coefficients were remarkably reduced at both design conditions retaining specified lift coefficient and satisfying other constraints. Two-point design results show mixed features of the one-point design results at low-lift condition and cruise conditions.

• 한국유체기계학회 논문집
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• 제12권3호
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• pp.7-12
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• 2009

In this paper, shape optimization based on three-dimensional flow analysis has been performed for impeller design of centrifugal compressor. To evaluate the objective function of an isentropic efficiency, Reynolds-averaged Navier-Stokes equations are solved with SST (Shear Stress Transport) turbulence model. The governing equations are discretized by finite volume approximations. The optimization techniques based on the radial basis neural network method are used for the optimization. Latin hypercube sampling as design of experiments is used to generate thirty design points within design space. Sequential quadratic programming is used to search the optimal point based on the radial basis neural network model. Four geometrical variables concerning impeller shape are selected as design variables. The results show that the isentropic efficiency is enhanced effectively from the shape optimization by the radial basis neural network method.

• 정보저장시스템학회논문집
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• 제3권4호
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• pp.178-182
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• 2007

Topology optimization methods are classified into two methods such as the density method and the homogenization method. Those methods need to consider relationships between the material property and the density of each element in a design domain, the relaxation of the design space, etc. However, it is hard to apply on some cases due to the complexity to compose the design objective and its sensitivity analysis. In this paper, a modified topology optimization is proposed to assist designers who do not have mathematical or theoretical background of the topology optimization. In this study, optimal topology of structures can be achieved by the sequential design of experiment (DOE) and the sensitivity analysis. We conducted the DOE with an orthogonal array and the sensitivity analysis of design variables to determine sensitive variables used for connectivity between elements. The modified topology optimization method has advantages such as freedom from penalizing intermediate values and easy application with basic DOE concept.

• 한국항공우주학회지
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• 제33권12호
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• pp.26-32
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• 2005

공중발사 방식은 일반적인 지상발사와 비교해 볼 때 많은 장점을 지니고 있다. 그러나 공중발사 로켓의 형상은 모선에 장착 시 많은 제한이 따르기 때문에 여러 해석분야를 통합한 시스템 설계가 필요하다. 시스템 설계는 순차적 최적화와 MDF 기법을 이용하여 수행되었다. 해석 모듈은 임무분석, 단배분, 추진해석, 형상, 중량해석, 공력해석, 궤적해석을 포함한다. 두 가지 기법 중 MDF 기법을 이용하였을 때 더 좋은 결과를 도출하였다. 시스템 최적화 결과 총 중량 1244.91kg, 위성중량 7.5kg, 총 길이 6.36 m, 지름 0.60m을 지닌 초음속 공중발사 로켓이 설계되었다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.469-475
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• 2008

The design of a scramjet inlet is a process to search global optimization results among those factors influencing the geometry of scramjet in their ranges for some requirements. An optimization algorithm of hybrid genetic algorithm based on genetic algorithm and simplex algorithm was established for this purpose. With the sample provided by a uniform method, the compressive angles which also are wedge angles of the inlet were chosen as the inlet design variables, and the drag coefficient, total pressure recovery coefficient, pressure rising ratio and the combination of these three variables are designed specifically as different optimization objects. The contrasts of these four optimization results show that the hybrid genetic algorithm developed in this paper can capably implement the optimization process effectively for the inlet design and demonstrate some good adaptability.

• 한국정밀공학회지
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• 제21권10호
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• pp.137-146
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• 2004

This is the second of two companion papers concerned with the analysis and design of a pneumatic vibration isolation system. The properties of the system are clarified by observation of the transmissibility surface calculated by the models and algorithm developed in the first paper of this research. It Is shown that the nonlinear model proposed in this research is more closer to experimental results than the linear model that have been used in previous studies. The design optimization of the major design variables that affect the performance of the system is achieved by using the condition for attenuation, disturbance rejection and maximum damping in resonance peak. The design space search method is adopted for the optimization of the orifice area. The models, transmissibility calculation algorithms and design optimization techniques developed in this research are shown to be greatly helpful to the optimal design of the pneumatic vibration isolation system by experiment.

