Next Article in Journal
Design and Experimental Characterization of an Actuation System for Flow Control of an Internally Blown Coanda Flap
Previous Article in Journal
Calibration of a Load Measurement System for an Unmanned Aircraft Composite Wing Based on Fibre Bragg Gratings and Electrical Strain Gauges
Previous Article in Special Issue
SPH-FEM Design of Laminated Plies under Bird-Strike Impact
Open AccessArticle

Interface Failure of Heated GLARETM Fiber–Metal Laminates under Bird Strike

Designing Plastics and Composite Materials Department, Montan University, 8700 Leoben, Austria
Aerospace 2020, 7(3), 28; https://doi.org/10.3390/aerospace7030028
Received: 2 February 2020 / Revised: 7 March 2020 / Accepted: 10 March 2020 / Published: 17 March 2020
(This article belongs to the Special Issue Crashworthiness Design for Aviation Safety)
Many high-strength composite materials have been developed for aircraft structures. GLAss fiber REinforced aluminum (GLARE) is one of the high-performance composites. The review of articles, however, yielded no study on the impact damage of heated GLARE laminates. This study, therefore, aimed at developing a numerical model that can delineate the continuum damage of GLARE 5A-3/2-0.3 laminates at elevated temperatures. In the first stage, the inter-laminar interface failure of heated GLARE laminate had been investigated at room temperature and 80 °C. The numerical analysis employed a three-dimensional GLARE 5A-3/2-0.3 model that accommodated volumetric cohesive interfaces between mating material layers. Lagrangian smoothed particles populated the projectile. The model considered the degradation of tensile and shear modulus of glass fiber reinforced epoxy (GF/EP) at 80 °C, while incorporated temperature-dependent critical strain energy release rate of cohesive interfaces. When coupled with the material particulars, an 82 m/s bird impact at room temperature exhibited delamination first in the GF/EP 90°/0° interface farthest from the impacted side. Keeping the impact velocity, interface failure propagated at a slower rate at 80 °C than that at room temperature, which was in agreement with the impact damage determined in the experiments. The outcomes of this study will help optimize a GLARE laminate based on the anti-icing temperature of aircraft. View Full-Text
Keywords: heated GLARE; cohesive zone elements; fracture toughness; bird strike; inter-ply failure heated GLARE; cohesive zone elements; fracture toughness; bird strike; inter-ply failure
Show Figures

Figure 1

MDPI and ACS Style

Hasan, M. Interface Failure of Heated GLARETM Fiber–Metal Laminates under Bird Strike. Aerospace 2020, 7, 28.

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.

Article Access Map by Country/Region

1
Search more from Scilit
 
Search
Back to TopTop