Prediction of Fatigue Crack Growth and Damage Directionality in Non-Conventional Fibre Metal Laminates

Master thesis (2019)

Authors

R.F.H. van Maris Aerospace Engineering

Contributors

R.C. Alderliesten Structural Integrity & Composites - Aerospace Engineering (mentor)
J. Sinke Aerospace Manufacturing Technologies - Aerospace Engineering (graduation committee member)
B. Y. Chen Aerospace Structures & Computational Mechanics - Aerospace Engineering (graduation committee member)
Faculty
Aerospace Engineering, Aerospace Engineering
Copyright: © 2019 Rutger van Maris
More Info
expand_more

Published Date

19-07-2019

Language

English

Reuse Rights

Other than for strictly personal use, it is not permitted to download, forward or distribute the text or part of it, without the consent of the author(s) and/or copyright holder(s), unless the work is under an open content license such as Creative Commons.

Faculty

Aerospace Engineering

Abstract

This thesis presents a model that is able to predict fatigue crack growth and damage directionality in non-conventional Fibre Metal Laminates (FMLs) in CentreCracked Tension (CCT) specimens. Non-conventional FMLs encompass all FMLs other than standardised ones such as GLARE. FMLs can be made non-conventional by using multiple fibre types, any fibre orientation, multiple alloy types or thicknesses, or a combination thereof. These characteristics provide much more tailorability than standardised FMLs and thereby extend the applicability of FMLs to, for example, door corner reinforcements and wing structures. Contrary to standardised FMLs, the damage in non-conventional FMLs is non-uniform, necessitating the ability to compute the crack growth rate in the metal layers and the delamination at the metal-fibre interfaces separately.

Files

Thesis.pdf
(pdf | 13.7 Mb)
Unknown license