• KSCE Journal of Civil and Environmental Engineering Research
• /
• v.29 no.4A
• /
• pp.299-305
• /
• 2009

In this study, in order to research the causes lead to fatigue crack in the coped stringer of a steel railway bridge, we take the steel railway bridge which actually occurs fatigue crack as a research object and manufacture the full size of crossbeam-stringer and floor system model to perform the experimental test. The results indicates that, the fatigue crack in the top of coped area of stringers is caused by the reciprocal action of the in plane stress in the tip of coped area of web by the negative moment occurred in the end of the stringers. While the fatigue crack in the bottom of coped area of stringers is due to the plane stress caused by the out-plane deformation relative to the bottom of coped area of web of the fixed end in the stringers.

• Computational Structural Engineering
• /
• v.6 no.3
• /
• pp.81-88
• /
• 1993

An efficient approach to the buckling analysis of stiffened cylindrical shells with rings and stringers under the axial and the lateral pressure loadings is presented. By this approach, the local buckling as well as overall buckling behavior has been investigated considering the discreteness of stiffeners and appropriate adoption of displacement functions. Some design criteria based on structural stability to determine optimum scantlings of stiffeners are also suggested. It is shown that the optimum scantlings of stiffeners can be designed from the condition of equal local and overall buckling strength.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
• /
• 1996.04a
• /
• pp.349-354
• /
• 1996

The analytical solutions for the free vibration and buckling of cross-ply laminated composite cylindrical shell with axial stiffeners(stringers) and circumferential stiffeners(rings), that is, orthogonally stiffened shells, are presented using the energy method. The stiffeners are assumed to be an integral part of the shell and have been directly included in analysis(it's called discrete stiffener theory). The effect of the parameters such as the stacking sequences, the shell thickness, the shell length-to-radius ratio are studied. By comparison with the previously published analytical results for the stiffened cylindrical shells, it is shown that natural frequencies can be determined with adequate accuracy.

• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 2004.10a
• /
• pp.1070-1073
• /
• 2004

This paper is on the development of a system for removing membranes which is designed exclusively for aircraft components. Membrane removal solution is a most critical issue in aerospace industries since a method of manufacturing the components tends to be changed from fabrication of many parts to cutting into one body. The cutting method inevitably produces a huge amount of chips and then membranes remain in the body. The membrane removal process, as a result, becomes an important issue since it is directly related to productivity. We tried to develop a new machine which will replace the conventional method that uses a handy tool. The machine has been designed for a cutting tool set to follow the unique shape of the slot in the body by a cam follower and cut the membrane automatically. The design has been checked by structural analysis: stress and vibration analysis. A prototype test has been finished. This paper summarizes a series of development process of the deburring machine and some design issues are discussed.

• Journal of the Korean Society of Safety
• /
• v.19 no.4 s.68
• /
• pp.101-108
• /
• 2004

In this study, open conical shells with ring and stringers are analyzed A versatile 4-node shell element which is useful for the analysis of conical shell structures is used and 3-D beam element is used for stiffeners. An improved flat shell element is established by the combined use of the addition of non-conforming displacement modes and the substitute shear strain fields. The proposed element has six degrees of freedom per node and permits an easy connection to other types(beam element) of finite elements. Optimum location and optimum section properties of ring and stinger are obtained. It is shown thai the thickness of conical shell can be reduced about $20\~50\%$ by appropriate location of stiffeners.

• Journal of the Korean Society of Marine Environment & Safety
• /
• v.5 no.2
• /
• pp.99-111
• /
• 1999

The object of this study is to get the superior double hull structure to its crashworthiness against collision comparing absorbed energy capacities of its various types with each other, varying material properties, collision positions and velocities, and structural arrangements such as double hull width, web and stringer spaces, etc. Local absorbed energy capacities, failure behaviors and damage extents of their members are also considered during collision in addition to the estimations of their global ones. This paper describes a series of numerical simulations of collisions between DWT 45,000 oil tanker(struck ship) and DWT 10,500 rigid one(striking ships) using Hydrocode LS/DYNA3D. Collisions are assumed to occur at the middle of struck ship with striking one moving at right angle to its centerline. The following remarks were obtained through this study: More flexible the double hull structure is, much superior its crashworthiness against collision is. The increment of double hull width does not give much influence than other factors do. The exact use of material property such as failure strain is also important on the numerical simulation of collision.

• Proceedings of the KSR Conference
• /
• 2003.10b
• /
• pp.557-562
• /
• 2003

The responses of the floor system of a railway bridge are investigated for fatigue life prediction of damaged members using fracture mechanics approach. Numerical analysis of the structure is performed in order to see the influence of track-structure interaction and continuity of the truss connection on the response of the bridge members. Fatigue crack growth analysis is carried through equivalent stress obtained from time-history analysis. The results of time-history analysis agree with measured responses. The fatigue propagation life increases as the curvature in the coped stringer increases.

• Journal of KSNVE
• /
• v.6 no.4
• /
• pp.457-467
• /
• 1996

The analytical solutions for the free vibration and buckling of cross -ply laminated composite cylindrical shell with the orthogonal stiffeners, i. e., axial stiffeners(stringers) and circumferential stiffeners(rings), are presented using the energy method. The stiffeners are assumed to be an integral part of the shell and have been directly included in analysis(it's called discrete stiffener theory). The effect of the parameters such as the stacking sequences, the shell thickness, the shell length-to-radius ratio are studied. By comparison with the previously published analytical results for the stiffened cylindrical shells, it is shown that natural frequencies can be determined with adequate accuracy.

• Journal of Aerospace System Engineering
• /
• v.1 no.1
• /
• pp.36-44
• /
• 2007

This study was performed on preliminary structural design of a small scale WIG craft which has been developed as a next generation high speed maritime transportation system in Korea. A composite structure design using the foam-sandwich for main wing and tail fins and the honeycomb sandwich and skin-stringer-ring frame for fuselage was applied for weight reduction as well as structural stability. A commercial FEM code, NASTRAN for was utilized to confirm the structural safety for the reiterate design modifications to meet design requirements including the target weight. Each main wing was jointed with the fuselage by eight high strength insert bolts for easy assembling and disassembling as well as for assuring the required 20 years service life. For control surface structural design, the channel type spar, the foam sandwich skin and the lug joint were adopted.

• International Journal of Aerospace System Engineering
• /
• v.7 no.1
• /
• pp.7-15
• /
• 2020

In this paper the crack growth, modeling, and simulation of the stiffened and un-stiffened cracked panels presented using commercially available finite element software packages. Computation of stresses and convergence of stress intensity factor for single edge notch (SEN) specimens carried out using the finite element method (FEM) and extended finite element method (XFEM) and compared with an analytical solution. XFEM techniques like cohesive segment method and LEFM using virtual crack closure technique (VCCT), used for crack growth analysis and presented results for un-stiffened and stiffened panels considering various crack domain. The non-linear analysis considering both geometric and material non-linearity on stiffened panels with various stringers like a blade, L, inverted T and Z sections the results were presented. Arrived at the optimum stringer section type for the considered panel under axial loading from the numerical analysis.