Impact Behavior of Hybrid Glass/Carbon Epoxy Composites

Pérez-Martín, María Jesús; Enfedaque, Alejandro; Dickson, William; Gálvez, Francisco

doi:10.1115/1.4023344

Cited by 20 publications

(17 citation statements)

References 5 publications

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“…Recently, the Hashin damage model in conjunction with finite element method has also been used to predict the damage behavior of composite laminates under low velocity impact . Moreover, when the velocity of impact projectile reaches up to a certain value, no delamination appears in the damage process of composites under high‐velocity impact . Therefore, for the purpose of simplify our calculations, the Hashin damage model, which takes into account four failure modes: fiber tension, fiber compression, matrix tension, and matrix compression, is adopted to model the damage initiation in the composite in this study.…”

Section: Description Of Numerical Modelmentioning

confidence: 99%

“…The four boundaries of laminates are fixed, and the impact point is the centre position of laminate. The hybrid woven carbon and S2‐glass fabric composites are chosen as a model system , and the dimensions of laminates are 50 mm × 50 mm. The composite laminates are meshed by an 8‐node quadrilateral in‐plane continuum shell element (SC8R) with reduced integration and hourglass control.…”

Section: Description Of Numerical Modelmentioning

confidence: 99%

“…Pandya et al presented an experimental study on the high‐velocity impact behavior of woven hybrid carbon and E‐glass fabric composites. Pérez‐Martín et al studied the high‐velocity impact performance in hybrid woven carbon and S2‐glass and E‐glass fabric laminates. The researches on the impact damage behavior of hybrid glass/carbon composites are mainly through experimental method, while the numerical analysis is still limited.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Modeling analysis of fiber hybridization in hybrid glass/carbon composites under high‐velocity impact

Meng

Wang

2015

Polymer Composites

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The effects of fiber hybridization on damage behavior of hybrid glass/carbon composites under high‐velocity impact were investigated. The Hashin damage model is adopted to model the damage initiation of composites, and the bilinear form of damage evolution law based on the effective displacement is employed. The numerical results show a reasonable agreement with the experimental data. The residual velocity of impact projectile is approximately shown a linearly decreasing trend with the increasing of the thickness of glass fabric ply. As the proportion of glass fabric ply in the hybrid laminates increases, the impact resistance of laminates increased gradually. POLYM. COMPOS., 38:2536–2543, 2017. © 2015 Society of Plastics Engineers

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Section: Description Of Numerical Modelmentioning

confidence: 99%

Section: Description Of Numerical Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Modeling analysis of fiber hybridization in hybrid glass/carbon composites under high‐velocity impact

Meng

Wang

2015

Polymer Composites

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“…Perez et al [15] studied the high velocity impact performance of woven carbon and glass fabric hybrid laminates, and their results have been used to describe the role played by glass-fiber hybridization on the fracture micromechanics and on the overall laminate performance. Marino et al [16] investigated the behavior of composite laminates under low velocity impact, with the aim of determining the influence of stacking sequence and laminate thickness on contact loads, absorbed energy, and delamination.…”

Section: Introductionmentioning

confidence: 99%

Experimental impact study on unidirectional glass-carbon hybrid composite laminates

Julias

Vela

2015

Science and Engineering of Composite Materials

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In this experimental study, the impact response of unidirectional hybrid composite laminate was investigated. Hybrid laminates with different stacking sequences were fabricated, using unidirectional glass and carbon fiber as reinforcement and epoxy resin as matrix. ASTM standard D5628 was followed to conduct the experiment using the instrumented drop weight impact test apparatus.All the square specimens were tested at an impact velocity of 3.43 m/s and the time histories of force and energy absorbed were recorded. The impacted specimens and their X-ray images were visually inspected to understand the failure pattern. The experimental results showed that the addition of carbon fiber increases the impact strength by absorbing more force and energy. Furthermore, the laminate can be stiffened with the carbon fiber layers by interfacing glass fiber layers on either side.

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“…They modeled the progressive delamination of plies using a tie-break interface approach. Perez-Martin et al [32] investigated the high-velocity (∼700 m∕s) ballistic impact performance in hybrid woven carbon and glass fabric laminates manufactured by a resin transfer molding process. Recently, Sinha et al [33] have analyzed a typical turbofan rotor blade under birdstrike loading.…”

Section: Introductionmentioning

confidence: 99%

Transient Response of a Multilayered Composite Rotating Airfoil Under Slicing-Impact Loading

Sinha¹

2014

AIAA Journal

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In this paper, a semiclosed form of numerical solution is obtained for a slicing-impact edge loading on a multilayered composite airfoil. The analytical derivation of the governing partial differential equation simulates the transient event of the slicing process by considering the moving bird in the form of a soft-body impactor as it comes into contact with the rotating fan blades modeled as prestressed airfoil due to centrifugal force field. The oblique-impact formulation of a composite pretwisted fan blade includes the effect of both the contact-impact loads as well as the Coriolis forces. The consideration of coupled longitudinal-transverse elastic wave propagation in a rotating coordinate system is a key to correctly predict the impact response of a blade mounted on a rotor shaft. The dynamic loading on the airfoil and its transient response produced during the bird strike is determined by solving the coupled nonlinear dynamical equations governing the movement of the bird slice in the time domain using a sixth-order Runge-Kutta technique. Nomenclature A = cross-sectional area of the composite airfoil B D , B L = diameter and length of the cylinder representing the bird B M = mass of the incoming bird in the shape of a cylinder B m = mass of the single bird slice impacting on individual blade b = base radial distance of the blade root at the clamped end C = C 0 C 0 x, chord width of the airfoil at any span height x C 0 = C L − C 0 ∕L, rate of change of chord width from root to tip C = velocity-dependent matrix of composite airfoil c = chordwise instantaneous location of the traveling bird slice at any time t D 11 , D 22 , D 12 , D 66 = orthotropic flexural rigidity terms for the multilayered composite airfoil E xx , E yy = equivalent Young's modulus of elasticity of the composite airfoil material in the local x (span) and y (chord) directions, respectively ê t ;ê a ;ê r = unit vectors in the coordinate system attached to the rotating shaft ê x ;ê y ;ê z = unit vectors attached to the local airfoil span, chord, and normal directions ft Bird-slice = dynamic load being applied by the bird slice on the airfoil f impulse = time-dependent load on the blade leading edge during bird-slicing action f travel = time-dependent load on the blade during slice travel across the chord f cf = centrifugal forces on the blade acting radially outward fftg = external force column vector G xy , G yz , G zx = directional shear moduli in the bulk orthotropic blade material h = thickness of the airfoil blade î;ĵ;k = unit vectors in the global rectangular Cartesian coordinates (fixed in space) K = structural stiffness matrix of airfoil (functions of E xx , E yy , ν xy , G yz , h, etc.) K Ω = stiffness matrix due to centrifugal effect (functions of Ω, ρ, h, R, L, etc.) L = spanwise length of the airfoil along its stacking axis M = mass matrix of airfoil (functions of ρ, h, C, L, etc.) N b= number of blades on the fan rotor n1, n2 = number of terms in the deformation shape function Q x , Q y = shear forces per unit length at the x and ...

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Impact Behavior of Hybrid Glass/Carbon Epoxy Composites

Cited by 20 publications

References 5 publications

Modeling analysis of fiber hybridization in hybrid glass/carbon composites under high‐velocity impact

Modeling analysis of fiber hybridization in hybrid glass/carbon composites under high‐velocity impact

Experimental impact study on unidirectional glass-carbon hybrid composite laminates

Transient Response of a Multilayered Composite Rotating Airfoil Under Slicing-Impact Loading

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