• 한국전산구조공학회논문집
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• 제34권6호
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• pp.347-353
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• 2021

본 논문에서는 구조물의 좌굴 온도와 좌굴 형상을 제어하는 새로운 크기 최적화 방법에 대해서 소개한다. 구조적 안정성 관점에서 구조물의 좌굴 온도와 좌굴 형상을 예측하는 것은 중요한 주제 중 하나이다. 이를 공학적인 직관을 통해 예측하고 최적화된 구조 설계를 하는 것은 너무나 어려운 과제이다. 이러한 한계점을 해결하기 위해 본 연구에서는 유한요소 시뮬레이션과 치수 최적 설계 방식의 조합을 제안한다. 구조물의 좌굴 온도와 좌굴 형상이 구조물의 두께에 영향을 받는다는 생각에서 착안해 설계 변수를 구조물의 노드의 두께 값으로 설정했다. 좌굴 온도 값과 좌굴 형상을 목적 함수로 정해진 부피 값을 제약 조건으로 두었다. 치수 최적 설계를 통해 원하는 좌굴 온도와 좌굴 형상을 유도하기 위한 최적의 두께 분포를 결정할 수 있다. 제안된 치수 최적 설계의 타당성은 본 논문의 다양한 직사각형 복합 구조물 예제들을 사용해서 검증하였다.

• Nuclear Engineering and Technology
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• 제35권6호
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• pp.537-546
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• 2003

The purpose of this paper is to investigate the buckling characteristics of a conceptually designed KALIMER-150(Korea Advanced LIquid MEtal Reactor, 150MWe) reactor vessel and verify the buckling behavior using the reduced scale cylindrical shell structures. To do this, nonlinear buckling analyses using finite element method and evaluation formulae are carried out. From the results, the KALIMER-150 reactor vessel exhibits a dominant bending buckling mode and is significantly affected by the plastic behavior. The interaction effects with the vertical seismic load cause the lateral buckling load to be slightly decrease. From the results of the buckling experiments using reduced scaled cylindrical shell structures, it is verified that the buckling modes such as pure bending, pure shear, and mixed(bending plus shear) mode clearly appear under a lateral load corresponding to the slenderness ratio of cylinder.

• 한국구조물진단유지관리공학회 논문집
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• 제18권6호
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• pp.11-20
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• 2014

본 연구는 정현형 주름과 마름모형 주름 형상의 전단좌굴 특성을 비교, 분석하는 것이 목적이다. 이를 위해서 동일한 길이의 마름모꼴 주름과 정현파주름을 해석대상모델로 채택하였으며, 선형좌굴해석을 통한 전단좌굴특성과 이론식에 의한 특성을 분석하였다. 일반적으로 주름강판의 전단좌굴 형태는 국부좌굴, 전체좌굴 및 두 좌굴에 의한 연성좌굴로 분류된다. 그러나 마름모꼴주름과는 달리 정현파주름형상은 평평한 면이 없기 때문에 전단좌굴의 양상에 대한 경향이 달라진다. 특히 국부좌굴과 전체좌굴의 경계에서 나타나는 전단응력변화와 양상은 주름형태에 의해 차이가 난다. 분석 결과에서 볼 때, 제형 (마름모꼴)의 경우는 이론식내의 전체좌굴과 국부좌굴의 경계에서 연성좌굴모드가 발생했다. 그러나 정현파형의 경우 전체좌굴이 발생하는 구간에서 연성좌굴모드가 발생하는 양상을 보였다. 또한 국부좌굴 구간에는 제형형상이 그리고 전체좌굴 구간에서는 정현파형상이 전단좌굴에 저항하는데 유리하게 작용하였다.

• 대한기계학회논문집
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• 제19권2호
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• pp.354-362
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• 1995

The finite element modeling is used to study the buckling and postbuckling behavior of composite laminates with an embedded delamination. Degenerated shell element and rigid beam element are utilized for the finite element modeling. In the nonlinear finite element formulation, the updated Lagrangian description method based on the second Piola-Kirchhoff stress tensor and the Green strain tensor is used. The buckling and postbuckling behavior of composite laminates with a delamination are investigated for various delamination sizes, stacking sequences, and boundary conditions. It is shown that the buckling load and postbuckling behavior of composite laminates depend on the buckling model which is determined by the delamination size, stacking sequence and boundary condition. Also, results show that introduction of couplings can reduce greatly the buckling load.

• Structural Engineering and Mechanics
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• 제5권6호
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• pp.715-728
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• 1997

The aim of this paper is to investigate the secondary buckling behaviour and mode-coupling of spherical caps under uniformly external pressure. The analysis makes use of a rotational finite shell element on the basis of strain-displacement relations according to Koiter's shell theory (Small Finite Deflections). The post-buckling behaviours after a bifurcation point are analyzed precisely by considering multi-mode coupling between several higher order harmonic wave numbers: and on the way of post-buckling path the positive definiteness of incremental stiffness matrix of uncoupled modes is examined step by step. The secondary buckling point that has zero eigen-value of incremental stiffness matrix and the corresponding secondary mode are obtained, moreover, the secondary post-buckling path is traced.

