A finite element simulation of the test procedure of stiffened panels

Hu, Song; Jiang, Lei

doi:10.1016/s0951-8339(98)00007-0

Cited by 21 publications

(14 citation statements)

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“…The welded structures under the axial compressive loading usually exhibit such difference in the initial stiffness due to the precise consideration of the residual stresses. The similar difference was also found in the study conducted by some other researchers like Hung et al (2002) and Hu and Jiang (1998). As in the present study, ultimate capacity against buckling is the main concern therefore, this small difference in initial stiffness may be ignored.…”

Section: Verification Of Reference Specimensupporting

confidence: 90%

“…To produce the residual stresses in welded structures, heat analysis with coupled temperature analysis is often used in FE study (Nakai et al, 2006;Hu and Jiang, 1998). In order to incorporate the residual stresses in FE study a combination of negative and positive temperature field was applied in the welded and other plate region respectively, considering the coupled temperature analysis with the coefficient of thermal expansion equal 11.0×10 −6 K −1 .…”

Section: Residual Stressesmentioning

confidence: 99%

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Experimental and numerical evaluation of bearing capacity of steel plate girder affected by end panel corrosion

et al. 2014

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The present study deals with the effect of uniform and non-uniform local corrosion damages at the bearing stiffener and nearby web on the bearing capacity of plate girder. Five plate girder ends simulated with different uniform and non-uniform types of corrosion damage, at the base of the bearing stiffener are used in the experimental program. The experimental results are modeled and verified on a Finite Element (FE) software ABAQUS, considering shell-solid coupling elements formulation. The study is further extended to various damage cases i.e., stiffener damage, stiffer plus web damages etc. considering different damage heights and residual thicknesses. The study concludes that minimum thickness within any damage height may be used to simulate the corrosion damage in a FE analysis. At the end, some empirical relationships are also proposed to estimate the bearing strength of the plate girder affected by the local corrosion damage at plate girder end.

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Section: Verification Of Reference Specimensupporting

confidence: 90%

Section: Residual Stressesmentioning

confidence: 99%

Experimental and numerical evaluation of bearing capacity of steel plate girder affected by end panel corrosion

et al. 2014

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“…Based on theory [22] and clearly demonstrated in the literature [23][24][25], the modelling of initial geometric imperfections is of great importance when evaluating initial skin buckling behaviour. In addition, failure behaviour may be affected by geometric imperfections if the imperfections are 'large' and span the entire structure [16].…”

Section: Initial Imperfection Modellingmentioning

confidence: 99%

The computational post-buckling analysis of fuselage stiffened panels loaded in shear

Murphy¹,

Price²,

Lynch³

et al. 2005

Thin-Walled Structures

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Fuselage panels are commonly fabricated as skin-stringer constructions, which are permitted to locally buckle under normal flight loads. The current analysis methodologies used to determine the post buckling response behaviour of stiffened panels relies on applying simplifying assumptions with semi-empirical / empirical data. Using the Finite Element method and employing non-linear material and geometric analysis procedures it is possible to model the post buckling behaviour of stiffened panels without having to place the same emphases on simplifying assumptions or empirical data. Previous work has demonstrated that using a commercial implicit code, the Finite Element method can be used successfully to model the post buckling behaviour of flat riveted panels subjected to uniform axial compression. This paper expands the compression modelling procedures to flat riveted panels subjected to uniform shear loading, investigating element, mesh, idealisation and material modelling selection, with results validated against mechanical tests. The work has generated a series of guidelines for the non-linear computational analysis of flat riveted panels subjected to uniform shear loading, highlighting subtle but important differences between shear and compression modelling requirements.

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“…Unless otherwise stated, the magnitude of this imperfection is 10% of the skin thickness, a value that is representative of typical imperfections present in conventional riveted fuselage structures. The post buckling analysis is then performed using the incremental-iterative Newton-Raphson solution procedure [11][12][13]. Within the NewtonRaphson solution procedure the structural problem is expressed as…”

Section: Solution Proceduresmentioning

confidence: 99%

The computational post buckling analysis of fuselage stiffened panels loaded in compression

Lynch¹,

Murphy

Price

et al. 2004

Thin-Walled Structures

View full text Add to dashboard Cite

Fuselage panels are commonly fabricated as skin-stringer constructions, which are permitted to locally buckle under normal flight loads. The current analysis methodologies used to determine the post buckling response behaviour of stiffened panels relies on applying simplifying assumptions with semi-empirical / empirical data. Using the Finite Element method and employing non-linear material and geometric analysis procedures it is possible to model the post buckling behaviour of stiffened panels without having to place the same emphases on simplifying assumptions or empirical data. Investigation of element, mesh, idealisation, imperfection and solution procedure selection is been undertaken, with results validated against mechanical tests. The research undertaken has demonstrated that using a commercial implicit code, the Finite Element method can be used successfully to model the post buckling behaviour of flat riveted panels. The work has generated a series of guidelines for the non-linear computational analysis of flat riveted panels subjected to uniform axial compression.

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A finite element simulation of the test procedure of stiffened panels

Cited by 21 publications

References 0 publications

Experimental and numerical evaluation of bearing capacity of steel plate girder affected by end panel corrosion

Experimental and numerical evaluation of bearing capacity of steel plate girder affected by end panel corrosion

The computational post-buckling analysis of fuselage stiffened panels loaded in shear

The computational post buckling analysis of fuselage stiffened panels loaded in compression

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