• Journal of Mechanical Science and Technology
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• 제15권5호
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• pp.671-680
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• 2001

Boundary condition is one of the major factors to influence the numerical stability and solution accuracy in numerical analysis. One of the most important physical boundary conditions in the flowfield analysis is the wall boundary condition imposed on the body surface. To solve a two-dimensional Euler equation, totally four numerical wall boundary conditions should be prescribed. Two of them are supplied by the flow tangency condition. The other two conditions, therefore, should be prepared additionally in a suitable way. In this paper, four different sets of wall boundary conditions are proposed and then applied to solve high-speed flowfields around a quarter circle geometry. A two-dimensional compressible Euler solver is prepared based on the finite volume method. This solver hires three different upwind schemes; Steger-Warmings flux vector splitting, Roes flux difference splitting, and Lious advection upstream splitting method. It is found that the way to specify the additional numerical wall boundary conditions strongly affects the overall stability and accuracy of the upwind schemes in high-speed flow calculation. The optimal wall boundary conditions should be also chosen very carefully depending on the numerical schemes used to solve the problem.

• 한국지능시스템학회논문지
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• 제21권6호
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• pp.673-678
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• 2011

본 논문에서는 물체의이동이나 정보 탐색을위하여 유용하게 사용될 수 있는 4족 로봇의 정지 밸런스를 분석하고자 한다. 이 목적을위하여, 일반적인 4족 로봇의유용한 모델을 제시하고, 정지 안정성을 고려한 경계 조건을 제안한다. 착지된 상태에서 4족 로봇의 정지 밸런스를 분석하기 위하여 다양한 자유 운동을 고려하며, 시뮬레이션을 통하여 밸런스 여유를 고찰한다. 이러한 분석은 4족 로봇 보행의 효과적인 밸런싱 제어를 위하여 유용하게 활용될 수 있을것이다.

• 대한수학회지
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• 제58권5호
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• pp.1109-1129
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• 2021

This paper considers an anisotropic polytropic infiltration equation with a source term $$u_t={\sum\limits_{i=1}^{N}}{\frac{{\partial}}{{\partial}x_i}}\(a_1(x){\mid}u{\mid}^{{\alpha}_i}{\mid}u_{x_i}{\mid}^{p_i-2}u_{x_i}\)+f(x,t,u)$$, where p_i > 1, α_i > 0, a_i(x) ≥ 0. The existence of weak solution is proved by parabolically regularized method. Based on local integrability $u_{x_i}{\in}W_{loc}^{1,p_i}(\Omega)$, the stability of weak solutions is proved without boundary value condition by the weak characteristic function method. One of the essential characteristics of an anisotropic equation different from an isotropic equation is found originally.

• 대한수학회논문집
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• 제30권3호
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• pp.297-311
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• 2015

We present a robust and accurate boundary condition for pricing financial options that is a hybrid combination of the payoff-consistent extrapolation and the Dirichlet boundary conditions. The payoff-consistent extrapolation is an extrapolation which is based on the payoff profile. We apply the new hybrid boundary condition to the multi-dimensional Black-Scholes equations with a high correlation. Correlation terms in mixed derivatives make it more difficult to get stable numerical solutions. However, the proposed new boundary treatments guarantee the stability of the numerical solution with high correlation. To verify the excellence of the new boundary condition, we have several numerical tests such as higher dimensional problem and exotic option with nonlinear payoff. The numerical results demonstrate the robustness and accuracy of the proposed numerical scheme.

• Steel and Composite Structures
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• 제11권5호
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• pp.359-374
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• 2011

In this paper, the influence of fibre orientation and aspect ratio on stability analysis of simply supported skew plates subjected to in plane loading is studied by using a four noded hybrid plate finite element. The formulation of the element is based on Hellinger-Reissner variational principle. The element is developed by combining a hybrid plane stress element and a hybrid plate element. Some numerical problems are solved and the effects of skew angle, aspect ratio, fibre orientation and loading type on the critical buckling loads are highlighted.

• International Journal of Aeronautical and Space Sciences
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• 제13권1호
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• pp.43-57
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• 2012