• International Journal of Aeronautical and Space Sciences
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• 제18권3호
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• pp.450-466
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• 2017

This paper defines the modified effective membrane stiffness, bending stiffness considering the directionally dependent mechanical properties and mode shape function of a composite lattice rectangular plate, which is assumed to be a Kirchhoff-Love plate. It subsequently presents an approximate method of conducting a buckling analysis of the composite lattice rectangular plate with various boundary conditions under uniform compression using the Ritz method. This method considers the coupled buckling mode as well as the global and local buckling modes. The validity of the present method is verified by comparing the results of the finite element analysis. In addition, this paper performs a parametric analysis to investigate the effects of the design parameters on the critical load and buckling mode shape of the composite lattice rectangular plate based on the present method. The results allow a database to be obtained on the buckling characteristics of composite lattice rectangular plates. Consequently, it is concluded that the present method which facilitates the calculation of the critical load and buckling mode shape according to the design parameters as well as the parametric analysis are very useful not only because of their structural design but also because of the buckling analysis of composite lattice structures.

• 항공우주시스템공학회지
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• 제14권6호
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• pp.68-73
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• 2020

Skin-stringer structures are widely used in aircrafts due to their advantage of minimizing structural weight while maintaining load carrying capacity. However, buckling load can cause serious damage to these structures. Therefore, the buckling characteristics of skin-stringer structures should be carefully considered during the design phase to ensure structural soundness. In this study, finite element method was applied to predict the buckling characteristics of stiffened panels. In terms of the failure mode, finite element analysis showed a symmetrical buckling mode, whereas an asymmetrical mode was determined by experimentation. The numerical results were obtained and compared to the experimental data, showing a difference of 9.3% with regard to the buckling loads.

• Structural Engineering and Mechanics
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• 제57권3호
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• pp.543-567
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• 2016

This study attempts to address the buckling and free vibration characteristics of an isotropic cylindrical panel subjected to non-uniform temperature rise using numerical approach. Finite element analysis has been used in the present study. The approach involves three parts, in the first part non-uniform temperature field is obtained using heat transfer analysis, in the second part, the stress field is computed under the thermal load using static condition and, the last part, the buckling and pre-stressed modal analysis are carried out to compute critical buckling temperature as well as natural frequencies and associated mode shapes. In the present study, the effect of non-uniform temperature field, heat sink temperatures and in-plane boundary constraints are considered. The relation between buckling temperature under uniform and non-uniform temperature fields has been established. Results revealed that decrease (Case (ii)) type temperature variation field influences the fundamental buckling mode shape significantly. Further, it is observed that natural frequencies under free vibration state, decreases as temperature increases. However, the reduction is significantly higher for the lowest natural frequency. It is also found that, with an increase in temperature, nodal and anti-nodal positions of free vibration mode shapes is shifting towards the location where the intensity of the heat source is high and structural stiffness is low.

• 대한기계학회논문집A
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• 제20권8호
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• pp.2491-2500
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• 1996

An experimental and analytical investigation is performed to study the buckling behavior of composite laminates with an embedded delamination. It is of particular interest to veryfy whether delamination growth cddurs with continuming deformation after buckling of composite laminates with an embedded delamination. Experiments are conducted for [0/sub 4///90/sub 8//0/sub 4/]/sub r/ laminates with delamination size in which local buckling mode governs buckling. Results show that delamination growth occurs in hgigher load after buckling and is accompanid by other damage mechanisms such as splitting. Also, it is found that transverse deformation before difurcation buckling is due to initial imperfection and structure such as plate with small bending stiffness is sensitive to that.

• 한국전산구조공학회논문집
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• 제15권3호
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• pp.535-543
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• 2002

본 논문의 목적은 전단하중을 받는 얇은 원통구조물의 세장비에 따른 좌굴특성을 보다 깊이 있게 검토하는 것이다. 이를 위하여 J. Okada 등이 제안한 좌굴평가식을 사용하여 세장비에 따른 좌굴강도 평가를 수행하였다. 좌굴강도 평가 결과들로부터 세장비 L/R=3.1, 1.6, 그리고 1.0을 갖는 세가지 좌굴시험체를 결정하고 이에 대한 수치해석과 좌굴특성시험을 수행하였다. 그 결과, 세장비 L/R=3 이상인 경우 평가식에서 예측된 바와 같은 굽힘좌굴이 지배적으로 나타났으며 세장비 L/R=1.0이하로 작을 경우에는 전단좌굴이 지배적으로 나타났고, 세장비 L/R=1.6 영역에서는 전단과 굽힘좌굴이 동시에 발생하는 복합자굴 특성이 나타났다 그리고 수치해석과 평가식에 의한 좌굴특성평가 결과는 시험결과들과 잘 일치하였다.