• Steel and Composite Structures
• /
• v.22 no.5
• /
• pp.1193-1214
• /
• 2016

In this paper, the 3D stress state and inter-laminar stresses in a rotating thin laminated cylinder shell are studied. The thickness of the cylinder is supposed to be thin and it is made of laminated composite material and can have general layer stacking. The governing equations of the cylindrical shell are obtained by employing the Layerwise theory (LWT). The effect of rotation is considered as rotational body force which is induced due to the rotation of the cylinder about its axis. The Layerwise theory (LWT), is used to discrete the partial differential equations of the problem to ordinary ones, in terms of the displacements of the mathematical layers. By applying the Free boundary conditions the solution of the governing equations is completed and the stress state, the inter-laminar stresses, and the edge effect in the rotating cylindrical shells are investigated in the numerical results. To verify the results, LWT solution is compared with the results of the FEM solution and good agreements are achieved. The inter-laminar normal and shear stresses in rotating cylinder are studied and effects of layer stacking and angular velocity is investigated in the numerical results.

• Journal of the Korea Concrete Institute
• /
• v.25 no.1
• /
• pp.45-51
• /
• 2013

Short beam tests of GFRP and CFRP specimens exposed to high temperature were conducted to measure the inter-laminar shear strength. For the phase I test, the exposure time and temperature were varied to measure reduction in the strength due to the applied conditions. As a results, the critical temperature was found to $270^{\circ}C$ for the both FRP reinforcements. The high temperature, which causes 50% loss of inter-laminar shear strength, is defined as the critical temperature in this study. It should be noted that the critical temperature for the inter-laminar shear strength is mainly dependent on resin properties not on fiber type. In the phase II test, the effect of exposure time was investigated at intervals of 0.25hour for the critical temperature. All test results demonstrate that the exposure time effect is not significant compared to the maximum exposure temperature, but it is not negligible and, moreover, is significant at the critical temperature.

• Journal of the Korea institute for structural maintenance and inspection
• /
• v.18 no.3
• /
• pp.108-115
• /
• 2014

Mechanical properties of GFRP rebars significantly decrease due to high temperature as well as alkalinity of concrete. This study focuses on the long-term reduction of inter-laminar shear strength of pre-damaged GFRP rebars by high temperature. For this investigation, bare GFRP rebar specimens were exposed to $270^{\circ}C$ for 1hour and then immerged in alkali solution for several months and tested in shear. No thermally conditioned specimens were immerged and tested for the comparisons. In results, the reduction of thermally damaged GFRP rebars was greater than that of no thermally damaged ones. Based on the accelerated experimental test data, an polynomial equation is presented for prediction of long-term residual inter-laminar shear strength of GFRP rebars previously damaged by high temperature.

• Proceedings of the Korean Society For Composite Materials Conference
• /
• 2004.04a
• /
• pp.161-164
• /
• 2004

In these days, composite materials are applied to the military field like parts of air crafts, rockets, ammunitions and so on. As high pressure is loaded on the composite body, however, cracks or delamination phenomena can be occurred between layers of laminate. These cracks or delamination usually cause a deterioration of mechanical properties under the complicated loads. In this study, methods for improvement of the inter-laminar bonding strength of thick carbon/epoxy composite structures are suggested and discussed in terms of segment bending test.

• Korean Journal of Metals and Materials
• /
• v.49 no.8
• /
• pp.589-595
• /
• 2011

Laminated glass fiber-reinforced plastic (GFRP) composites were applied to an insulating structure of a magnet system for a nuclear fusion device. Decreased inter-laminar strength by a strong repulsive force between coils which is induced a problem of structural integrity in laminated GFRPs. Therefore, it is important to investigate the inter-laminar characteristics of laminated GFRP composites in order to assure more reliable design and better structural integrity. Three types of the laminated GFRP composites using a high voltage insulating materials were fabricated according to each molding process. To evaluate the grade of the fabricated composites, mechanical tests, such as hardness, tensile and compressive tests,were carried out. The autoclave molding composites satisfied almost of the mechanical properties reguested at the G10 class standard, but the vacuum impregnation (VPI) and Prepreg composites did not.

