• 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.34 no.9
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• pp.1-10
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• 2006

An optimization study on a small turbopump impeller operating at the low specific speed is conducted to obtain high output head at the impeller exit. Its specific speed in SI unit (RPM, m3/sec, m) is 4.0, and the outer diameter is 56mm. On the optimization, the outer diameter of the impeller is maintained constant to restrict the pump size, and an objective function of pressure head is maximized with eight design variables, which are related with designing an impeller shape. The response surface method is used to the optimization scheme, and the commercial code CFX-10 is applied for numerical analysis. The pressure head of the objective function obtained with an optimized impeller is increased by 9.7% compared with that obtained on an impeller designed with typically recommended design parameters. This increment is caused by reducing the recirculation region within the impeller passage.

• Journal of Korea Water Resources Association
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• v.38 no.12 s.161
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• pp.1021-1028
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• 2005

This study purpose to develop simulation model of optimal design condition of urban storm sewer system considering risk. Urban Storm Sewer Optimal Design Model(USSOD) can compute pipe capacity, pipe slope, crown elevation, excavation depth, risk and return cost in the condition of design discharge. Rational formula is adopted for design discharge and Manning's formula is used for pipe capacity. Discrete differential dynamic programming(DDDP) technique which is a kind of dynamic programming(DP) is used for optimization and first order second moment approximation method and uncertainty analysis is also for developing model. USSOD is applied to hypothetical drainage basin to test and verify, which resulted economical and efficient design in urban drainage sewer system.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2001.11a
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• pp.360-364
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• 2001

본 논문에서는 최근의 진화적 구조최적화(ESO) 전략을 회전축의 형상최적화에 적용하였으며, 각 계산 스텝마다 단위 유한요소의 크기를 변경함으로써 기존의 방법보다 빠르고 정확한 최적형상에 수렴하는 새로운 방법을 제시하였다. 축요소의 직경을 시스템 설계변수로 하였으며, 축중량의 감소, 공진배율(Q-factor)의 감소 및 충분한 위험속도의 분리여유를 갖도록 목적함수를 설정하였다. 불평형응답 및 굽힙응력의 구속조건을 부가하였으며, 목적함수에 대한 설계변수의 감도해석을 수행하였다. 전동기축계에 대한 적용 결과로부터 주파수와 동적 구속조건하의 로터베어링 시스템에 대한 축 형상 최적화에 ESO법이 효과적으로 이용될 수 있음을 확인하였다.

• Proceedings of the Korean Information Science Society Conference
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• 2006.06a
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• pp.79-81
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• 2006

커널(Kernel)을 이용한 분류 방법은 넓은 마진(large margin) 분류기로서 SVM(Support Vector Machine)을 주로 사용하게 된다 하지만, 이 방법은 라그랑제 파라미터(Lagrange Parameter)의 최적화 과정을 포함함으로써 학습 과정을 쉽지 않게 만든다. 이 최적화 과정은 특히 DNA computing과 같은 단순한 과정의 설계를 통해 결과를 얻어야 하는 새로운 계산 모델에 커널을 적용하고자 했을 경우 큰 장벽이 된다. 본 논문에서는 넓은 마진을 목표로 하는 최적화 과정이 아닌 다른 라벨(label)의 데이터간의 경계 파악을 위한 간단한 커널 갱신 방법의 도입을 통해 분류기를 설계한다. 이 방법을 가우시안 커널에 적용시켜 본 결과, 반복을 통해 데이터의 구조를 찾아갈 수 있는 특성을 보여주며, 결국 넓은 마진의 최적화된 파라미터를 찾게 됨을 보여준다. 본 논문에서는 이 최적화 방법을 DNA 분자를 이용한 커널 생성 모델인 DNA 커널에 적용시켰을 때 잘 알려진 AML/ALL 데이터를 잘 분류해 냄을 보여준다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.5
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• pp.18-27
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• 2005

Airfoils with improved longitudinal static stability were designed for a WIG craft through aerodynamic design optimization. The response surface method is coupled with NURBS-based shape functions and Navier-Stokes flow analysis. The procedure runs in the network-distributed design framework of commercial-code based automated design capability to enhance computational efficiency and robustness.Lift maximization design maintaining similar static margin to a DHMTU airfoil successfully produced a new airfoil shape characterized by pronounced front-loading and the well-known reflexed aft-camber line. Another airfoil design of lower variation in pitching moment during take-off showed weakened front-loaded characteristics and hence decreased lift slightly. Investigations using the present design methodology on an existing optimization result based on potential flow analysis and NACA-type geometry generation demonstrated significance of carrying various geometry generations and more realistic flow analysis with optimization.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.22 no.5
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• pp.501-507
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• 2009

By using topology and shape optimization, a theoretically optimum FRP deck was proposed. Firstly, a topologically optimal shape, truss-like structure without hinges, was found. A truss-shape frame is the most ideal structure when subjected to a concentrated force at the center of simply supported beam. An armature was found at the point joining horizontal chord and diagonal chord, which was used as a new design variable. Secondly, optimum value of each variable was decided through shape optimization using genetic algorithm. To compare it with existing commercial FRP decks, shape optimization was performed by fixing the height of FRP decks. To verify the performance of the FRP deck proposed in this study, a finite element analysis was performed. As a result, it satisfies serviceability and safety guide lines of FRP decks.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.38 no.4
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• pp.363-370
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• 2014

A new NURBS-based shape optimization method is proposed. Most shape optimization studies consider only control point positions as design variables. Some shape optimization processes present problems with mesh quality and convergence when control points are constrained to a limited space. If the weights of the control points are regarded as additional design variables, it should be possible to attain a better degree of shape control. In this study, positions and weights of NURBS control points are used as design variables, and a shape optimization algorithm incorporates position optimization and weight optimization steps. This method is applied to shape optimization benchmarking problems to verify its advantages.

• Korean Journal of Optics and Photonics
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• v.8 no.2
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• pp.88-94
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• 1997

Photographic lenses and an aspheric optical pickup-lens are designed by using damped least-squares(DLS) method. We start optimization with arbitrary initial damping factor. To improve the rate of convergence and the stability in optimization, we apply the special procedure that estimates numerical adequacy of derivative increments of variables to the DLS method. When the initial damping factor is almost equal to the median of series of eigenvalues, the convergence and the stability of the method significantly are improved. Optimized lenses have the performance of each target.

• Proceeding of EDISON Challenge
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• 2016.03a
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• pp.541-547
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• 2016

본 연구에서는 Slotted flap을 장착한 WIG선(Wing In Ground effect ship)에서 발생하는 진동을 최소화하기 위해 WIG선의 공력특성을 수치적으로 분석하고 그에 따라 플랩 형상에 대하여 최적화를 진행하였다. 주 익형에 대한 형상은 NACA 4412로 고정한 상태에서 플랩의 각도와 x, y좌표를 설계변수로 설정하였으며, 그에 따라 설정한 평균 $C_L$값을 유지하면서 진동의 진폭 크기가 작아지도록 제한 조건 및 목적 함수를 설정하였다. 최적화된 익형에서 플랩과 주 익형 사이에서 분출되는 유체는 코안다 효과의 영향을 받아 플랩 윗부분을 타고 흐른다. 이로 인해 진동에 결정적인 영향을 미치는 박리영역이 억제되었으며, 진동이 최소화 되었다. 결론적으로 플랩의 최적화를 통하여 기본 설계 익형에서 89%의 진동이 저감되는 것과 동시에 Lift/Drag 96.2로 기본 설계 익형에 비해 4.1배 향상되었다.