Durability of stiffened CFRP panels with initial delaminations

Master thesis (2018)

Authors

D.J.H. Cederløf Aerospace Engineering

Contributors

C. Kassapoglou (mentor)
R. Benedictus (graduation committee member)
C.D. Rans (graduation committee member)
M.V. Donadon (graduation committee member)
Faculty
Aerospace Engineering, Aerospace Engineering
Copyright: © 2018 Daan Cederløf
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Published Date

02-07-2018

Language

English

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Faculty

Aerospace Engineering

Abstract

A numerical fatigue delamination model is validated by means of experimental tests. Delamination is initiated on the skin-stiffener interface which, under cyclic compressive loading and in the post-buckling regime, grows at a decreasing rate. A cohesive zone formulation is used to model the static and fatigue delamination growth, good agreement is found in terms of delamination shape. Further investigation is required, using improved material inputs, for the model to be validated in terms of delamination magnitude. The numerical model shows promising characteristics, which may be employed for future damage tolerant composite structural designs.