• Journal of the Korean Society of Fisheries and Ocean Technology
• /
• v.34 no.4
• /
• pp.450-456
• /
• 1998

• Steel and Composite Structures
• /
• v.35 no.3
• /
• pp.439-447
• /
• 2020

This paper presents two sets of full three-dimensional thermoelastic finite element analyses of superimposed thermo-mechanically loaded Spar Wingskin Joints made with laminated Graphite Fiber Reinforced Plastic composites. The study emphasizes the influence of residual thermal stresses and material anisotropy on the inter-laminar delamination behavior of the joint structure. The delamination has been pre-embedded at the most likely location, i.e., in resin layer between the top and next ply of the fiber reinforced plastic laminated wingskin and near the spar overlap end. Multi-Point Constraint finite elements have been made use of at the vicinity of the delamination fronts. This helps in simulating the growth of the embedded delamination at both ends. The inter-laminar thermoelastic peel and shear stresses responsible for causing delamination damage due to a combined thermal and a static loading have been evaluated. Strain energy release rate components corresponding to the Mode I (opening), Mode II (sliding) and Mode III (tearing) of delamination are determined using the principle of Virtual Crack Closure Technique. These are seen to be different and non-self-similar at the two fronts of the embedded delamination. Residual stresses developed due to the thermoelastic anisotropy of the laminae are found to strongly influence the delamination onset and propagation characteristics, which have been reflected by the asymmetries in the nature of energy release rate plots and their significant variation along the delamination front.

• Proceedings of the Korean Nuclear Society Conference
• /
• 1997.05b
• /
• pp.177-182
• /
• 1997

금속연료가 연소할 때 발생하는 Fission Gas는 주로 직경방향으로의 Swelling을 일으켜 낮은 연소도의 원인이 되어 왔다. 따라서 본 연구에서는 높은 연소도를 갖는 금속연료의 개발을 목적으로 Fission Gas가 Plenum으로 쉽게 방출하는 조직인 Laminar Structure를 갖는 합금의 설계를 연구하였다. 또한 조사 후의 조직안정성을 예측하기 위해 열처리 후의 미세조직의 변화를 관찰하여 조직안정성을 시험하였다. U-10wt.%Zr 합금 중 Zr 원소 대신에 2wt.% 및 3wt.%의 W 또는 Mo을 첨가한 합금을 제조하여 합금원소 첨가의 영향에 따른 미세조직의 변화를 조사하였다. 그 결과 모든 조성의 합금은 Matrix에 있어서 Laminar Structure를 나타내었다. 또한 U-10wt.%Zr에 비해 2wt.% 및 3wt.%W의 W 또는 Mo를 첨가한 합금의 lamina Thickness가 철면 미세해짐을 확인하였다. 특히 U-7wt.%Zr-3wt.%W의 경우는 U-10wt.Zr에 비해 Laminar Thickness가 1/2배까지 감소되었다. 합금원소(W, Mo) 첨가에 의한 Laminar Thickness의 감소는 Fission Gas의 Inter-connected Path가 보다 잘 형성되게 하여 Gas의 방출속도를 증가시켜 Swelling을 감소시킬 것으로 생각된다. 열처리한 금속연료의 미세조직을 비교한 결과를 보면 합금원소(W, Mo)를 첨가한 합금을 50$0^{\circ}C$에서 1000시간동안 열처리한 것을 U-Zr 2원계 합금을 열처리한 것과 비교했을 때 약 1/3배 정도의 Laminar Thickness를 유지하는 것으로 보아 합금원소를 첨가하면 조사 후의 조직안정성에도 크게 기여할 것으로 기대된다.

• International Journal of Air-Conditioning and Refrigeration
• /
• v.15 no.2
• /
• pp.47-53
• /
• 2007

Laminar heat transfer experiments were conducted in flat extruded aluminum tubes. Three different flat tubes-two with smooth inner channel, one with micro-finned inner channel-were tested. Smooth tube data were in reasonable agreement with the predictions by simplified theoretical models. The heat transfer coefficients of the micro-fin tube were significantly smaller than those of the smooth tube. The reason was attributed to the decelerating flow in the inter-fin region. Heat transfer correlations were developed from the data.

• Transactions of the Korean Society of Mechanical Engineers B
• /
• v.30 no.5 s.248
• /
• pp.480-488
• /
• 2006

Numerical simulations of flow over two spheres placed in a tandem arrangement are conducted to investigate the effect of the inter-sphere spacing on the flow characteristics. The Reynolds numbers considered are 100, 250, 300 and 425, corresponding to steady axisymmetric, steady planar-symmetric, unsteady planar-symmetric, and unsteady asymmetric flows, respectively, in the case of a single sphere. For small inter-sphere spacings, the flow past two spheres is more stable than that past a single sphere. For example, with the spacing of the sphere radius, the flow is steady axisymmetric up to Re=300. However, for relatively large spacings, the flow past two spheres becomes unstable and vortex shedding takes place even at Re=250. The drag coefficient of the rear sphere decreases significantly with decreasing inter-sphere spacing due to reduction of the stagnation pressure, thus being smaller than that of the front sphere. Also, the rear sphere shows large fluctuations of the lift force as compared to the front one in the case of unsteady flow.