Details
| Original language | English |
|---|---|
| Pages (from-to) | 102-114 |
| Number of pages | 13 |
| Journal | Thin-walled structures |
| Volume | 44 |
| Issue number | 1 |
| Publication status | Published - 14 Nov 2006 |
| Externally published | Yes |
Abstract
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.
Keywords
- Large deflection theory, Local buckling model, Panel buckling, Post-buckling, Semi-analytical, Stiffened cylindrical shell
ASJC Scopus subject areas
- Engineering(all)
- Civil and Structural Engineering
- Engineering(all)
- Building and Construction
- Engineering(all)
- Mechanical Engineering
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In: Thin-walled structures, Vol. 44, No. 1, 14.11.2006, p. 102-114.
Research output: Contribution to journal › Article › Research › peer review
}
TY - JOUR
T1 - A semi-analytical model for local post-buckling analysis of stringer- and frame-stiffened cylindrical panels
AU - Buermann, Philipp
AU - Rolfes, Raimund
AU - Tessmer, Jan
AU - Schagerl, Martin
PY - 2006/11/14
Y1 - 2006/11/14
N2 - 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.
AB - 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.
KW - Large deflection theory
KW - Local buckling model
KW - Panel buckling
KW - Post-buckling
KW - Semi-analytical
KW - Stiffened cylindrical shell
UR - http://www.scopus.com/inward/record.url?scp=32344448334&partnerID=8YFLogxK
U2 - 10.1016/j.tws.2005.08.010
DO - 10.1016/j.tws.2005.08.010
M3 - Article
AN - SCOPUS:32344448334
VL - 44
SP - 102
EP - 114
JO - Thin-walled structures
JF - Thin-walled structures
SN - 0263-8231
IS - 1
ER -