Numerical Modelling of Skin-Stringer Separation in Thermoplastic Composite Stiffened Panels

Master thesis (2024)

Authors

A. Malladi Aerospace Engineering

Contributors

S.R. Turteltaub Group Turteltaub - Aerospace Engineering (supervisor 1)
C. Bisagni Group Bisagni - Aerospace Engineering (supervisor 1)
R.C. Alderliesten Group Alderliesten - Aerospace Engineering (supervisor 2)
Bianca Giovanardi Group Giovanardi - Aerospace Engineering (supervisor 2)
Faculty
Aerospace Engineering
Copyright: © 2024 Avyadhish Malladi
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Published Date

22-02-2024

Language

English

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Faculty

Aerospace Engineering

Abstract

This thesis project focuses on the evaluation of the Extended Finite Element Model (XFEM) for modelling skin-stringer separation in thermoplastic composite stiffened panels. The study uses test results from a reference study in the literature on a PEKK-FC carbon composite panel with three stringers joined to the skin using a short-fibre reinforced butt joint. The modelling strategy was developed using Double Cantilever Beam (DCB) specimens. The XFEM-based panel models were then developed using two different damage initiation criteria: Quadratic Stress Criterion (QUADS) and Maximum Principal Stress Criterion (MAXPS). These models were compared with the Virtual Crack Closure Technique (VCCT) model from the reference study. The project also addresses the challenges posed by the crack tip impingement problem in the XFEM-based model with MAXPS and tests different strategies to overcome it. A proof of concept is provided for using the UDMGINI subroutine to address these challenges, setting the stage for future studies and algorithm development.