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Title: Buckling load reduction for stiffened panels due to cutouts in ribs
Authors: Watson, Andrew
Williams, F.W.
Kennedy, David
Issue Date: 1998
Publisher: © American Institute of Aeronautics and Astronautics (AIAA)
Citation: WATSON, A., WILLIAMS, F.W. and KENNEDY, D., 1998. Buckling load reduction for stiffened panels due to cutouts in ribs. AIAA Journal, 36(2), pp. 264-266
Abstract: In aerospace structures it is common to find stiffened panels with transverse supporting structures, e.g. wing ribs or fuselage frames. Incorporating cutouts into these supporting structures to allow the stringers to pass through freely considerably reduces the buckling load of the panels. It is shown that a minor modification in the fabrication of the stiffened panel gives most of the advantages of cutouts while still giving a buckling load close to that of a panel with no cutouts.
Version: Accepted for publication
URI: https://dspace.lboro.ac.uk/2134/8694
Publisher Link: http://www.aiaa.org/content.cfm?pageid=318&volume=36&issue=2&pubid=2&paperid=7510
ISSN: 0001-1452
Appears in Collections:Published Articles (Aeronautical and Automotive Engineering)

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