Finite element simulation of carbon fibre-reinforced composite laminates subjected to low velocity impact using damage induced static load-deflection methodology

Farooq, Umar; Myler, Peter

doi:10.1016/j.tws.2015.09.008

Cited by 12 publications

(4 citation statements)

References 22 publications

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“…The BVID is not visible to naked eyes and sometimes difficult to detect under non-destructive inspection. These BVID severely reduce the FRP composites residual strength by growing throughout the structure with time, resulting in premature, sudden and catastrophic failure of the FRP structures (Farooq and Myler, 2015; Pashmforoush et al., 2018; Zhang et al., 2013). Furthermore, along with the BVID, the poor through-thickness strength further increases the FRP composites vulnerability (Caminero et al., 2017).…”

Section: Introductionmentioning

confidence: 99%

Effect of ply position switching in quasi-isotropic glass fibre reinforced polymer composite subjected to low velocity impact

Singh

Mahesh

2022

International Journal of Damage Mechanics

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This paper reports the influence of woven (0°/90°) and (±45°) lamina position interchanging about the midplane in an eight-layered quasi-isotropic glass fibre reinforced polymer (GFRP) composite under low velocity impact (LVI). In order to fabricate GFRP composite, two lamina orientations as (0°/90°) (referred as ‘a’) and (±45°) (referred as ‘c’) arranged in different stacking sequences. Three number of sample groups as (i) sandwiched ([aacc]S and [ccaa]S) (ii) intercalated ([acca]S and [caac]S) and (iii) alternate ([acac]S and [caca]S) resulted in six number of stacking sequences. The drop weight impact tests are performed at two incident velocities as 1.5 and 4 m/s. The corresponding impact energies generated are 11.39 and 81.05 J, respectively. The impact velocity 1.5 m/s created the barely visible impact damage (BVID) in the GFRP composite, while the impact velocity 4 m/s perforated the GFRP composite. The experimental results showed that the intercalated laminate design with four mismatching interfaces (i.e., [acca]S), offered better impact resistance than two other designs with two and six angle mismatching interfaces. It is also perceived that the impact response (maximum peak load, maximum impact energy and minimum impactor displacement) was independent of the number of angles of mismatching interfaces. Moreover, low velocity impact response of a quasi-isotropic GFRP composite depends on the balanced lamina position about the midplane in the laminate. Experimental results for maximum peak load, maximum energy absorption and laminate displacement proved the significance of conventional designing methodology. Further, the impactor displacement value at maximum peak load and the landing displacement value of the descending portion of the force-displacement curve after reaching the maximum peak load proved to be a practical approach along with the use of determinant of the bending stiffness matrix in determining the better performing stacking sequences for a quasi-isotropic GFRP composite made of (0°/90°) and (±45°) plies under LVI.

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Section: Introductionmentioning

confidence: 99%

Effect of ply position switching in quasi-isotropic glass fibre reinforced polymer composite subjected to low velocity impact

Singh

Mahesh

2022

International Journal of Damage Mechanics

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“…Sandwich panels and composites, due to their lightweight, high hardness, and strength, have a wide range of applications in industries such as aerospace, civil engineering, and automotive manufacturing [1][2][3][4]. Sandwich structures, possessing high-strength and stiff face sheets along with one or multiple flexible core layers (such as foams, honeycombs, etc), exhibit remarkable resistance against impact and out-of-plane loading [5,6].…”

Section: Introductionmentioning

confidence: 99%

Study on low-velocity impact response of kevlar/epoxy-polyurethane sandwich panels

Taghipoor,

Peysayyar

2023

Phys. Scr.

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This study aims to investigate the maximum energy absorption of sandwich panels featuring composite facesheets and a polyurethane foam core under low-velocity impact. The research explores various impactor head geometries, fiber orientations, and the number of composite layers on the panel facesheets. Three different impactor heads with flat, hemispherical, and conical shapes were used for experimental impacts. Numerical simulations were performed using Abaqus/Explicit finite element software, with damage initiation in the composite layers determined by the three-dimensional Hashin criterion. The results revealed that the conical-head impactor caused the highest energy absorption, accompanied by the greatest displacement and velocity changes. Among specimens with different fiber orientations, the 60° fiber layers exhibited a 9.41% and 8.45% higher maximum force compared to the 30° and 45° fiber layers, respectively. Furthermore, the study investigated the influence of the number of composite layers in the facesheets. It was found that panels with more layers in the bottom facesheet demonstrated a 4.94% increase in energy absorption compared to panels with more layers in the top facesheet. This research provides valuable insights into optimizing sandwich panel designs for enhanced energy absorption during low-velocity impact scenarios.

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“…The delamination area increased with energy and it has a significant effect on impact behaviour because diameter and boundary conditions affect the stiffness of the target material. Farooq and Myler [31] modeled the effect of 8, 16 and 24 layers of unidirectional carbon fiber composites on the impactor geometry by finite element method. Soto et al [32] studied the fiber composites at two different impact energies (20J, 30J) by experimentally and finite element method.…”

Section: Introductionmentioning

confidence: 99%

Impactor Diameter and Ply Number Effects on the Impact Behavior of Carbon Fiber Composite Laminates

Özsoy

2022

Gazi Üniversitesi Fen Bilimleri Dergisi Part C: Tasarım Ve Teknoloji

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As it is known, impact damage is a major mechanical phenomena for composite materials especially used in the aerospace structures. The factors affecting the impact behaviour of the composites depend on the impactor systems as well as the target material. In this study ply number and impactor geometry effects of carbon fiber reinforced epoxy composites were investigated by impact tests. In this context, drop weight impact tests were carried out at 6J, 12J and 24J energy levels by using hemispherical impactors with 10 mm and 20 mm diameters. Laminated composites were manufactured in 6, 10 and 14 plies with vacuum infusion method. The effects of laminate thickness, impactor diameter and impact energy effects on the force, velocity, absorbed energy and damage surfaces were investigated. It is observed that impactor geometries and velocities caused the different damage mechanisms in composites and impactors played an important role in determining the penetration and perforation behaviours of composites.

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Finite element simulation of carbon fibre-reinforced composite laminates subjected to low velocity impact using damage induced static load-deflection methodology

Cited by 12 publications

References 22 publications

Effect of ply position switching in quasi-isotropic glass fibre reinforced polymer composite subjected to low velocity impact

Effect of ply position switching in quasi-isotropic glass fibre reinforced polymer composite subjected to low velocity impact

Study on low-velocity impact response of kevlar/epoxy-polyurethane sandwich panels

Impactor Diameter and Ply Number Effects on the Impact Behavior of Carbon Fiber Composite Laminates

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