• Journal of the Earthquake Engineering Society of Korea
• /
• v.5 no.1
• /
• pp.63-72
• /
• 2001

상부 벽체와 하부 골조로 구성되는 주상복합건물은 전이층에서 수직적인 강성과 강도의 불연속성을 갖는다. 이러한 복합구조는 전이층에서 춤이 큰 보에 의하여 하중이 전달되면 설계시 매우 중요하게 고려하여야 하는 사항이다. 그러나 이에 대한 연구가 충분히 이루어져 있지 않으며 실제 전이보의 설계시 춤을 매우 크게 하여 요구되는 강도보다 큰 안전율이 고려되고 있다. 본 연구에서는 전이층의 단순화모델을 이용하여 보의 높이 및 지지면의 길이에 따른 아치거동의 변화를 조사하였다. 유한요소법을 이용하여 구조물을 분석하고 두 변수를 포함하는 헌치부재를 이용하여 그 효과를 기존 시스템과 비교하였다. 중요 변수와 헌치의 기울기는 1:1의 비율에서 사장 효율이 좋은 것으로 나타났으며, 이러한 결과를 전이보를 대신하여 사용한 결과 중력방향의 상부 아치거동에 대하여 효과적으로 작용하는 것으로 나타났다. 또한 응력 집중부위에서의 응력 감소와 깊이 전이보의 높이감소에 효과적으로 작용하는 것으로 나타났다.

• The Optical Journal
• /
• s.104
• /
• pp.23-25
• /
• 2006

프린터 시장은 삼성과 HP가 전체 시장의 60% 이상 과점상태를 보이고 있지만 후발업체들이 추격을 강화하는 가운데, 전체 시장은 소폭의 성장과 함께 가격하락세를 보이고 있다. 지난해 프린터 시장은 잉크젯에서 컬러 레이저로, 프린터 단품에서 복합기로의 변화를 거듭했다. 지금까지 프린터 시장을 주도해왔던 잉크젯 단품 제품은 지난해 정점을 찍으면서 앞으로 점차 수요가 감소하고 이 자리를 컬러 레이저와 복합기가 차지할 것으로 보인다.이런 전망에 확신을 실어주듯 지난해 컬러레이저 시장은 성장성이 높은 시장으로 떠오르며 시장경쟁이 가장 치열했다. 또한 향후에는 컬러 레이저 제품이 급속도로 성장할 것으로 전망되며, 복사기 및 프린터 업체들이 공통으로 기업용 솔루션 관련 시장을 본격 공략하며 치열한 경쟁관계를 형성할 것으로 보인다.

• Composites Research
• /
• v.17 no.5
• /
• pp.7-14
• /
• 2004

This paper deals with adaptive fuzzy logic controller design to achieve proper dynamic response of a composite thin-walled beam with a tip mass. In order to check the effectiveness of this controller, three different types of control logic are selected and applied. The adaptive control capabilities provided by a system of piezoactuators bonded or embedded into the structure are also implemented in the system. Results show that the fuzzy logic controller is more effective than the proportional or velocity feedback controller for the vibration control of composite thin-walled beam with a tip mass.

• Journal of Korean Society of Steel Construction
• /
• v.26 no.5
• /
• pp.397-405
• /
• 2014

A shear-flexible beam element is presented for the flexural analysis of laminated composite T-beams with arbitrary lay-ups. Based on the first-order shear deformable beam theory, the derived element takes into account warping shear deformation and all coupling coming from material anisotropy. Three different types of beam elements, namely, the two-noded, three-noded, and four-noded beam elements with seven degree-of-freedom per node are developed to solve governing equations. To demonstrate the versatility and accuracy of the beam element formulated, numerical results are performed for symmetric and anti-symmetric angle-ply composite T-beams under the uniformly distributed and concentrated load. The effects of fiber angle and shear deformation are investigated for different laminated stacking sequence. The quadratic and cubic elements are shown to be applicable to the flexural analysis of composite T-beams.

