• Journal of Korean Society of Steel Construction
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• v.17 no.3 s.76
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• pp.337-346
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• 2005

A composite bridge deck system assembled from a modular profile with double-rectangular cell has been developed for highway bridges. This study is focused on the experimental characterization of flexure performance of pultruded GFRP deck under static loading. Several tests were conducted on single modules and adhesively bonded 2 and 5-modules. The specimen details such as dimensions, material properties and fiber architecture, and experimental set-up and testing procedure have been addressed. It is found that the presented GFRP composite modular deck is very efficient for use in bridges.

• Journal of the Korean Society of Manufacturing Technology Engineers
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• v.19 no.6
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• pp.782-789
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• 2010

It is important to satisfy the requirements and standards for the protections of passengers in a car accident. There are lots of studies on the crushing energy absorption of a structure member in automobiles. In this paper, we have studied to investigate collapse characteristics and moisture absorption movements of CFRP( carbon fiber reinforced plastics) structure members when CFRP laminates are under the hygrothermal environment. In particular, the absorbed energy, mean collapse load and deformation mode were analyzed for CFRP members which absorbed most of the collision energy. Also, variation of stacking angle is important to increase the energy absorption capability. The purpose of this study is to evaluate the strength reduction and moisture absorption behavior of CFRP hat shaped member. Therefore we have made a impact collapse experiment to research into the difference of absorbed energy and deformation mode between moisture absorbed specimen and non-moisture absorbed. As a result, the effect of moisture absorption and impact loads of approximately 50% reduction in strength are shown.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.31 no.6 s.261
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• pp.671-678
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• 2007

Front-side members of automobile, such as the hat shaped section members, are structures with the greatest energy absorbing capability in a front-end collision of vehicle. This paper was performed to analyze energy absorption characteristics of the hat shaped section members, which are basic shape of side member. The hat shaped section members consisted of the spot welded side member which was utilized to an actual vehicle and CFRP side member for lightweight of vehicle structural member. The members were tested under static axial loading by universal testing machine. Currently, stacking condition related to the collapse characteristics of composite materials is being considered as an issue fer the structural efficiency and safety of automobiles, aerospace vehicles, trains, ships even elevators during collision. So, energy absorption characteristics were analyzed according to stacking condition and shape of section and compared the results of spot welded side member with those of CFRP side member.

• Journal of Korean Society of Steel Construction
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• v.9 no.3 s.32
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• pp.333-340
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• 1997

This paper will expand the third-order shear deformation theory by the double-Fourier series and reduce to the solution of a system of ordinary differential equations in time, which are integrated numerically using Newmark's direct integration method and clarify the undamped dynamic responses for the cross-ply and antisymmetric angle-ply laminated composite plates and shells with simply supported boundary condition. Numerical results for deflections are presented showing the effect of side-to-thickness ratio, aspect ratio, material anisotropy, and lamination scheme.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.12 no.2
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• pp.171-184
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• 1999

이 논문은 시공단계를 고려한 콘크리트 프레임 구조물의 거동 해석을 다루고 있다. 고층건물의 경우 하루에 시공이 완료되지 않으므로 각 시공단계에 따라 콘크리트의 시간의존적 현상은 다르게 발생된다. 이를 위하여 이 논문에서는 일반적인 프레임 해석기법에 콘크리트의 시간의존적 특성을 고려하였다. 이 연구에 도입된 해석기법은 단면을 가상의 층으로 나누고 각층은 일축상태로 가정한 적층단면을 사용하였다. 요소는 평면 보요소를 사용하였으며 강성행렬은 변위법을 바탕으로 유도하였고 전체적인 구조해석은 비선형 구조해석 방법의 하나인 복합법을 사용하였다. 콘크리트의 시간의존적 특성을 고려하기 위하여 단면의 각 층에서 크리프와 건조수축에 의한 변형률을 계산하였으며 크리프는 크리프 Compliance의 전개에 기본을 둔 1차 순환적 단계 알고리즘을 사용하였다. 끝으로 이 연구에서 제안된 해석모델을 이용하여 프레임해석 및 기둥축소에 관한 예제를 해석하였다.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.12 no.4
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• pp.563-571
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• 1999

변단 면과 다양한 경계조건을 갖는 보와 타워구조물의 제1모드에서의 고유진동수를 구하는 정확한 해는 1974년에 Kim에 의해 발표되었다. 최근 이 방법은 복합재료 적층 판을 포함하는 2차원 문제의 제 1모드 진동해석에 확장되었으며, 다양한 경계조건과 불규칙 단면을 갖는 판에 매우 효과적이다. 이 논문에서는 변단 면과 경계조건에 따른 특별직교 이방성 판에 대한, Kim에 의해 개발된 간편한 진동해석 방법의 응용결과가 주어진다. 또한 집중하중들에 대한 영향이 연구되었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.3
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• pp.261-268
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• 2011

Generally, modeling procedure of cross section of composite rotor blade is complicated and time-consuming, because it is made up of various stiffeners and multiple layers of composite materials. For efficient modeling of cross section of composite rotor blade, a modeling program so called KSec2D, which provides a user friendly GUI, is developed by using a 2D modeling algorithm based on set operation. By the developed program KSec2D, a modeling of complicated cross section of rotor blade is carried out. Through the demonstration, the usefulness of developed program in modeling procedure of cross section of composite rotor blade is verified.

• Journal of Korean Society of Steel Construction
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• v.14 no.1
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• pp.23-29
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• 2002

Many of the bridge systems, including the girders and cross-beams, and concrete decks behave as the special orthotropic plates. Such systems with boundary conditions other than Navier or Levy solution types, or with irregular cross sections, analytical solution is very difficult to obtain. Numerical method for eigenvalue problems are also very much involved in seeking such a solution. A method of calculating the natural frequency corresponding to the first mode of vibration of beam and tower structures with irregular cross-sections was developed and reported by Kim in 1974. Recently, this method was extended to two dimensional problems including composite laminates, and has been applied to composite plates with shear deformation effects. In this paper, application of this method to the specially orthotropic laminated plates with various boundary condition is accomplished and the result of analysis is presented.

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

• Composites Research
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• v.14 no.3
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• pp.32-41
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• 2001

Z-section composite stringers with various lengths and flange-widths are tested in axial compression for the validation of a finite element algorithm to calculate the buckling and crippling stresses of composite laminated stringers. The stacking sequence considered is $[{\pm}45/0/90]s$. Strain gages are attached to each specimen, and deflection and end-shortening are obtained by two LVDTs. The buckling load is determined from the load vs. strain response, load vs. end-shortening curves, and load vs. out-of-plane deflection curves. The ultimate stress after local buckling is used as the crippling stress. Comparison between finite element and experimental results shows good agreement in the local buckling and crippling stresses.