Paper number 188
|POSTBUCKLING FAILURE OF A BLADE-STIFFENED CARBON-EPOXY COMPRESSION PANEL|
B.G. Falzon1, K.A. Stevens2, M. Goia3 and G.A.O. Davies4
1,2,4 Department of Aeronautics, Imperial College of Science, Technology and Medicine, Prince Consort Road, London SW7 2BY, U.K.
3 Dipartimento di Ingegneria Aeronautica e Spaziale, Politecnico di Torino,
Corso Duca degli Abruzzi, 24 - 10129, Torino, Italia.
|Summary||The failure of postbuckled panels with blade-stiffeners has been studied experimentally. A new failure mechanism was identified for this particular type of stiffener where failure is initiated by a critical shear stress in the web. This shear stress was calculated from strain gauge measurements using lamination theory and incorporating edge effects. The critical shear stress was found to agree with the shear strength obtained from a three-point bending test of the web laminate.
||Keywords|| buckling, postbuckling, failure, stiffened carbon-epoxy panel, axial compression.
Theme : Mechanical and Physical Properties ; Simulation
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