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Title: Optimum design and testing of a postbuckled stiffened panel
Authors: Lillico, M.
Butler, R.
Hunt, G.W.
Watson, Andrew
Kennedy, David
Williams, F.W.
Issue Date: 2000
Publisher: © American Institute of Aeronautics and Astronautics (AIAA)
Citation: LILLICO, M. ... et al., 2000. Optimum design and testing of a postbuckled stiffened panel. IN: 41st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Atlanta, April 3-6, 8pp.
Series/Report no.: AIAA;2000-1659
Abstract: The efficient, industrially used, linear elastic preliminary design software VICONOPT is employed to design a stiffened panel with a post-buckled reserve of strength. The initial buckling mode is a local skin mode in longitudinal compression with allowance being made for the effects of an initial overall imperfection. The resulting panel has been analyzed using the non-linear FE package ABAQUS and four laboratory specimens have been tested to failure. The similarity of the experimental failure with the VICONOPT and ABAQUS predictions suggests that VICONOPT can give a satisfactory preliminary design. While neither model matches completely the boundary conditions found in a real aircraft compression panel, it is suggested that the VICONOPT model may be a better representation than either the ABAQUS model or the experimental tests.
Description: This is a conference paper. It was presented at the 41st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference [© AIAA]. The definitive published version can be found at: http://www.aiaa.org/content.cfm?pageid=2
Version: Accepted for publication
URI: https://dspace.lboro.ac.uk/2134/8677
Publisher Link: http://www.aiaa.org/content.cfm?pageid=2
ISBN: 1563474352
Appears in Collections:Conference Papers and Presentations (Aeronautical and Automotive Engineering)

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