Next Article in Journal
Microstructure and Compressive Behavior of Al–Y2O3 Nanocomposites Prepared by Microwave-Assisted Mechanical Alloying
Previous Article in Journal
Effect of Artificial Defects on the Very High Cycle Fatigue Behavior of 316L Stainless Steel
Previous Article in Special Issue
Characterization of Local Residual Stress at Blade Surfaces by the V(z) Curve Technique
Article Menu
Issue 4 (April) cover image

Export Article

Open AccessArticle

Blunt Notch Strength of AA2024 3-3/2-0.4 Fibre Metal Laminate Under Biaxial Tensile Loading

1
German Aerospace Center, Institute of Materials Research, 51147 Cologne, Germany
2
Airbus Operations GmbH, 21129 Hamburg, Germany
3
Metallic Structures and Materials Systems for Aerospace Engineering, RWTH Aachen University, 52062 Aachen, Germany
*
Author to whom correspondence should be addressed.
Metals 2019, 9(4), 413; https://doi.org/10.3390/met9040413
Received: 18 March 2019 / Revised: 28 March 2019 / Accepted: 1 April 2019 / Published: 5 April 2019
(This article belongs to the Special Issue Modern Aerospace Materials)
  |  
PDF [5533 KB, uploaded 5 April 2019]
  |  

Abstract

Fibre metal laminates are utilized in lightweight structures, such as aircraft fuselages, as fibre metal laminates provide outstanding fatigue and damage tolerance capabilities, together with a reduced weight compared to monolithic metallic structures. One critical feature of fuselage structures is their strength reduction that owes to riveting, i.e., a state-of-the-art joining technique in aircrafts. In the present work, the blunt notch strength of fibre-laminate panels with rivet holes is investigated under service-relevant biaxial loading conditions. To this purpose, cruciform specimens with a five-hole pattern were produced. These specimens were tested under various biaxiality ratios and fibre orientations. All tests were supported by three-dimensional digital image correlation to obtain the deformation field in the gauge area. Moreover, the displacement fields obtained during deformation were used in an elasto-plastic finite element model as boundary conditions to determine the maximum strains in the vicinity of the blunt notch holes and thus extend the application of the experimental results. The asymmetric strain fields obtained by digital image correlation reveal the interaction of the fibres with the blunt notch holes. Finally, it is shown that the biaxial loading conditions do not significantly influence the blunt notch strength. View Full-Text
Keywords: fibre metal laminate; blunt notch strength; biaxial testing; finite element fibre metal laminate; blunt notch strength; biaxial testing; finite element
Figures

Figure 1

This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited (CC BY 4.0).
SciFeed

Share & Cite This Article

MDPI and ACS Style

Schwinn, J.; Breitbarth, E.; Beumler, T.; Requena, G. Blunt Notch Strength of AA2024 3-3/2-0.4 Fibre Metal Laminate Under Biaxial Tensile Loading. Metals 2019, 9, 413.

Show more citation formats Show less citations formats

Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.

Related Articles

Article Metrics

Article Access Statistics

1

Comments

[Return to top]
Metals EISSN 2075-4701 Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
Back to Top