• 한국CDE학회논문집
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• 제3권3호
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• pp.183-191
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• 1998

There are many available algorithms based on the different approaches to solve the intersection problems between two curves. Among them, the implicitization method is frequently used since it computes precise solutions fast and is robust in lower degrees. However, once the degrees of curves to be intersected are higher than cubics, its computation time increases rapidly and the numerical stability gets worse. From this observation, it is natural to transform the original problem into a set of easier ones. Therefore, curves are subdivided appropriately depending on their geometric behavior and approximated by a set of rational quadratic Bezier cures. Then, the implicitization method is applied to compute the intersections between approximated ones. Since the solutions of the implicitization method are intersections between approximated curves, a numerical process such as Newton-Raphson iteration should be employed to find true intersection points. As the seeds of numerical process are close to a true solution through the mix-and-match process, the experimental results illustrates that the proposed algorithm is superior to other algorithms.

• 대한기계학회논문집B
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• 제29권10호
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• pp.1163-1171
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• 2005

The shape optimization of an airfoil has been performed for an incompressible viscous flow. In this study, Pareto frontier sets, which are global and non-dominated solutions, can be obtained without various weighting factors by using the multi-objective genetic algorithm An NACA0012 airfoil is considered as a baseline model, and the profile of the airfoil is parameterized and rebuilt with four Bezier curves. Two curves, front leading to maximum thickness, are composed of five control points and the rest, from maximum thickness to tailing edge, are composed of four control points. There are eighteen design variables and two objective functions such as the lift and drag coefficients. A generation is made up of forty-five individuals. After fifteenth evolutions, the Pareto individuals of twenty can be achieved. One Pareto, which is the best of the . reduction of the drag furce, improves its drag to $13\%$ and lift-drag ratio to $2\%$. Another Pareto, however, which is focused on increasing the lift force, can improve its lift force to $61\%$, while sustaining its drag force, compared to those of the baseline model.

• 한국항공우주학회지
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• 제39권5호
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• pp.424-432
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• 2011

원심압축기 임펠러의 최적화연구를 수행하기 위하여 임펠러의 형상변수와 설계변수에 관한 연구를 수행하였다. 최적화된 결과로부터 성능향상이 달성되었는지를 평가하기 위하여 기존에 실험되어진 임펠러를 선택하였으며, 이 임펠러에서 최적화를 위한 설계변수를 선정하였다. 임펠러 유로에서 허브와 쉬라우드에서의 형상은 베지어곡선으로 재설계되었다. 또한 임펠러 허브와 팁에서의 블레이드 캠버선도 베지어곡선으로 표현하였다. 각각의 형상곡선은 6-8개의 조정점으로 충분히 일치하는 곡선을 얻게 되었으며, 이 중 형상의 변화에 큰 영향을 미치는 조정점을 선택하여 8개의 설계변수로 최적화가 가능함을 보여주었다. 따라서 기존에 사용되고 있는 원심압축기 임펠러의 점 데이터를 활용하여 최적화 형상을 위한 연구가 진행될 수 있음을 보여주었다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2001년도 춘계 학술대회논문집
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• pp.72-77
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• 2001

The computational efficiency of an shape optimization procedure is highly dependent upon the proper selection of shape representation methods and design variables. In this study, shape functions, Bezier and NURBS(non-uniform rational B-splines) curves are selected as configuration generation methods and their efficiencies on the nose shape design of high-speed air vehicles, are compared. The effects of the number of control points, weighting factors and the optimization methods when utilizing the NURBS curves, are investigated. By implementing Bezier and NURBS curves, shapes having lower drag than the optimization case utilizing the shape functions, were obtained, hence it was demonstrated that these curves have better capability in representing the configuration. Efforts will be given to improve the convergence behavior when utilizing the NURBS, hence to reduce the number of Navier-Stokes analysis calculations.

• 한국CDE학회논문집
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• 제4권4호
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• pp.350-354
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• 1999

The problem of the computation of derivatives arises in various applications of rational Bezier curves. These applications sometimes require the computation of derivative on numerous points. Therefore, many researches have dealt with the representation for the computation of derivatives with the small computation error. This paper compares the performances of the representations for the derivative of rational Bezier curves in the performances. The performance is measured as computation requirements at the pre-processing stage and at the computation stage based on the theoretical derivation of computational bound as well as the experimental verification. Based on this measurement, this paper discusses which representation is preferable in different situations.

