Postbuckling behavior of selected flat stiffened graphite-epoxy panels loaded in compression

Starnes, James H.; Knight, Norman F.; Rouse, Marshall

doi:10.2514/3.9072

Cited by 100 publications

(28 citation statements)

References 7 publications

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“…This skin-flange separation has been identified as the primary failure mechanism for panels subjected to compression, pressure and/or shear loadings and in panels demonstrating postbuckling behavior [3][4][5][6][7][8]. The influence of stitching on the separation of the flange from the stringer, examined in references 9 and 10, indicate that stitching can significantly improve the debonding resistance of graphite-epoxy panels.…”

Section: Introductionmentioning

confidence: 99%

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Improving strength of postbuckled panels through stitching

Jegley

2007

Composite Structures

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The behavior of blade-stiffened graphite-epoxy panels with impact damage is examined to determine the effect of adding through-the-thickness stitches in the stiffener flange-to-skin interface. The influence of stitches is evaluated by examining buckling and failure for panels with failure loads up to 3.5 times greater than buckling loads. Analytical and experimental results from four configurations of panel specimens are presented. For each configuration, two panels were manufactured with skin and flanges held together with through-the-thickness stitches introduced prior to resin infusion and curing and one panel was manufactured with no stitches holding the flange to the skin. No mechanical fasteners were used for the assembly of any of these panels. Panels with and without low-speed impact damage were loaded to failure in compression. Buckling and failure modes are discussed. Stitching had little effect on buckling loads but increased the failure loads of impact-damaged panels by up to 30%.

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Section: Introductionmentioning

confidence: 99%

“…Analytical and experimental results from these panels are presented herein. Since impact damage has been a critical factor in the design of composite aircraft structure [3,11,12], the problem of skin-stiffener separation is examined in both undamaged and impact-damaged panels.…”

Section: Introductionmentioning

confidence: 99%

Improving strength of postbuckled panels through stitching

Jegley

2007

Composite Structures

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“…The multi-stringer panel is generally designed to operate at loads several times the initial buckling load but, naturally, before any damage initiates. With efficient nonlinear finite element analyses, the initial buckling and post-buckling deformations of these panels may be predicted [5]. However, the analytical methods to predict failure of the panel are less efficient, and hence, panels are invariably tested to evaluate design and determine failure load.…”

Section: Introductionmentioning

confidence: 99%

Local fracture mechanics analysis of stringer pull-off and delamination in a post-buckled compression panel

Martin¹

1996

Appl Compos Mater

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This paper describes some of the current global/local testing and analysis approaches to evaluating the design of composite structure. A case study for the local, fracture mechanics analysis of failure in a 4-stringer compression panel is described in detail. The analysis investigates the variation of strain energy release rate G with debond length using a 2-D plane strain finite element analysis (FEA) of one of the stringers. The boundary conditions on the local model were determined from a global shell element model of the panel. Delamination was also modelled in the cap of the stringer using FEA and a closed form solution. The values of G for these two damage modes were compared with the material's fracture toughness. Using this analysis, the load to initiate the stringer debond and to cause edge delamination of the cap may be determined.

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“…Many theoretical and experimental studies have been performed on buckling and postbuckling behavior of flat stiffened composite panels (see for example [Frostig et al 1991;Segal et al 1987;Starnes et al 1985;Vestergen and Knutsson 1978;Romeo 1986;Bucci and Mercuria 1992]). A wide body of descriptions and detailed data on buckling and postbuckling tests was compiled in [Singer et al 2002] (see chapters [12][13][14].…”

Section: Introductionmentioning

confidence: 99%

Buckling and postbuckling behavior of laminated composite stringer stiffened curved panels under axial compression: Experiments and design guidelines

Abramovich¹,

Weller²

2009

J. Mech. Solids Struct.

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An extensive test series on circular cylindrical laminated composite stringer-stiffened panels subjected to axial compression, shear loading introduced by shear and combined axial compression and shear was carried out at the Technion, Israel. The test program was an essential part of an ongoing effort undertaken by the POSICOSS project (improved postbuckling simulation for design of fibre composite stiffened fuselage structures) aiming at design of low cost, low weight airborne structures that was initiated and supported by the Fifth European Initiative Program.The first part of this test series, dealing with panels PSC1-PSC9 (blade-stiffened), has already been summarized and published. The results of the tests with panels BOX1-BOX4 (blade-and J-stiffened) have also been reported and published. These tests dealt with two identical stiffened panels, combined together by two flat nonstiffened aluminum webs, to form a torsion box, thus enabling application of shear tractions, through introduction of torsion, and combined axial compression and shear. The present manuscript aims at describing test results and relevant numerical studies on the buckling and postbuckling behavior of another set of four panels, AXIAL1-AXIAL4, stiffened by J-type stringers. Based on the experimental studies carried out within the framework of the POSICOSS project and reported in the literature and on the present study design guidelines were formulated and presented. Accompanying supporting calculations were presented as well; they were performed with a "fast" calculation tool developed at the Technion, and based on the effective width method modified to handle laminated circular cylindrical stringer-stiffened composite panels.

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Postbuckling behavior of selected flat stiffened graphite-epoxy panels loaded in compression

Cited by 100 publications

References 7 publications

Improving strength of postbuckled panels through stitching

Improving strength of postbuckled panels through stitching

Local fracture mechanics analysis of stringer pull-off and delamination in a post-buckled compression panel

Buckling and postbuckling behavior of laminated composite stringer stiffened curved panels under axial compression: Experiments and design guidelines

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