An experimental investigation into pin loading effects on fatigue crack growth in Fibre Metal Laminates

Journal article (2016)

Authors

Z. Zhang The First Aircraft Design and Research Institute of AVIC, Structural Integrity & Composites - Aerospace Engineering
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)
Copyright: © 2016 Z. Zhang, W. Wang, C.D. Rans, R. Benedictus
DOI: https://doi.org/10.1016/j.prostr.2016.06.419
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Published Date

2016

Language

English

Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Structural Integrity & Composites

Abstract

This paper provides an experimental investigation into the pin loading effects on the crack growth behaviour in Fibre Metal Laminates. The pin loading effects and bypass loading effects are incorporated in two different tested joints. The analysis of the test results shows that pin loading dominates the crack growth only in the vicinity of the pin hole and the superposition method for analysing stress intensity factor in FMLs with pin loading effects can be applied.