• Journal of the Korean Society for Railway
• /
• v.10 no.5
• /
• pp.600-606
• /
• 2007

3D finite element analyses of a corrugated steel web girder and a steel truss web girder are conducted to investigate the static and dynamic behaviour of the hybrid girders. And the analyses results are compared with those by the equivalent beam theory. The equivalent theory is a theory that all section properties of a truss structure are replaced by section properties of a beam including a shear coefficient. When applying the equivalent beam theory, the shear coefficient of the corrugated steel web girder is estimated as the area ratio of flange section to web section and that of the steel truss web girder is calculated by the equation proposed by Abdel. Static deflections and natural frequencies by 3D finite element analyses and those by the equivalent beam theory are in good agreement.

• Journal of Korean Society of Steel Construction
• /
• v.14 no.1
• /
• pp.31-40
• /
• 2002

Free vibration of a thin-walled laminated composite beam is studied. A general analytical model applicable to the dynamic behavior of a thin-walled channel section composite is developed. This model is based on the classical lamination theory, and accounts for the coupling of flexural and torsional modes for arbitrary laminate stacking sequence configuration. i.e. unsymmetric as well as symmetric, and various boundary conditions. A displacement-based one-dimensional finite element model is developed to predict natural frequencies and corresponding vibration modes for a thin-walled composite beam. Equations of motion are derived from the Hamilton's principle. Numerical results are obtained for thin-walled composite addressing the effects of fiber angle. modulus ratio. and boundary conditions on the vibration frequencies and mode shapes of the composites.

• Composites Research
• /
• v.23 no.6
• /
• pp.47-54
• /
• 2010

Thermal vibration characteristics of a thin walled composite beam attached on spacecraft are investigated in this paper. The composite beam is assumed to have a thin CUS(circumferentially uniform stiffness) wall and modeled with several composite materials which are already space qualified such as T300/Epoxy, YS90AEpoxy. Steady state angle and peak to peak error in spacecraft attitude angle and tip displacement of composite beams are evaluated as a performance index for thermal vibration characteristics. Evaluation results shows that composite beam made out of YS90A has nearly 2 times better than T300 in terms of peak to peak attitude error angle.

• Composites Research
• /
• v.17 no.3
• /
• pp.29-37
• /
• 2004

The aeroelastic stability analysis of composite bearingless rotors is investigated using a large deflection beam theory in hover. The bearingless rotor configuration consists of a single flexbeam with a wrap-around type torque tube and the pitch links located at the leading edge and trailing edge of the torque tube. The outboard main blade, flexbeam and torque tube are all assumed to be an elastic beam undergoing flap bending, lead-lag bending, elastic twist and axial deflections, which are discretized into beam finite elements. For the analysis of composite bearingless rotors, flexbeam is assumed to be a rectangular section made of laminate. Two-dimensional quasi-steady strip theory is used for aerodynamic computation. The finite element equations of motion for beams are obtained from Hamilton's principle. The p-k method is used to determine aeroelastic stability boundary. Numerical results are presented for selected bearingless rotor configurations based on the lay-up of laminae in the flexbeam and pitch links location. A systematic study is made to identify the importance of the stiffness coupling terms on aeroelastic stability for various fiber orientation and for different configuration.

• Journal of the Computational Structural Engineering Institute of Korea
• /
• v.20 no.6
• /
• pp.691-697
• /
• 2007

Numerical eigen analysis of beam-like structure can be easily and effectively done by various conventional beam theory-based methods. However, in case of the structures composed of composite-sectioned beams, the application of conventional numerical methods requires one to derive both equivalent material and geometry properties. In the present paper, these equivalent properties are derived by the transformed section method and the test FEM program is coded. The numerical accuracy of the proposed method is verified through the comparison with the ANSYS 3-D model.

• Journal of Korean Society of Steel Construction
• /
• v.13 no.3
• /
• pp.233-244
• /
• 2001

In this study, flexural rigidity reduction of multi-delaminated composite beams are investigated. In order to evaluate the flexural rigidity reduction. Performed theoretical analysis. In order to investigate flexural rigidity reduction about effects of delamination on composite beams, the general kinematic governing equations are derived and solved by dividing the delaminated beam and imposing the continuity conditions into each sub-beam. For condition to appear multiple delamination through the laminated composite beams, the flexural rigidity reduction are compared according to many stacking sequences and several forms for delaminations. The present study could be used to evaluate the flexural rigidity reduction of composite laminated beams on multi-delaminations.