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Please use this identifier to cite or link to this item: https://dspace.lboro.ac.uk/2134/8902

Title: Postbuckling of stiffened panels using strut, strip, and finite element methods
Authors: Lillico, M.
Butler, R.
Hunt, G.W.
Watson, Andrew
Kennedy, David
Issue Date: 2003
Publisher: © American Institute of Aeronautics and Astronautics (AIAA)
Citation: LILLICO, M.... et al., 2003. Postbuckling of stiffened panels using strut, strip, and finite element methods. AIAA Journal, 41(6), pp. 1172-1179
Abstract: Postbuckling 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.
Description: 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=318
Version: Closed access
URI: https://dspace.lboro.ac.uk/2134/8902
Publisher Link: http://www.aiaa.org/content.cfm?pageid=318
ISSN: 0001-1452
1533-385X
Appears in Collections:Closed Access (Aeronautical and Automotive Engineering)

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