In a modern aircraft, there are many variations in its mass, stiffness, and aerodynamic characteristics. Recently, an analytical approach was proposed, and this approach uses the idea of uncertainty to find out the most critical flight flutter boundary due to the variations in such aerodynamic characteristics. An analytical method that has been suggested to predict robust stability is the mu method. We previously analyzed the robust flutter boundary by using the mu method, and in that study, aerodynamic variations in the Mach number, atmospheric density, and flight speed were taken into consideration. The authors' previous attempt and the results are currently quoted as varying Mach number mu analysis. In the author's previous method, when the initial flight conditions were located far from the nominal flutter boundary, conservative predictions were obtained. However, relationships among those aerodynamic parameters were not applied. Thus, the varying Mach number mu analysis results required validation. Using an optimization approach, the varying Mach number mu analysis was found out to be capable of capturing a reasonable robust flutter boundary, i.e., with a low percentage difference from boundaries that were obtained by optimization. Regarding the optimization approach, a discrete nominal flutter boundary is to be obtained in advance, and based on that boundary, an interpolated function was established. Thus, the optimization approach required more computational effort for a larger number of uncertainty variables. And, this produced results similar to those from the mu method which had lower computational complexity. Thus, during the estimation of robust aeroelastic stability, the mu method was regarded as more efficient than the optimization method was. The mu method predicts reasonable results when an initial condition is located near the nominal flutter boundary, but it does not consider the relationships that are among the aerodynamic parameters, and its predictions are not very accurate when the initial condition is located far from the nominal flutter boundary. In order to provide predictions that are more accurate, the relationships among the uncertainties should also be included in the mu method.

• 한국화재소방학회논문지
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• 제29권4호
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• pp.33-38
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• 2015

강구조 건축물의 바닥하중은 보부재를 통하여 기둥부재로 전달되며, 보부재는 양단 고정단 또는 단순보 조건으로 구성된다. 양단 고정단 강재보와 한단 힌지 그리고 타단 회전단의 단순보는 경계조건의 차이에 따라 전달되는 최대하중과 처짐 등 구조적 내력성능이 상이하나, 화재 시 내화성능 평가는 단순보의 경계조건으로 평가되고 있다. 따라서 본 논문에서는 강재보의 경계조건에 따른 내력적 성능의 차이를 확인하기 위하여 일반 구조용 강재(SS 400)의 고온특성을 적용한 열전달해석 및 열응력해석을 수행하였으며, 그 결과 동일한 보부재의 길이와 단면 조건하에서 부정정 구조물인 고정단 경계조건이 정정 단순보 경계조건에 비해서 내력과 처짐이 건전한 것으로 나타났다. 따라서 강재 보의 내화시험 시 단순보로 시험하는 것이 안전측으로 판단되었다.

• Journal of the Korean Society for Industrial and Applied Mathematics
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• 제23권3호
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• pp.179-202
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• 2019

This paper presents second derivative generalized extended backward differentiation formulas (SDGEBDFs) based on the second derivative linear multi-step formulas of Cash [1]. This class of second derivative linear multistep formulas is implemented as boundary value methods on stiff problems. The order, error constant and the linear stability properties of the new methods are discussed.

• 터널과지하공간
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• 제19권6호
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• pp.498-506
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• 2009

복공식 압축공기 저장 터널의 라이닝은 고압의 공기압을 견뎌야 하므로 일반 도로터널 라이닝의 경우와는 다른 접근법에 의해 안정성 해석이 수행될 필요가 있다. 이에 따라 이 연구에서는 원통형 실린더의 탄성해 및 탄소성 해를 기반으로 하여 복공식 압축공기 저장터널에 설치되는 콘크리트 라이닝의 안정성 해석법이 제안되었다. 탄성해석의 경우 라이닝 내측 경계면의 항복개시조건을 라이닝 파괴기준으로 설정하였다. Mohr-Coulomb 항복기준을 적용한 탄소성 해석의 경우 최대 허용 항복 깊이까지 항복영역이 확대되는 조건을 파괴기준으로 설정하였다. 제안된 방법을 이용한 안정성해석 결과 라이닝의 내측 공기압과 배면하중의 상대적 크기가 라이닝의 안정성에 큰 영향을 미치는 것으로 나타났다. 상대적으로 추정이 힘든 배면하중의 정확한 예측이 라이닝 안정성 평가에서 매우 중요한 것으로 나타났다. 이에 따라 배면하중의 크기에 큰 영향을 주는 라이닝 설치시점 선택의 중요성이 강조되었다.

• 한국전산구조공학회:학술대회논문집
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• 한국전산구조공학회 2002년도 가을 학술발표회 논문집
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• pp.244-251
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• 2002

The purpose of this paper is to investigate the stability of tapered columns with general boundary condition(translational and rotational elastic support) at one end and carrying a tip mass of rotatory inertia with translational elastic support at the other end. The column model is based on the classical Bernoulli-Euler beam theory which neglects the effects of rotatory inertia and shear deformation. The governing differential equation for the free vibrations of linearly tapered columns subjected to a subtangential follower force is solved numerically using the corresponding boundary conditions. And the bisection method is used to calculate the critical divergence/flutter load. After having verified the results of the present study, the frequency and critical divergence/flutter load are presented as functions of various nondimensional system parameters.