Analytical prediction model for fatigue crack growth in Fibre Metal Laminates with MSD scenario

Journal article (2017)

Authors

W. Wang Structural Integrity & Composites - Aerospace Engineering
C.D. Rans Structural Integrity & Composites - Aerospace Engineering
R. Benedictus Aerospace Structures & Materials
Research Group
Structural Integrity & Composites (Aerospace Engineering) (TU Delft)
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Published Date

01-11-2017

Language

English

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Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Structural Integrity & Composites

Abstract

This paper presents a theoretical and experimental study on Multiple-site Damage (MSD) crack growth behaviour in Fibre Metal Laminates (FMLs). The prediction model is developed based on a simplified analysis of the effects of load redistribution on a single crack in FMLs containing multiple cracks. Test results show that the crack growth accelerates as cracks grow towards each other. The tests also show non-symmetric crack growth behaviour and non-symmetric interfacial delamination propagation in case of multiple cracks. The prediction model successfully captures the crack growth acceleration and non-symmetric growth behaviour.

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