• 한국유체기계학회 논문집
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• 제17권4호
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• pp.19-29
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• 2014

In addition to the development of micro hydro turbine, the challenge in micro hydro turbine design as sustainable hydro devices is focused on the optimization of turbine runner blade which have decisive effect on the turbine performance to reach higher efficiency. A multi-objective optimization method to optimize the performance of runner blade of propeller turbine for micro turbine has been studied. For the initial design of planar blade cascade, singularity distribution method and the combination of the Bezier curve parametric technology is used. A non-dominated sorting genetic algorithm II(NSGA II) is developed based on the multi-objective optimization design method. The comparision with model test show that the blade charachteristics is optimized by NSGA-II has a good efficiency and load distribution. From model test and scale up calculation, the maximum prototype efficiency of the runner blade reaches as high as 90.87%.

• 수산해양기술연구
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• 제39권4호
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• pp.298-304
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• 2003

In this paper a free-form hull design program and performance prediction program for planing boat is introduced. This program enables the designer to do complex geometric hull shape design on a personal computer and accurately to predict power requirements for a given loading and velocity. For a free form design, Bezier curve model is adopted as a basic representation tool of curves and surfaces, and this program has versatile functions to do fairing jobs with a convenient graphical user interface. After creating a hull form the geometric data is provided in a manner compatible with a variety of analysis tools including 'Motion Analysis(by Zarnick)' for prediction of motion characteristics in regular waves, 'Running Attitude (by Savitsky)' for prediction of the running attitude and required power.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2002년도 춘계 학술대회논문집
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• pp.94-101
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• 2002

The steam turbine rotor blade is designed using the Turbine Rotor Design Package developed by the authors. It can quickly accomplish blade shape design in the power plant industry. The quasi-3d code is employed for analysis of passage flow in the blade sections. Iterative change of each blade shape is made by moving position of control points in the Bezier curve under GUI(graphic user interface) environment. The full 3-D blade shape is obtained by stacking of the section blades.

• 한국정보처리학회논문지
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• 제7권2호
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• pp.558-568
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• 2000

본 논문에서는 등고선 지도의 3차원 정보를 이용하여 수치지형도 자동 생성방법을 제안한다. 제안된 방법은 등고선의 세선화와 라벨링을 통해 등고성분과 비 등고성분을 정확히 구분하였으며, Bezier 곡선을 사용하여 끊어진 등고선을 부드럽게 연결한다. 마지막으로 등고선으로부터 얻어진 고도 데이터를 사용하여 3차원 데이터를 생성한다. 제안된 방법은 수치 지형도를 만들기 위해 소요되는 막대한 양의 인력과 시간, 비용을 절약할 수 있다.

• 한국통신학회논문지
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• 제39C권11호
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• pp.1011-1022
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• 2014

현 공중노드의 무선네트워크 환경은 지상중계소 중심으로 구축되어 있는 반면에 한반도 환경여건은 전국토의 약 70% 정도가 산악지역으로 이루어져 있어 전파 음영지역(shadow zone)이 다수 존재하는 실정이다. 항공기가 중 저고도 임무 수행 도중 음영지역에 진입되어 통신 링크가 단절되지 않도록 효율적인 대응책 마련이 요구되고 있다. 따라서 본 논문에서는 Bezier Curve를 이용한 항공기 위치예측 및 음영지역 진입제어 방법을 제안한다. 제안된 방법은 항공기 이동경로 예측이 가능하여 음영지역 진입여부를 사전에 진단할 수 있으며 음영지역 진입 이전에 상황을 경고 전파하고 위험지역 이탈조치를 취하는 등 효율적인 제어가 가능하였다. 모의실험결과 제안된 방법은 항공기 위치예측 및 음영지역 진단이 용이하고 위험지역 진입 이전에 이탈조치 함으로써 항공작전 시 끊김 없는(seamless) 통신 지원이 가능한 것으로 나타나고 있다.