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This and the next image are from:
V. Weissberg, T. Genosar and G. Ghilai (Engineering and Development Group, IAI Ben Gurion A.P, Israel), “Instability and collapse of sandwich shells representing A/C wing skins”, (publisher and date not given in the pdf file. The most recent citation is dated 2005. The photograph in the next slide includes a date, “28/02/2008”.)
ABSTRACT: Instability failure mode of nearly cylindrical sandwich shell was investigated by theoretical calculation. Finite Element Analysis and finally verified by two test specimens. During the test, information regarding snap-though, buckling mode and post buckling behaviour were collected. These indications were obtained by using the F/S method.
PARTIAL INTRODUCTION: The instability and the failure mode of nearly cylindrical sandwich shells, loaded in torsion, were investigated by theoretical calculation, Finite Element Analysis and verified by three parametric test specimens. Limited studies on composite wing boxes have been reported (Ref. 1-3), but they are all for solid laminate skins and none for thin composite sandwich shell skins. The purpose of this work was to develop a method for the analysis for the prediction of instability (buckling) and collapse (failure) of lightweight sandwich shells. The results are to be used in the design of GA (general aviation) structures.
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