Archivio Istituzionale della RicercaThe aim of this work is the study of the influence of a large notch damage in a stiffened aeronautical panel. In particular, the damage onset and evolution due to a cut-out located in the bay of an omega stiffened composite panel subjected to a compressive load is investigated. Three different cut-outs are considered: parallel, normal, and 45° oriented respect to the load. The effects of such configurations are compared in terms of fibre and matrix failures, in order to better understand which configuration is the most sensitive to these type of damages.
Large Notch Damage Evolution in Omega Stiffened Composite Panels / Riccio, A.; Sellitto, A.; Saputo, S.; Russo, A.; Antonucci, V.; Ricciardi, M. R.; Zarrelli, M.; Lopresto, V.. - In: PROCEDIA ENGINEERING. - ISSN 1877-7058. - 167:(2016), pp. 151-159. (Intervento presentato al convegno International Symposium on Dynamic Response and Failure of Composite materials, DRAF 2016 tenutosi a ISCHIA nel 2016) [10.1016/j.proeng.2016.11.682].
Large Notch Damage Evolution in Omega Stiffened Composite Panels
Saputo S.;
2016
Abstract
The aim of this work is the study of the influence of a large notch damage in a stiffened aeronautical panel. In particular, the damage onset and evolution due to a cut-out located in the bay of an omega stiffened composite panel subjected to a compressive load is investigated. Three different cut-outs are considered: parallel, normal, and 45° oriented respect to the load. The effects of such configurations are compared in terms of fibre and matrix failures, in order to better understand which configuration is the most sensitive to these type of damages.
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https://hdl.handle.net/11583/2979154