PSI - Issue 24

Available online at www.sciencedirect.com Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2019) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2019) 000 – 000

www.elsevier.com/locate/procedia www.elsevier.com/locate/procedia

ScienceDirect

Procedia Structural Integrity 24 (2019) 279–288

© 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Peer-review under responsibility of the AIAS2019 organizers In this work, a numerical analysis of the buckling behavior of a panel in CFRP with longitudinal and transverse stiffeners is reported. The focus was to evaluate the influence of damage at the center of the panel, simulated with a cut that affects the central stringer and the underlying skin. Two FEM models have been created: one with damage and the other intact. The numerical models reproduce the component to estimate the axial rigidity, the deformation field and the unstable behavior before buckling. Experimental tests were carried out using a test facility for medium-sized structural elements on a real damaged component with saw-cut. Two comparisons have been made. In a first comparison, the experimental campaign confirmed the results of the numerical model performed for a damaged component. Subsequently, a comparison between numerical cases was made. The influence of damage on the buckling load and on the axial stiffness was evaluated. © 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Peer-review under responsibility of the AIAS2019 organizers In this work, a numerical analysis of the buckling behavior of a panel in CFRP with longitudinal and transverse stiffeners is reported. The focus was to evaluate the influence of damage at the center of the panel, simulated with a cut that affects the central stringer and the underlying skin. Two FEM models have been created: one with damage and the other intact. The numerical models reproduce the component to estimate the axial rigidity, the deformation field and the unstable behavior before buckling. Experimental tests were carried out using a test facility for edium-sized structural elements on a real da aged component with saw-cut. Two comparisons have been made. In a first comparison, the experimental campaign confirmed the results of the numerical model performed for a damaged component. Subsequently, a comparison between numerical cases was made. The influence of damage on the buckling load and on the axial stiffness was evaluated. © 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Peer-review under responsibility of the AIAS2019 organizers AIAS 2019 International Conference on Stress Analysis Experimental behavior of a CFRP damaged panel subjected to compressive stress Alessandro Castriota a *, Vito Dattoma a , Benedetto Gambino b , Riccardo Nobile a , Andrea Saponaro a AIAS 2019 International Conference on Stress Analysis Experimental behavior of a CFRP damaged panel subjected to compressive stress Alessandro Castriota a *, Vito Dattoma a , Benedetto Gambino b , Riccardo Nobile a , Andrea Saponaro a a Università del Salento - Dipartimento di Ingegneria dell’Innovazione, Via per Monteroni, 73100 Lecce b Leonardo Aircraft SpA – Airframe, Structure Technologies, Zona ASI Incoronata – 81100 Foggia - Italia a Università del Salento - Dipartimento di Ingegneria dell’Inn v zione, Via per Monteroni, 73100 Lecce b Leonardo Aircraft SpA – Airframe, Structure Technologies, Zona ASI Incoronata – 81100 Foggia - Italia Abstract Abstract

Keywords: CFRP; stiffness; reinforced panel; stringers; buckling; saw-cut Keywords: CFRP; stiffness; reinforced panel; stringers; buckling; saw-cut

1. Introduction 1. Introduction

In the aeronautical and aerospace field, the use of innovative materials such as composite materials is In the aeronautical and aerospace field, the use of innovative materials such as composite materials is

* Corresponding author. Tel.: +39 0832 297786; fax: +39 0832 297768. E-mail address: alessandro.castriota@unisalento.it * Corresponding author. Tel.: +39 0832 297786; fax: +39 0832 297768. E-mail address: alessandro.castriota@unisalento.it

2452-3216 © 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Peer-review under responsibility of the AIAS2019 organizers 2452-3216 © 2019 The Authors. Published by Elsevier B.V. This is an ope access article under t CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Peer-review under responsibility of the AIAS2019 organizers

2452-3216 © 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Peer-review under responsibility of the AIAS2019 organizers 10.1016/j.prostr.2020.02.025