Effect of Laminate Configuration and Impactor's Mass on the Initial Impact Damage of Graphite/Epoxy Composite Plates Due to Line-Loading Impact

Choi, Hyung Yun; Wang, Hong Sheng; Chang, Fu‐Kuo

doi:10.1177/002199839202600603

Cited by 56 publications

(9 citation statements)

References 9 publications

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“…Other S2/FM94 glass fibre plates with different orientation systems exhibit a higher load-bearing capability. Therefore, introducing different fibre orientations can improve the strength and stiffness with constant density [ 9 , 16 ].…”

Section: Resultsmentioning

confidence: 99%

“…Therefore, studying impact damage is important, especially with modern aircraft, which have an increasing percentage of composites in their structures. There are four main failure mechanisms (failure modes) that occur in fibre reinforced composites due to low-velocity impact loading [ 9 ]. The first failure mechanism occurs in the matrix due to tension, compression, or shear loading.…”

Section: Introductionmentioning

confidence: 99%

“…The adhesion (bonding) strength and quality within the fibre/matrix system of the composites can also play an important role in impact damage resistance [ 15 ]. Early studies showed that altering the stacking sequence in a composite can influence the impact damage in a greater way than altering its thickness [ 9 ]. Belingardi and Vadori [ 16 ] reported that glass fibre composites with a stacking sequence of [0/90] exhibit the highest saturation energy (i.e., better impact resistance) compared to the other tested fibre orientations

.…”

Section: Introductionmentioning

confidence: 99%

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Effect of Fibre Orientation on Impact Damage Resistance of S2/FM94 Glass Fibre Composites for Aerospace Applications: An Experimental Evaluation and Numerical Validation

et al. 2021

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This study aims to investigate the influence of fibre orientation and varied incident energy levels on the impact-induced damage of S2/FM94, a kind of aerospace glass fibre epoxy/composite regularly used in aircraft components and often subjected to low-velocity impact loadings. Effects of varying parameters on the impact resistance behaviour and damage modes are evaluated experimentally and numerically. Laminates fabricated with four different fibre orientations 0/90/+45/−458s, 0/90/90/08s, +45/−4516s, and 032 were impacted using three energy levels. Experimental results showed that plates with unidirectional fibre orientation failed due to shear stresses, while no penetration occurred for the 0/90/90/08s and +45/−4516s plates due to the energy transfer back to the plate at the point of maximum displacement. The impact energy and resulting damage were modelled using Abaqus/Explicit. The Finite Element (FE) results could accurately predict the maximum impact load on the plates with an accuracy of 0.52% to 13%. The FE model was also able to predict the onset of damage initiation, evolution, and the subsequent reduction of the strength of the impacted laminates. The results obtained on the relationship of fibre geometry and varying incident impact energy on the impact damage modes can provide design guidance of S2/FM94 glass composites for aerospace applications where impact toughness is critical.

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Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

.…”

Section: Introductionmentioning

confidence: 99%

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Effect of Fibre Orientation on Impact Damage Resistance of S2/FM94 Glass Fibre Composites for Aerospace Applications: An Experimental Evaluation and Numerical Validation

et al. 2021

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“…Damage is also affected by the size, shape, mass, velocity and material properties of the impactor. 8 To ensure reliable and optimized patch design, understanding the effects of multiple input uncertainties, damage mechanics, and their interactions is imperative.…”

