Examination of small crack normal to multiple elasticity and plasticity mismatched interfaces in residually stressed fiber metal laminate (Glare): Theoretical and numerical approaches

Bhat, Sunil; Patibandla, Rajasekhar

doi:10.1177/1056789512449766

Cited by 6 publications

(5 citation statements)

References 19 publications

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“…Variable residual stresses, σ r , develop in material layers of the laminate during its high temperature curing due to different stiffness and the coefficients of thermal expansion of the materials, α, as seen in Table I. The coefficients of thermal expansion of the laminate in longitudinal ( y) direction, α ll , and in transverse (x) direction, α tl , are obtained as 18.62 × 10 −6 C −1 and 17.25 × 10 −6 C −1 , respectively with the help of basic formulations related to composites and laminates (Bhat and Patibandla, 2013). These coefficients along with the coefficients of thermal expansion of individual materials and their stiffness matrices, {M}, of 3 × 3 order that are derived from conventional two dimensional (2D) stress-strain constitutive equations are employed in theoretical estimation of residual stresses.…”

Section: Glare Under Uni-axial Tensionmentioning

confidence: 99%

Numerical investigations on delaminated Glare under uni-axial tension

Bhat

Narayanan

2016

International Journal of Structural Integrity

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Purpose – Since failure of laminated composites by delaminations is common, the purpose of this paper is to present a numerical procedure to check the stability of delaminations in fiber metal laminate (Glare), with different possible damage configurations, under uni-axial tension. Deformation behavior of the laminate is also examined. Influence of the type and the extent of damage, represented by varying sizes and number of delaminations, on delamination driving force and laminate deformation is found. Design/methodology/approach – Delaminated Glare is modeled by finite element method. Interface cohesive elements are used to model the delaminations. Finite element results provide the deflection/deformation characteristics of the laminate. Driving forces of delaminations are estimated by J integrals that are numerically obtained over cyclic paths near delamination tips. Laminates with different types of delaminations are also fabricated and externally delaminated for measurement of their interlaminar fracture toughness. The delamination is considered to be stable if its driving force is less than corresponding interlaminar fracture toughness of the laminate. Findings – