Buckling behavior of compression-loaded quasi-isotropic curved panels with a circular cutout

Mark, W Hilburger; Vicki, O Britt; Michael, P Nemeth

doi:10.1016/s0020-7683(00)00114-1

Cited by 45 publications

(17 citation statements)

References 13 publications

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“…This prebuckling outward deformation response has been shown to cause a significant increase in the buckling load, e.g., in some cases greater than twice the predicted linear bifurcation buckling load, and a nonlinear load-end-shortening response 7 . In contrast, the circumferentially stiff laminates and the two angle-ply laminates presented here do not exhibit the nonlinear load-end-shortening response curves or large magnitude buckling loads as observed in the corresponding quasi-isotropic panels.…”

Section: A [90 2 / ±45] 3s [±60] 6s and [+60 6 / -60 6 ] S Laminatesmentioning

confidence: 97%

“…However, it has been shown that curved panels can also be very sensitive to mismatches between the panel and fixture geometries, the magnitude of elastic edge restraints along the loaded edges, and the selection of knife edges that are sometimes used to simulate test-fixtureinduced in-plane friction effects and rotational restraints 6 . Previous testing of curved quasi-isotropic panels demonstrated that some panels exhibit larger magnitude prebuckling out-of-plane deformations and buckling loads than those predicted using finite-element analysis 7 . It was suggested by the author that this observed difference in the test and analysis results was primarily caused by test-fixture-induced friction along the clamped end creating circumferential restraint.…”

Section: Introductionmentioning

confidence: 95%

“…The work presented by Thornburgh and Hilburger 14 and Hilburger et al 7 illustrated the effect of the loaded edge boundary condition on the buckling response of compression-loaded curved quasi-isotropic panels. Similar behavioral characteristics can be clearly seen in the results for the axially stiff panel with no cutout, as shown in Figure 14.…”

Section: A Effects Of the Loaded Edge Boundary Conditionmentioning

confidence: 99%

“…Multiple authors have studied the effects of rectangular cutouts on the buckling response of compression-loaded composite panels [8][9][10][11] . Several studies also appear in the literature that illustrate the effects of a circular cutout on the buckling response of compression-loaded curved panels constructed from aluminum 12 and a quasi-isotropic graphite-epoxy laminated composite 7 . Both of these works indicated that the circular cutout size greatly affects the buckling characteristics of curved panels.…”

Section: Introductionmentioning

confidence: 99%

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A Numerical and Experimental Study of Compression-Loaded Composite Panels with Cutouts

Thornburgh¹,

Hilburger²

2006

47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

2
0
1
0

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Results from a numerical and experimental study on the effects of laminate orthotropy and circular cutout size on the response of compression-loaded composite curved panels are presented.Several 60-in-radius composite panels with four different laminate configurations were tested with cutout diameters that range from 10% to 60% of the panel width. Finite-element analyses were performed for each panel in order to identify the effects boundary conditions, measured initial geometric imperfections and thickness variations had on the nonlinear and buckling behavior of the panels. The compression-loaded panels considered herein exhibited two separate types of behavior depending on the laminate stacking sequence and cutout size. More specifically, some of the panels exhibited the classical "snap-through" type buckling response; however, some of the panels exhibited a monotonically increasing stable response and achieved compressive loads in excess of twice the predicted linear bifurcation buckling load. In general, the finite-element analyses were able to predict accurately the nonlinear response and buckling loads of the panels and the prebuckling and postbuckling out-of-plane deformations and strains.

