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The study aimed to investigate the impact behavior of fabric laminates composed of carbon, Kevlar, and hybrid materials through low‐velocity impact tests. Non‐hybrid and hybrid laminates were created using layup techniques with sandwich stacking sequences. Drop weight impact tests were conducted using varying levels of impact energy to assess the influence of stacking sequence and hybridization on impact properties. The results showed significant improvements in impact properties with increasing stacking sequence, particularly a 108.8% and 137.4% enhancement in C4 and K4 laminates, respectively. Kevlar laminates exhibited higher energy resistance than carbon laminates, and the Kevlar‐carbon‐Kevlar‐carbon hybrid laminate demonstrated superior impact force and energy absorption capabilities. Additionally, the study analyzed penetration depth and identified different failure modes dependent on stacking sequence and impact energy levels. These findings provide valuable insights for optimizing fabric laminated composites. Thus, the research could be implemented in industries requiring materials with enhanced impact resistance, such as aerospace, automotive, sports equipment, and protective gear manufacturing. Highlights: Investigated the impact performance of stacked fabric structures, including carbon, Kevlar, and hybrid laminated composites, through low‐velocity impact tests.Fabricated both non‐hybrid and hybrid laminates using layup techniques with a sandwich stacking sequence to assess the impact properties of the composite laminates.Observed greater penetration depth in the C2 stacked structure, while the KCKC hybrid laminate showcased greater resistance to a depth of penetration (DOP).Various failure modes were investigated, demonstrating their relationship with stacking sequence and impact energy levels. [ABSTRACT FROM AUTHOR]

Carbon fabric/resin laminated composites (CFRC) are extensively used in aerospace, transportation, and other fields owing to their superiorities of lightweight, high strength, and convenient integral molding. Therefore, strong interlaminar binding and prominent wear resistance are urgent requirements for avoiding premature failure of laminated materials in harsh working environments. To elevate the superficial wear resistance and interlaminar bonding strength of composites simultaneously, the modified composites were obtained by introducing carbon fiber powder (CFP) with different densities on the surface of the composites and between layers. The experimental results indicate that CFP can be evenly distributed in the interlaminar resin enrichment zone of the sample (CFRC‐40) when the deposition density is 40 g/m2. Consequently, CFRC‐40 presents optimal thermal conductivity owing to better heat transfer bridges between layers of the composite established by CFP. At the same time, the mechanical properties such as the tensile, impact, and interlaminar shear strengths of CFRC‐40 are improved by 42.8%, 10.2%, and 8.5%, respectively, compared with the original CFRC, which are attributed to the absorption of crack propagation energy and the inhibition of crack propagation by CFP. Furthermore, the dynamic friction coefficient maintains at a high level after introducing CFP with a density of 40 g/m2, while the wear rate significantly decreases by 61.2% from 12.99 × 10−14 m3(N m)−1 to 5.04 × 10−14 m3(N m)−1. This study proposes an innovative strategy to improve the interlaminar bonding of carbon fabric/resin laminated composite, which is conducive to obtaining composite with excellent mechanical and tribological properties. Highlights: A facile and effectual method was adopted to introduce carbon fiber powder (CFP) into the interlamination and surface of the composites simultaneously.The mechanical properties and abrasive resistance of the composites were obviously strengthened by regulating the content and distribution of CFP.CFP at a certain scale, could not only hinder the propagation of cracks but also alleviate the surface wear and extend the service life of composites. [ABSTRACT FROM AUTHOR]

In this study, the failure behavior of carbon fiber‐reinforced pin‐jointed composite plates were analyzed for different criteria. For this purpose, composite plates with a single and double pin joints were prepared from four layers carbon fiber composites. The effect of pin number, pin position on plate damage load and type was investigated experimentally and numerically under the tensile test. Numerically, progressive damage analysis was performed using Hashin and Puck failure criteria, and the approach rates to the experimental results were determined. It was observed that the experimental results obtained for single pin joint composites and the numerical data obtained using the Puck damage criterion were at least 87 % compatible, and this rate was determined as 85 % for the Hashin failure criterion. For the double pin jointed composites, it was seen that the experimental results and the results of the Puck damage criterion were compatible with at least 90 %, and this rate was obtained as 84 % for the Hashin failure criterion. The dominant damage type seen in the specimen is matrix shear and fiber compression according to the Hashin damage criterion, inter fiber failure in transverse tension for Puck. [ABSTRACT FROM AUTHOR]

