• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2004년도 추계 학술대회논문집
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• pp.173-176
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• 2004

In this study, the multidisciplinary aerodynamic-structural optimal design is carried out for the supersonic fighter wing. Through the aeroelastic analyses of the various candidate wings, the aerodynamic and structural performances are calculated such as the lift coefficient, the drag coefficient and the deformation of the wing. In general, the supersonic fighter is maneuvered under the various flight conditions and those conditions must be considered all together during the design process. The multi-point design, therefore, is deemed essential. For this purpose, supersonic dash, long cruise range and high angle of attack maneuver are selected as representative design points. Based on the calculated performances of the candidate wings, the response surfaces for the objectives and constraints are generated and the supersonic fighter wing is designed for better aerodynamic performances and less weights than the baseline. At each design point, the single-point design is performed to obtain better performances. Finally, the multi-point design is performed to improve the aerodynamic and structural performances for all design points. The optimization results of the multi-point design are compared with those of the single-point designs and analyzed in detail.

• 한국군사과학기술학회지
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• 제1권1호
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• pp.145-153
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• 1998

천음속 날개꼴의 수치최적화 설계에 있어서, 하나의 흐름조건에 의해 설계된 날개꼴의 공력특성은 다른 흐름조건에서 나쁜 특성을 나타낼 수 있다. 따라서, 실용적인 날개꼴의 설계를 위해서 multi-point 수치최적화 설계능력은 필수적인 요소이다. 본 논문에서는 Navier-Stokes 방정식 흐름해석 코드와 feasible direction 최적화 알고리즘을 이용하여 two-point 수치최적화 설계를 수행하였으며, 가중치가 수치최적화 설계에 주는 영향을 분석하고 비교하였다. 그 결과로서 two-point수치최적화 설계된 날개꼴이 두 흐름조건의 주변영역에서 동시에 요구 공력특성을 만족시키며, 가중치가 큰 방향으로 최적화 설계됨을 확인하였다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2003년도 The Fifth Asian Computational Fluid Dynamics Conference
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• pp.240-242
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• 2003

A method for performing two-dimensional lift-constraint drag minimization in inviscid compressible flows on unstructured meshes is developed. Sensitivities of objective function with respect to the design variables are efficiently obtained by using a continuous adjoint method. In addition, parallel algorithm is used in multi-point design optimization to enhance the computational efficiency. The characteristics of single-point and multi-point optimization are examined, and the comparison of these two method is presented.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2005년도 추계 학술대회논문집
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• pp.99-104
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• 2005

For the efficient reliability analysis, Bi-direction two-point approximation(BTPA) method is developed which solves shortcomings of conventional two-point approximation(TPA) methods that generate an approximate surface with low accuracy or sometimes do an unstable approximate surface. The conventional reliability based design optimization(RBDO) methods require high computational cost compared with the deterministic design optimization(DO) methods. To overcome the computational inefficiency of RBDO, the approximate reliability analysis approaches on the TPA surface are proposed. Using these FORM and SORM analysis strategies, multi-point aerodynamic-structure interacted shape design optimizations with uncertainty are performed very efficiently.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2006년도 PARALLEL CFD 2006
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• pp.259-262
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• 2006

• 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.

• 한국실내디자인학회논문집
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• 제13권5호
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• pp.56-65
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• 2004

This study divides the expression techniques of Zaha Hadid into various types who has manipulated her targeted drawings as her unique design tools in the process of architectural design, analyzes them in terms of the vanishing point, visual point for observation and object of observation and attempts to figure out how the multi-visual expression is applied in the conception of form and space and method of observation. By doing so, this study will suggest the characteristics of the expression techniques using multi-visual. Through the above study, the utilization and characteristics of multi-visual expression of the architecture design process of Zaha Hadid are summarized as follows. Firstly, Zaha Hadid utilizes the strained multi-visual perspective technique which can look out over the interaction between masses simultaneously at multi-angles by changing a perspective drawing of vanishing point 1, 2, and 3. Secondly, it utilizes a landscape perspective technique and embodies an Idea of landscape's spatial arrangement through it as the means to search a dynamic relation of architecture, city, land, and space. Thirdly, there is a projected expression using X-ray perspective technique to make the relations between inside and outside of building to three-dimension volume. Zaha Hadid has used the expression techniques using multi-visual by utilizing various points and has developed and used them as her creative tools for idea. By means of escaping from the expression techniques of simple revival, she has used a new expression technique that can represent recognized space. In the past, the content could change the expression techniques in architecture; however, the liberation of architectural expression techniques can change the content in modern times when require new attempts.

• International Journal of Aeronautical and Space Sciences
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• 제8권1호
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• pp.66-78
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• 2007

A multi-point aerodynamic shape optimization technique has been developed for helicopter rotor blades in hover based on a continuous adjoint method on unstructured meshes. The Euler flow solver and the continuous adjoint sensitivity analysis were formulated on the rotating frame of reference. The 'objective function and the sensitivity were obtained as a weighted sum of the values at each design point. The blade section contour was modified by using the Hicks-Henne shape functions. The mesh movement due to the blade geometry change was achieved by using a spring analogy. In order to handle the repeated evaluation of the design cycle efficiently, the flow and adjoint solvers were parallelized based on a domain decomposition strategy. A solution-adaptive mesh refinement technique was adopted for the accurate capturing of the wake. Applications were made to the aerodynamic shape optimization of the Caradonna-Tung rotor blades and the UH-60 rotor blades in hover.

• 품질경영학회지
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• 제14권1호
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• pp.26-32
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• 1986

A class of multi-factor designs for estimating the slope of second order response surfaces is presented. For multi-factor designs the variance of the estimated slope at a point is a function of the direction of measurement of the slope and the design. If we average the variance over all possible directions, the averaged variance is only a function of the point and the design. By choice of design, it is possible to make this variance constant for all points equidistant from the design origin. This property is called "slope-rotatability over all directions", and the necessary and sufficient conditions for a design to have this property are given and proved. The class of design with this property is mainly discussed.

• 대한조선학회논문집
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• 제45권4호
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• pp.462-467
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• 2008

In this paper, we investigated the design method of mooring system in ultra deep sea and carried out the conceptual design for offshore West Africa oil field in ultra deep sea of 3000 meters. Recently, it was feasible to design and install the offshore floating structures in deep sea of up to 2000 meters. Due to the simplicity, two-point mooring design is fully utilized. Force-excursion curves are throughly examined to find out the feasibility of various combinations of mooring lines. Free length and pretension effects are discussed. It is found that composite materials including synthetic fiber rope may be good solution for ultra deep sea mooring design.