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Section: A [90 2 / ±45] 3s [±60] 6s and [+60 6 / -60 6 ] S Laminatesmentioning
confidence: 97%

Section: Introductionmentioning
confidence: 95%

Section: A Effects Of the Loaded Edge Boundary Conditionmentioning
confidence: 99%

Section: Introductionmentioning
confidence: 99%

See 2 more Smart Citations
A Numerical and Experimental Study of Compression-Loaded Composite Panels with Cutouts
Thornburgh¹,
Hilburger²
2006
47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
2
0
1
0
View full text Add to dashboard Cite
Results from a numerical and experimental study on the effects of laminate orthotropy and circular cutout size on the response of compression-loaded composite curved panels are presented.Several 60-in-radius composite panels with four different laminate configurations were tested with cutout diameters that range from 10% to 60% of the panel width. Finite-element analyses were performed for each panel in order to identify the effects boundary conditions, measured initial geometric imperfections and thickness variations had on the nonlinear and buckling behavior of the panels. The compression-loaded panels considered herein exhibited two separate types of behavior depending on the laminate stacking sequence and cutout size. More specifically, some of the panels exhibited the classical "snap-through" type buckling response; however, some of the panels exhibited a monotonically increasing stable response and achieved compressive loads in excess of twice the predicted linear bifurcation buckling load. In general, the finite-element analyses were able to predict accurately the nonlinear response and buckling loads of the panels and the prebuckling and postbuckling out-of-plane deformations and strains.
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“…Hilburger et al [7] conducted investigations in composite curved panels with cutouts. The study is focused in the effect of a centrally located circular cutout on the buckling load of curved panels under axial compression with fixed laminate.…”

Section: Introductionmentioning
confidence: 99%

Investigation of Buckling Behavior of Composite Shell Structures with Cutouts
Arbelo
¹
,
Herrmann
²
,
Castro
³

et al. 2014
Appl Compos Mater
38
0
8
0
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Thin-walled cylindrical composite shell structures can be applied in space applications, looking for lighter and cheaper launcher transport system. These structures are prone to buckling under axial compression and may exhibit sensitivity to geometrical imperfections. Today the design of such structures is based on NASA guidelines from the 1960's using a conservative lower bound curve generated from a database of experimental results. In this guideline the structural behavior of composite materials may not be appropriately considered since the imperfection sensitivity and the buckling load of shells made of such materials depend on the lay-up design. It is clear that with the evolution of the composite materials and fabrication processes this guideline must be updated and / or new design guidelines investigated. This need becomes even more relevant when cutouts are introduced to the structure, which are commonly necessary to account for access points and to provide clearance and attachment points for hydraulic and electric systems. Therefore, it is necessary to understand how a cutout with different dimensions affects the buckling load of a thin-walled cylindrical shell structure in combination with other initial geometric imperfections. In this context, this paper present some observations regarding the buckling load behavior vs. cutout size and radius over thickness ratio, of laminated composite curved panels and cylindrical shells, that could be applied in further recommendations, to allow identifying when the buckling of the structure is dominated by the presence of the cutout or by other initial imperfections.

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A mesh-free method for analysis of the thermal and mechanical buckling of functionally graded cylindrical shell panels
Zhao
¹
,
Liew
²

2009
Comput Mech
52
3
19
0
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The buckling response of functionally graded ceramic-metal cylindrical shell panels under axial compression and thermal load is presented here. The formulation is based on the first-order shear deformation shell theory and element-free kp-Ritz method. The material properties of shell panels are assumed to vary through their thickness direction according to a power-law distribution of the volume fraction of constituents. Approximations of the displacement field are expressed in terms of a set of mesh-free kernel particle functions. A stabilized conforming nodal integration approach is employed to estimate the bending stiffness, and the shear and membrane terms are evaluated using a direct nodal integration technique to eliminate membrane and shear locking for very thin shells. The mechanical and thermal buckling responses of functionally graded shell panels are investigated, and the influences of the volume fraction exponent, boundary conditions, and temperature distribution on their buckling strengths are also examined.

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Buckling behavior of compression-loaded quasi-isotropic curved panels with a circular cutout

Cited by 45 publications

References 13 publications

A Numerical and Experimental Study of Compression-Loaded Composite Panels with Cutouts

A Numerical and Experimental Study of Compression-Loaded Composite Panels with Cutouts

Investigation of Buckling Behavior of Composite Shell Structures with Cutouts

A mesh-free method for analysis of the thermal and mechanical buckling of functionally graded cylindrical shell panels

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