Low-velocity impact behavior of fiber metal laminates

Nikolaos Tsartsaris, Michele Meo, Ferdinando Dolce, Umberto Polimeno, M Guida, F Marulo

Research output: Contribution to journalArticle

35 Citations (Scopus)

Abstract

The low-velocity impact response of a range of fiber metal laminate (FML) panels was investigated through testing and finite element simulations. The objective of this study was to understand the impact-damage resistance of these novel composites, so that they can be designed optimally for impact-resistant aircraft applications. The FML panels were made up of aluminum alloy 7475 T761 and unidirectional S2 glass/epoxy oriented in a cross-ply configuration. Experimental tests were performed using a free-fall drop dart testing machine. The plate specimens were constrained on a circular edge by the clamping fixture. The shape and the nature of the damage inflicted by impact were evaluated using both destructive cross-sectional microphotography and nondestructive ultrasonic techniques. The tests showed that FML laminates are capable of absorbing energy through localized plastic deformation and through failure at the interface between the layers. In particular, delaminations occurred in the back face of the aluminum-alloy sheet and its adjacent fiber-reinforced epoxy layer and in between adjacent fiber-reinforced epoxy layer. The finite element code, LS-DYNA3D, was used to perform numerical simulations of low-velocity impact to predict the complex damage propagations. The computed post-impact deformed shapes and damage patterns were found to be fairly close to experimental results.
Original languageEnglish
Pages (from-to)803-814
Number of pages12
JournalJournal of Composite Materials
Volume45
Issue number7
DOIs
Publication statusPublished - Apr 2011

Fingerprint

Laminates
Metals
Fibers
Aluminum alloys
Testing
Delamination
Plastic deformation
Ultrasonics
Aircraft
Glass
Computer simulation
Composite materials

Cite this

Tsartsaris, N., Meo, M., Dolce, F., Polimeno, U., Guida, M., & Marulo, F. (2011). Low-velocity impact behavior of fiber metal laminates. Journal of Composite Materials, 45(7), 803-814. https://doi.org/10.1177/0021998310376108

Low-velocity impact behavior of fiber metal laminates. / Tsartsaris, Nikolaos; Meo, Michele; Dolce, Ferdinando; Polimeno, Umberto; Guida, M; Marulo, F.

In: Journal of Composite Materials, Vol. 45, No. 7, 04.2011, p. 803-814.

Research output: Contribution to journalArticle

Tsartsaris, N, Meo, M, Dolce, F, Polimeno, U, Guida, M & Marulo, F 2011, 'Low-velocity impact behavior of fiber metal laminates', Journal of Composite Materials, vol. 45, no. 7, pp. 803-814. https://doi.org/10.1177/0021998310376108
Tsartsaris, Nikolaos ; Meo, Michele ; Dolce, Ferdinando ; Polimeno, Umberto ; Guida, M ; Marulo, F. / Low-velocity impact behavior of fiber metal laminates. In: Journal of Composite Materials. 2011 ; Vol. 45, No. 7. pp. 803-814.
@article{ac28583851b847408a3a3ff2d2f3ea48,
title = "Low-velocity impact behavior of fiber metal laminates",
abstract = "The low-velocity impact response of a range of fiber metal laminate (FML) panels was investigated through testing and finite element simulations. The objective of this study was to understand the impact-damage resistance of these novel composites, so that they can be designed optimally for impact-resistant aircraft applications. The FML panels were made up of aluminum alloy 7475 T761 and unidirectional S2 glass/epoxy oriented in a cross-ply configuration. Experimental tests were performed using a free-fall drop dart testing machine. The plate specimens were constrained on a circular edge by the clamping fixture. The shape and the nature of the damage inflicted by impact were evaluated using both destructive cross-sectional microphotography and nondestructive ultrasonic techniques. The tests showed that FML laminates are capable of absorbing energy through localized plastic deformation and through failure at the interface between the layers. In particular, delaminations occurred in the back face of the aluminum-alloy sheet and its adjacent fiber-reinforced epoxy layer and in between adjacent fiber-reinforced epoxy layer. The finite element code, LS-DYNA3D, was used to perform numerical simulations of low-velocity impact to predict the complex damage propagations. The computed post-impact deformed shapes and damage patterns were found to be fairly close to experimental results.",
author = "Nikolaos Tsartsaris and Michele Meo and Ferdinando Dolce and Umberto Polimeno and M Guida and F Marulo",
year = "2011",
month = "4",
doi = "10.1177/0021998310376108",
language = "English",
volume = "45",
pages = "803--814",
journal = "Journal of Composite Materials",
issn = "0021-9983",
publisher = "Sage Publications",
number = "7",

}

TY - JOUR

T1 - Low-velocity impact behavior of fiber metal laminates

AU - Tsartsaris, Nikolaos

AU - Meo, Michele

AU - Dolce, Ferdinando

AU - Polimeno, Umberto

AU - Guida, M

AU - Marulo, F

PY - 2011/4

Y1 - 2011/4

N2 - The low-velocity impact response of a range of fiber metal laminate (FML) panels was investigated through testing and finite element simulations. The objective of this study was to understand the impact-damage resistance of these novel composites, so that they can be designed optimally for impact-resistant aircraft applications. The FML panels were made up of aluminum alloy 7475 T761 and unidirectional S2 glass/epoxy oriented in a cross-ply configuration. Experimental tests were performed using a free-fall drop dart testing machine. The plate specimens were constrained on a circular edge by the clamping fixture. The shape and the nature of the damage inflicted by impact were evaluated using both destructive cross-sectional microphotography and nondestructive ultrasonic techniques. The tests showed that FML laminates are capable of absorbing energy through localized plastic deformation and through failure at the interface between the layers. In particular, delaminations occurred in the back face of the aluminum-alloy sheet and its adjacent fiber-reinforced epoxy layer and in between adjacent fiber-reinforced epoxy layer. The finite element code, LS-DYNA3D, was used to perform numerical simulations of low-velocity impact to predict the complex damage propagations. The computed post-impact deformed shapes and damage patterns were found to be fairly close to experimental results.

AB - The low-velocity impact response of a range of fiber metal laminate (FML) panels was investigated through testing and finite element simulations. The objective of this study was to understand the impact-damage resistance of these novel composites, so that they can be designed optimally for impact-resistant aircraft applications. The FML panels were made up of aluminum alloy 7475 T761 and unidirectional S2 glass/epoxy oriented in a cross-ply configuration. Experimental tests were performed using a free-fall drop dart testing machine. The plate specimens were constrained on a circular edge by the clamping fixture. The shape and the nature of the damage inflicted by impact were evaluated using both destructive cross-sectional microphotography and nondestructive ultrasonic techniques. The tests showed that FML laminates are capable of absorbing energy through localized plastic deformation and through failure at the interface between the layers. In particular, delaminations occurred in the back face of the aluminum-alloy sheet and its adjacent fiber-reinforced epoxy layer and in between adjacent fiber-reinforced epoxy layer. The finite element code, LS-DYNA3D, was used to perform numerical simulations of low-velocity impact to predict the complex damage propagations. The computed post-impact deformed shapes and damage patterns were found to be fairly close to experimental results.

UR - http://www.scopus.com/inward/record.url?scp=84859941138&partnerID=8YFLogxK

UR - http://dx.doi.org/10.1177/0021998310376108

U2 - 10.1177/0021998310376108

DO - 10.1177/0021998310376108

M3 - Article

VL - 45

SP - 803

EP - 814

JO - Journal of Composite Materials

JF - Journal of Composite Materials

SN - 0021-9983

IS - 7

ER -