• 한국실내디자인학회논문집
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• 제20권5호
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• pp.68-77
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• 2011

In this research it is concentrated first of all on the attempts to reconstruct the historical context of the idea for the space design based on the natural construction and to re-appropriate il critically to the present context. Sequentially in the areas of philosophy, biology, neuroscience, and architecture it has been variously discussed on the problems about the synthesis of biology and techniques. In the context of the consilience of biology and technique Werner Nachtigall, who has intended to shed light on the morphological principles in the natural construction, founded the 'Bionik', which is different from the bionics or the biomechanics that are oriented to the imitation of natural forms. The space design that is on the basis of the Bionik treats organisms as a functional whole. Therefore the Bionik space design follows two kinds of principle such as the principle of analogy and the principle of optimization. After all the understanding of the consilience of nature and technique for Nachtigall and Bionik designers tends toward the explication of the complex process in which the human perceptions, the environment, and the phenomenal techniques are united together, and this complex process is associated with the space design based on the Bionik.

• Structural Engineering and Mechanics
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• 제55권6호
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• pp.1121-1137
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• 2015

High powered computers and engineering computer systems allow designers to routinely simulate complex physical phenomena. The presented work deals with the analysis of two finite element method optimization techniques (First Order Method-FOM and Subproblem Approximation Method-SAM) implemented in the individual Design Optimization module in the Ansys software to analyze the behavior of real problems. A design optimization is a difficult mathematical process, intended to find the minimum or maximum of an objective function, which is mostly based on iterative procedure. Using optimization techniques in engineering designs requires detailed knowledge of the analyzed problem but also an ability to select the appropriate optimization method. The methods embedded in advanced computer software are based on different optimization techniques and their efficiency is significantly influenced by the specific character of a problem. The efficiency, robustness and accuracy of the methods are studied through strictly convex two-dimensional optimization problem, which is represented by volume minimization of two bars' plane frame structure subjected to maximal vertical displacement limit. Advantages and disadvantages of the methods are described and some practical tips provided which could be beneficial in any efficient engineering design by using an optimization method.

• 한국항공우주학회지
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• 제31권5호
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• pp.25-36
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• 2003

항공기 설계는 설계 전 분야에 걸친 설계 요소들을 모두 고려한 통합적 환경에서 이루어 져야 한다. 이를 위해 각 분야간의 데이터 공유 및 일관성, 무결성, 최신성 등이 요구되며 이러한 요구사항을 만족할 수 있는 효율적인 데이터베이스의 설계가 필요하다. 데이터베이스의 설계 순기는 저장되고 관리해야 할 데이터의 분석, E-R Diagram의 작성, 테이블 사상으로 이루어진다. 본 연구에서는 상용의 Oracle 8i 데이터베이스 관리시스템을 이용하여 데이터베이스를 설계, 구축하였다. MDF(MultiDisplinary Feasible), IDF(Individual Discipline Feasible), CO(Collaborative Optimization) 등의 MDO(Multidisciplinary Design Optimization) 기법을 적용할 수 있는 데이터베이스의 설계과정을 정립하고, 간단한 수치예제와 무인전투기 최적화 설계 등의 예제를 통하여 통합환경에서의 데이터베이스 설계 방법의 타당성을 검증하였다.

• Smart Structures and Systems
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• 제20권5호
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• pp.607-618
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• 2017

In this research, a newly developed nature-inspired optimization method, the Lion Pride Optimization algorithm (LPOA), is utilized for optimal design of composite steel box girder bridges. A composite box girder bridge is one of the common types of bridges used for medium spans due to their economic, aesthetic, and structural benefits. The aim of the present optimization procedure is to provide a feasible set of design variables in order to minimize the weight of the steel trapezoidal box girders. The solution space is delimited by different types of design constraints specified by the American Association of State Highway and Transportation Officials. Additionally, the optimal solution obtained by LPOA is compared to the results of other well-established meta-heuristic algorithms, namely Gray Wolf Optimization (GWO), Ant Lion Optimizer (ALO) and the results of former researches. By this comparison the capability of the LPOA in optimal design of composite steel box girder bridges is demonstrated.