Parametric Investigation of Stiffened Panel Subjected to Compressive Loads: Influence of Initial Delamination Length on Damage Behaviour

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. 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.