Prediction methodology for fatigue crack growth behaviour in Fibre Metal Laminates subjected to tension and pin loading

Journal article (2017)

Authors

W. Wang Structural Integrity & Composites - Aerospace Engineering
C.D. Rans Structural Integrity & Composites - Aerospace Engineering
Z. Zhang The First Aircraft Design and Research Institute of AVIC
R. Benedictus Aerospace Structures & Materials
Research Group
Structural Integrity & Composites (Aerospace Engineering) (TU Delft)
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Published Date

15-12-2017

Language

English

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Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Structural Integrity & Composites

Abstract

Fibre Metal Laminates (FMLs) are a hybrid metal-composite laminate technology known for their superior resistance to fatigue crack growth compared to monolithic metals. This crack growth behaviour has been the subject of many studies, resulting in numerous empirical and analytical models to describe the complex damage growth phenomenon in the material. This study builds upon the analytical Alderliesten crack growth prediction methodology for FMLs, extending it from a tension loaded plate to a case of a combined tension-pin loaded plate. This new loading case is a more representative case to utilise for predicting fatigue crack growth behaviour in mechanically fastened joints. Development of the model extension and validation through experimental testing are detailed within this paper.

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