PSI - Issue 52

ScienceDirect Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2022) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2022) 000 – 000 Available online at www.sciencedirect.com Procedia Structural Integrity 52 (2024) 535–542

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www.elsevier.com/locate/procedia

2452-3216 © 2023 The Authors. Published by ELSEVIER B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of Professor Ferri Aliabadi 10.1016/j.prostr.2023.12.053 2452-3216 © 2023 The Authors. Published by ELSEVIER B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of Professor Ferri Aliabadi 2452-3216 © 2023 The Authors. Published by ELSEVIER B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of Professor Ferri Aliabadi * Corresponding author. Tel.: +39 081 5010 407. E-mail address: angela.russo@unicampania.it © 2023 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of Professor Ferri Aliabadi The findings of this investigation highlight the intricate relationship between the mechanical response of the panel and the initial delamination length. By systematically altering this parameter, variations in the panel ’ s damage behaviour can be observed. This study provides valuable insights into the influence of the initial delamination length on the overall damage characteristics of stiffened panels, contributing to a deeper understanding of the mechanics involved in such composite structures. These insights are essential for optimizing the design while ensuring the structural integrity of stiffened panels in engineering applications. The findings of this investigation highlight the intricate relationship between the mechanical response of the panel and the initial delamination length. By systematically altering this parameter, variations in the panel ’ s damage behaviour can be observed. This study provides valuable insights into the influence of the initial delamination length on the overall damage characteristics of stiffened panels, contributing to a deeper understanding of the mechanics involved in such composite structures. These insights are essential for optimizing the design while ensuring the structural integrity of stiffened panels in engineering applications. Keywords: Composite materials; Finite element analysis; Experimental tests; Impact analysis. 1. Introduction The aerospace industry has been revolutionized by the use of composite materials. Composites are materials made of two or more distinct components, such as fibres and resins, which when combined form a strong, lightweight material. This material is ideal for use in aerospace applications, as it is strong enough to withstand the rigors of flight Fracture, Damage and Structural Health Monitoring Parametric Investigation of Stiffened Panel Subjected to Compressive Loads: Influence of Initial Delamination Length on Damage Behaviour Angela Russo*, Andrea Sellitto, Concetta Palumbo, Rossana Castaldo, Aniello Riccio University of Campania “Luigi Vanvitelli”, Department of Engineering, via Roma, 29, Aversa (CE), 81031, Italy Abstract This paper presents a comprehensive investigation on the behaviour of a stiffened panel under compressive loads, focusing on the impact of the initial delamination length on the damage onset and evolution. To achieve this, a finite element model has been developed, representing a single stiffened composite panel. This model has been designed considering varying lengths of the initially delaminated area between the skin and stringer components. The numerical analysis employed the SMXB approach, a method based on the Virtual Crack Closure Technique (VCCT), and characterized by load-step and mesh independency. Fracture, Damage and Structural Health Monitoring Parametric Investigation of Stiffened Panel Subjected to Compressive Loads: Influence of Initial Delamination Length on Damage Behaviour Angela Russo*, Andrea Sellitto, Concetta Palumbo, Rossana Castaldo, Aniello Riccio University of Campania “Luigi Vanvitelli”, Department of Engineering, via Roma, 29, Aversa (CE), 81031, Italy Abstract This paper presents a comprehensive investigation on the behaviour of a stiffened panel under compressive loads, focusing on the impact of the initial delamination length on the damage onset and evolution. To achieve this, a finite element model has been developed, representing a single stiffened composite panel. This model has been designed considering varying lengths of the initially delaminated area between the skin and stringer components. The numerical analysis employed the SMXB approach, a method based on the Virtual Crack Closure Technique (VCCT), and characterized by load-step and mesh independency. Keywords: Composite materials; Finite element analysis; Experimental tests; Impact analysis. 1. Introduction The aerospace industry has been revolutionized by the use of composite materials. Composites are materials made of two or more distinct components, such as fibres and resins, which when combined form a strong, lightweight material. This material is ideal for use in aerospace applications, as it is strong enough to withstand the rigors of flight * Corresponding author. Tel.: +39 081 5010 407. E-mail address: angela.russo@unicampania.it