This article presents a free vibration analysis of laminated sandwich plates under various boundary conditions by using an efficient C0 eight‐node quadrilateral element. This new element is formulated based on the recently proposed layerwise model. The present model assumes an improved first‐order shear deformation theory for the face sheets while a higher‐order theory is assumed for the core maintaining an interlaminar displacement continuity. The advantage of this model relies on its number of variables is fixed, does not increase when increasing the number of lamina layers. This is a very important feature compared to the conventional layerwise models and facilitates significantly the engineering analysis. Indeed, the developed finite element is free of the shear locking phenomenon without requiring any shear correction factors. The governing equations of motion of the sandwich plate are derived via the classical Hamilton's principle. Several examples covering the various features such as the effect of modular ratio, aspect ratios, core‐to‐face thickness ratio, boundary conditions, skew angle, number of layers, geometry and ply orientations are solved for laminated composites and sandwich plates. The obtained results are compared with 3D, quasi‐3D, 2D analytical solutions, and those predicted by other advanced finite element models. The comparison studies indicate that the developed finite element model is of fast convergence to the reference and valid for both thick and thin laminated sandwich plates. Finally, it can be concluded that the present model is not only simple and accurate than the conventional ones, but also comparable with refined analytical solutions found in the literature. [ABSTRACT FROM AUTHOR]

This paper presents the seismic response analysis of a cylindrical container made of laminated composite. The analytical homogenization is used for calculation of the material properties of unidirectional fiber‐reinforced composite layer. Constitutive relations for laminate within the classical laminate theory are considered. Effective modulus of elasticity is obtained and put into a calculation of internal forces of the laminated composite cylindrical tank. The seismic analysis of liquid storage facilities has to have different approaches as the analysis of typical structures. Because of an earthquake, the hydrodynamic impulsive and convective pressures are generated in addition to hydrostatic pressure. The solved liquid‐filled container made of the laminated composite was situated for the region of Slovak Republic and was analyzed in respect of Eurocode 8 recommendations. [ABSTRACT FROM AUTHOR]

Lead-free magnetoelectric (ME) laminated (80Bi0.5Na0.5TiO3-20Bi0.5K0.5TiO3)/(Ni0.8Zn0.2)Fe2O4 (BNKT/NZFO) composites are prepared via a modified cofiring processing, combining grain refinement and liquid phase sintering with low sintering aid content. The microstructure, dielectric, ferroelectric, magnetic, and magnetoelectric properties are investigated by varying the thickness of NZFO layer. The results show that the coexistence of independent BNKT and NZFO phase and the presence of the morphotopic phase boundary in BNKT phase with high piezoelectric coefficient d33 of 131 pC/N are confirmed. Laminated composites have clear and well-bonded interfaces across the two layers, as well as improved ME properties. The maximum ME voltage coefficient ( αE31) of the laminated composite reach 115.1 mV cm−1 Oe−1 with an optimized BNKT/NZFO layer thickness ratio of 1/2. In addition, a zero-biased ME response was observed in BNKT/NZFO laminated composites. [ABSTRACT FROM AUTHOR]

Due to their lightweight, high specific stiffness and strength, cost effectiveness, corrosion and fatigue resistance, laminated composites have been widely used in many engineering applications, such as aircraft, automobiles, sporting products, and civil infrastructure. However, delamination damage along in-plane interfaces has been one of the issues that still remain unsolved. Although many natural load-bearing materials are also essentially laminated composites composed of mineral and organic phases, the underlying mechanisms for antidelamination are still largely unexplored. Here it is reported that the remarkable resistance to macroscopic indentation damage in the highly mineralized shell of the bivalve Placuna placenta originates from a characteristic nanoscale structural motif, i.e., screw dislocation-like connection centers, which join adjacent mineral layers together in the laminate structure. This leads to the formation of a complex interconnected network of microcracks surrounding the damage zone, which allows for both efficient energy dissipation and damage localization even when the shell is completely penetrated. Both theoretical analysis and experiment-based calculations suggest that the interfacial fracture toughness is enhanced by almost two orders of magnitude in comparison to classic laminated composites without connection centers. This design strategy for achieving a 3D integrative laminate architecture can be potentially applied in the design of advanced laminated composite materials. [ABSTRACT FROM AUTHOR]

Diffusion bonding of metallic glasses and crystalline metals utilizing excellent superplasticity of monolithic bulk metallic glasses (BMGs) within supercooled liquid region has been found to be an efficient method to improve the room temperature plasticity and fracture toughness of metallic glass. A Zr-based BMG/copper laminated composite was fabricated by copressing method, and the interface bonding status was characterized by scanning electron microscopy (SEM) and high-resolution transmission electron microscopy. No void or crack is detected, and the interface is a metallurgical bonding of atomistic level. Although the BMG retains amorphous state after copressing at 390 °C, the region of the amorphous-crystalline mixture structure with the width of 30-40 nm occurred within the diffusion zone. Copyright © 2013 John Wiley & Sons, Ltd. [ABSTRACT FROM AUTHOR]

L. Li and C. Ortiz show on page 3463 that adjacent mineral layers in the laminate composite of a bivalve (Placuna placenta) shell are joined together through characteristic nanoscale screw dislocation‐like connection centers. This leads to extensive crack bridging and deflection surrounding macroscopic indentation damage zones, which forms an interconnected network of microcracks, enabling simultaneous damage localization and energy dissipation. [ABSTRACT FROM AUTHOR]