A semi-analytical model for local post-buckling analysis of stringer- and frame-stiffened cylindrical panels

A fast semi-analytical model for the post-buckling analysis of stiffened cylindrical panels is presented. The panel is comprised of a skin (shell) and stiffeners in both longitudinal (stringers) and circumferential direction (frames). Local buckling modes are considered where the skin may buckle wit...

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Veröffentlicht in:Thin-walled structures Jg. 44; H. 1; S. 102 - 114
Hauptverfasser: Buermann, Philipp, Rolfes, Raimund, Tessmer, Jan, Schagerl, Martin
Format: Journal Article
Sprache:Englisch
Veröffentlicht: Oxford Elsevier Ltd 2006
New York, NY Elsevier Science
Schlagworte:
Buckling
Exact sciences and technology
Fundamental areas of phenomenology (including applications)
Large deflection theory
Local buckling model
Panel buckling
Physics
Post-buckling
Semi-analytical
Solid mechanics
Stiffened cylindrical shell
Structural and continuum mechanics
Post-buckling
Large deflection theory
Local buckling model
Panel buckling
Semi-analytical
Stiffened cylindrical shell
High strain
Localized mode
Displacement(deformation)
Modeling
Energy level
Trigonometric series
Structural frame
Local buckling
Defect
Eigenvalue problem
Buckling
Civil engineering
Stiffener
Eigenmode
Frame construction
Mechanical properties
Fourier series
Postbuckling
Reinforced structure
Reinforced shell
Trigonometric function
Cylindrical shell
Non linear effect
Aircraft
ISSN:0263-8231, 1879-3223
Online-Zugang:Volltext
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Beschreibung
Zusammenfassung:A fast semi-analytical model for the post-buckling analysis of stiffened cylindrical panels is presented. The panel is comprised of a skin (shell) and stiffeners in both longitudinal (stringers) and circumferential direction (frames). Local buckling modes are considered where the skin may buckle within a bay and may induce rotation of the stiffeners. Stringers and frames are considered as structural elements and are thus not ‘smeared’ onto the skin. Large out-of-plane deflections and thus non-linear strain–displacement relations of skin and stiffeners are taken into account. The displacements of skin and stiffeners are approximated by trigonometric functions (Fourier series). First, a linear buckling eigenvalue analysis is carried out and some combination of buckling eigenmodes is chosen as imperfection. Then the load history is started and the Fourier coefficients are determined by minimizing the stiffened panel's energy at each load level. A curve-tracing algorithm, the Riks method, is used to solve the equations. The present model can be used to assess the post-buckling behavior of stiffened panels, for example, aircraft fuselage sections.
Bibliographie:ObjectType-Article-2
SourceType-Scholarly Journals-1
ObjectType-Feature-1
content type line 23
ISSN:0263-8231
1879-3223
DOI:10.1016/j.tws.2005.08.010