Assessment of the Damage Tolerance of Post-Buckled Hat-Stiffened Panels using Single Stringer Specimens | Zendy

Chiara Bisagni | Zendy; Riccardo Vescovini | Zendy; Carlos G. Dávila | Zendy

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Assessment of the Damage Tolerance of Post-Buckled Hat-Stiffened Panels using Single Stringer Specimens

Author(s) -

Chiara Bisagni,

Riccardo Vescovini,

Carlos G. Dávila

Publication year - 2010

Publication title -

nasa sti repository (national aeronautics and space administration)

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.2010-2696

Subject(s) - stringer , damage tolerance , structural engineering , delamination (geology) , materials science , finite element method , compression (physics) , nonlinear system , composite number , composite material , shell (structure) , engineering , geology , paleontology , physics , subduction , quantum mechanics , tectonics

A procedure is proposed for the assessment of the damage tolerance and collapse of stiffened composite panels using a single-stringer compression specimen. The dimensions of the specimen are determined such that the specimen’s nonlinear response and collapse are representative of an equivalent multi-stringer panel in compression. Experimental tests are conducted on specimens with and without an embedded delamination. A shell-based finite element model with intralaminar and interlaminar damage capabilities is developed to predict the postbuckling response as well as the damage evolution from initiation to collapse.

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