File(s) under permanent embargo
Reason: This item is currently closed access.
Postbuckling of stiffened panels using strut, strip, and finite element methods
journal contribution
posted on 2011-10-05, 11:21 authored by M. Lillico, R. Butler, G.W. Hunt, Andrew WatsonAndrew Watson, David KennedyPostbuckling results are presented for isotropic stiffened panels loaded in compression. Comparisons are made
between single-bay and double-bay nite element (FE) models (where “bay” denotes a repeating portion, between
supports, in the load/length direction) and a new strut model, following a Shanley-type approach, for single-bay
and multibay panels. The strut model has been incorporated within the strip programVIPASA with CONstraints
and OPTimization (VICONOPT) to design a multibay example panel with postbuckling reserve of strength in its
skins, assuming linear elastic material properties. The panel has been shown by VICONOPT to have a stiffener
buckling failuremode when an overall sinusoidal imperfection causing increased stiffener compression is present.
The failure is con rmed by the double-bay FE model, which is shown to be an imperfect representation of the
multibay case. Single-bay analysis using the strut model shows good agreement with the single-bay FE results.
The VICONOPT code is able to design a metallic panel of realistic dimensions and loading using 50 strip elements
(compared with the 9600 shell elements required by the nite element model) but cannot correctly account for
material nonlinearity. The important phenomenological difference between postbuckling of single-, double-, and
multibay panel models are indicated.
History
School
- Aeronautical, Automotive, Chemical and Materials Engineering
Department
- Aeronautical and Automotive Engineering
Citation
LILLICO, M.... et al., 2003. Postbuckling of stiffened panels using strut, strip, and finite element methods. AIAA Journal, 41(6), pp. 1172-1179Publisher
© American Institute of Aeronautics and Astronautics (AIAA)Version
- NA (Not Applicable or Unknown)
Publication date
2003Notes
This article is closed access. It was published in the AIAA Journal [© American Institute of Aeronautics and Astronautics] and is available from: http://www.aiaa.org/content.cfm?pageid=318ISSN
0001-1452;1533-385XPublisher version
Language
- en