Section: A Research Objectivesmentioning

confidence: 99%

Investigation of Composite Patch Performance Under Low-Velocity Impact Loading

Goodmiller

TerMaath

2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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A finite element model to investigate the performance of hybrid structure under lowvelocity impact loading was developed and validated using a building-block approach. The hybrid structure consisted of a composite patch adhesively bonded to a metal substrate. Each component of the model was validated individually to accurately capture the behavior and damage mechanisms of each material. Interlaminar composite damage and adhesive damage were modeled with cohesive zone theory. Hashin failure criteria with energy dissipation based damage evolution modeled intralaminar damage in the composite. The Johnson-Cook plasticity model captured the metal substrate's behavior. Each component was assembled into a hybrid structure model that captured the interactions between the damage modes. Once the hybrid model was validated with experimental results, a sensitivity study was performed on various input parameters to provide guidance for optimized design of composite patches subjected to low-velocity impact loading. NomenclatureA, B, C, m, n = Johnson-Cook material constants a 0 = initial crack length BK = Benzeggagh-Kenane C v = empirical variable adjusting for void content CDM = continuum damage mechanics CFRP = carbon-fiber reinforced polymer CZT = cohesive zone theory d = length of the lever arm in MMB test D = damage variable DCB = double cantilever beam E m = Young's Modulus of matrix E 1 , E 1f = Young's Modulus of ply or fiber, longitudinal orientation E 2 , E 2f = Young's Modulus of ply or fiber, transverse orientation E 3 = Young's Modulus of ply, out-of-plane orientation ENF = end-notched flexure F = applied load FRP = fiber reinforced polymer G c = critical fracture energy G f c , G f t = energy dissipation rate, longitudinal (fiber) compressive or tensile G I , G II = Mode I or II fracture energy G Ic , G IIc = Mode I critical fracture energy G m = shear modulus, matrix G m c , G m t = energy dissipation rate, transverse (matrix) compressive or tensile G shear = total shear fracture energy G T = total fracture energy G 12 , G 12f 2 G 13 = transverse shear modulus G 23 , G 23f = out-of-plane shear modulus of ply or fiber GFRP = glass-fiber reinforced polymer h = thickness of adhered plies K = penalty stiffness , = fiber or matrix bulk modulus L = length of half span for DCB, ENF, MMB tests , = Mode I or II cohesive zone length L e = length of each element LEFM = linear elastic fracture mechanics M = length of cohesive zone parameter MMB = mixed mode bending N e = number of elements in the cohesive zone S L , S Lm = longitudinal shear strength of ply or matrix S T = transverse shear strength S 0 , S a = maximum traction, Mode II; max. traction from coarse mesh refinement, Mode II t, t n , t s , t t = traction, Mode I, Mode II, or Mode III traction T = homologous temperature T c = thickness of adhesive layer ̅ = traction without damage application, Mode I T 0 , T a = maximum traction, Mode I; max. traction from coarse mesh refinement, Mode I = effective traction at damage inititiation V f = fiber volume ratio V m = ma...

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“…The orthotropic, linear elastic material law MAT54 based on Chang-Chang failure criteria [29][30][31][32] control failure in longitudinal (fibre) and transverse (normal to fibre) directions in tensile, compressive and shear loading of the fibre and the matrix. These failure modes in the Chang-Chang failure criterion for composite shell elements are:…”

Section: Fig 4: Definition Of Contact Between Different Surfacesmentioning

confidence: 99%

Modelling of Low Velocity Impact of Laminated Composite Substructures

Hadavinia¹,

Doğan²,

Elmarakbi

et al. 2011

Int. J. Vehicle Structures and Systems

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Impact is among the important loading scenario which is required to be addressed for fibre reinforced plastics (FRP) materials in ground or space vehicle applications. The failure behaviour of FRP materials under impact loading is a complex process and a detailed analysis of various mode of failure is necessary. In this paper the failure behaviour of laminated carbon fibre reinforced plastic (CFRP) composite structures under impact loading is investigated by conducting numerical simulations using the explicit finite element analysis ANSYS LS-DYNA software [1]. The impact responses and failure behaviours are being investigated by performing a parametric study and sensitivity analysis in which impact velocity, number of plies, incident angle, friction between contacted surfaces, impactor mass and the geometry are varied in separate cases. The FE model is validated by comparing the numerical results with other published results and good correlations are achieved.

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Effect of Laminate Configuration and Impactor's Mass on the Initial Impact Damage of Graphite/Epoxy Composite Plates Due to Line-Loading Impact

Cited by 56 publications

References 9 publications

Effect of Fibre Orientation on Impact Damage Resistance of S2/FM94 Glass Fibre Composites for Aerospace Applications: An Experimental Evaluation and Numerical Validation

Effect of Fibre Orientation on Impact Damage Resistance of S2/FM94 Glass Fibre Composites for Aerospace Applications: An Experimental Evaluation and Numerical Validation

Investigation of Composite Patch Performance Under Low-Velocity Impact Loading

Modelling of Low Velocity Impact of Laminated Composite Substructures

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