• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.1
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• pp.50-55
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• 2011

In this study, simultaneous aero-structural design was performed for HALE aircraft wing. The span and the shape of main spar were considered as design variables. To maximize aerodynamic performance and to minimize weight, multi-objective optimization was used. Nonlinear static aeroelastic analysis was performed to compute large deflection of wing. Design of experiment and response surface method were used to reduce computation cost in the design process. Also, aerodynamic performances of deformed wing and rigid wing were compared.

• Journal of the Korean Magnetics Society
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• v.20 no.6
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• pp.239-243
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• 2010

This paper deals with the optimum design criteria for the premium efficiency of 250 kW traction induction motor, using response surface methodology (RSM) and finite element method (FEM). The focus of this paper is found firstly a design solution through the comparison of torque according to rotor bar shape, rotor dimensions variations. And secondly a mixed resolution with central composite design (CCD) is introduced and analysis of variance (ANOVA) is conducted to determine the significance of the fitted regression model. The proposed procedure allows to be optimized the rotor copper bar shape, rotor slot, rotor dimensions starting from an existing motor or a preliminary design.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.23 no.3
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• pp.275-281
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• 2010

In this paper, the design optimization of structures with stress constraints is performed using isogeometric shape optimization method. The stress constraints have an important role in design optimization problems since stress concentration could result in structural failure. To represent exact geometry in analysis, the isogeometric analysis method uses the same basis functions as used in the CAD geometry. The geometrically exact model can be used in both stress and design sensitivity analyses so that it can yield more precise optimal design than finite element one. Through numerical examples, the isogeometric approach turns out to be effective in shape optimization problems under stress constraints.

• Proceedings of the KIEE Conference
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• 2009.07a
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• pp.849_850
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• 2009

본 논문에서는 mass heating에 적용되는 고주파 유도가열 코일의 형상설계에 대한 내용을 기술하였다. 고주파 전류가 흐르는 가운데, workpiece가 가장 고른 열분포 특성을 가질 수 있도록 가열시킬 수 있는 코일의 형태를 결정하는 과정을 나타내고 있다. 이를 설명하기 위해 유한요소법을 이용하여 와전류와 열전도 등의 결과를 데이터화하고 각 결과들의 순환적 재입력으로 수치들의 변화를 시각적으로 나타내어 제안된 코일 형상에 대한 효율성을 입증한다. 연구의 과정은 3차원 유한 요소 프로그램인 ANSYS로 이루어진다.

• Proceedings of the Acoustical Society of Korea Conference
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• 1998.06e
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• pp.255-258
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• 1998

본 연구에서는 해석적인 방법을 사용하여 고감도 멘드릴형 광섬유 음향센서를 설계하고자 하였다. 음향감지부의 형상으로 실린더형 멘드릴 및 중공원통형 층상복합체 멘드릴을 선정하고, 음향감도에 대한 이론식을 유도하여 재질변수 및 형상변수 등에 따른 음향감도를 해석하였다. 또한 해석적 방법 및 유한요소법을 이용한 분석결과를 비교하여 해석적인 방법의 타당성을 검증하였다. 그 결과, 멘드릴의 외경변화에 의한 감도변화 경향만이 다소 차이를 보이고 있으나 그 이외의 재질변수 및 형상변수에 의한 음향감도 변화 경향은 서로 잘 일치하는 것으로 분석되었다.

• Transactions of the Korean Society of Automotive Engineers
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• v.2 no.4
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• pp.59-71
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• 1994

A multi-polynomial method is proposed to synthesize DRRD cam profiles. A cam lift duration s divided into 10 sections, each of them is expressed by a polynomial equation. 12 design variables are extracted from the cam profile displacement, velocity, and acceleration curves. Because all the design variables have physical meanings which are familiar to most cam designers, it is easy to imagine a profile shape from the design variables. The design envelope of the method is wide enough to be used in DRRD automotive cam designs. Polydyne cams, widely used in automotive engines, are included into the envelope. Unlike Polydyne cams, the method provides capability of wide velocity factor variations, which gives much flexibility in flat-faced tappet design. Area factor of profiles designed by the method can be increased 5-10% compared to those of Polydyne cams without increasing acceleration factor. The method is especially useful for cam profile optimizations.

• Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
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• 1993.12a
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• pp.39-50
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• 1993

최근 회전계의 고속화, 소형화 및 정숙운전에 대한 요구가 엄격해짐에 따라 볼베어링을 저어널베어링으로 대체하는 흐름이 증가하고 있으나, 저어널베어링의 기본 구조상 운전시 여러 종류의 진동모드가 발생되며 이에 따라 엄밀한 설계가 요구된다. 이러한 요구에 따라 본 연구에서는 불안정성을 억제할 수 있는 것으로 알려진 빗살무늬 저어널베어링을 대상으로 하여 보다 정확한 설계를 위한 수치해석 프로그램을 개발하였다. 빗살무늬저어널베어링의 해석법으로는 간극의 비선형성을 단순화 시키기 위하여 무한홈을 가정한 협곡이론을 시초로 하여 최근에는 컴류터 계산속도의 발달로 실제 형상에 대해 해석한 직접계산법 등이 알려져 있다. 직접계산법은 협곡이론에 의한 계산법에 비해 많은 시간이 걸리는 단점이 있으나, 베어링이 소형화되어 실제 많은 홈을 가공하기 힘들거나 홈이 원호형으로서 직각홈으로 가정하기가 곤란한 요소에서는 협곡이론을 적용하는데 무리가 있을 것으로 사료된다. 따라서 본 연구에서는 직접계산법을 채택하여 소형 베어링 모델에 대한 부하특성을 수치해석하고, 이를 협곡이론과의 비교를 통하여 그 차이점을 검토하였다. 이를 위해 압축성을 고려한 레이놀즈 방정식에 대한 베어링 주위의 압력분포를 계산하는 프로그램을 제작하였으며, 주어진 설계조건하에서 빗살무늬 형상을 결정하는 피라미터들의 최적값을 산출하고, 아울러 플레인저어널베어링과의 비교를 통하여 설계조건에 따른 빗살무늬저어널베어링의 기존 불베어리의 대체 가능성을 평가하였다.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.33 no.8
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• pp.726-732
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• 2009

In many industries, the linear motor replaces the existing framework for linear transportation. Similar to other conventional motors, it is important to minimize the ripple of thrust and to maximize the thrust force of the linear motor. Because the two objectives are associated to each other, the multi-objective design process is necessary considering all objectives. This paper intends to optimize geometric parameters of the linear motor with two design objectives using design of experiments and sequential response surface method.

• 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 Society of Naval Architects of Korea
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• v.36 no.2
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• pp.9-21
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• 1999

The waterjet is very widely used today in propulsion system of high speed vessel but manufacturer is limited because of an efficiency and a difficulty of a manufacture on the inlet configuration of the waterjet. The importancy in designing the inlet configuration of the waterjet lies on the minimization of the cavitation which is largely affecting the efficiency. In this paper, the configuration analysis is carried out to find a optimum shape which is minimizing the cavitation using a two dimensional potential-based panel method with an inlet configuration of a flush type. Also, it is developed a direct design method finding an inlet configuration by a given pressure distributions. The numerically obtained optimum shape using this configuration analysis method show a good agreement compared to the Kashiwadani's results. It is carried out a direct design method over a lip and a ramp of an inlet configuration wish pressure distributions obtained a result of the configuration analysis and the results show a good agreement compared to original configuration.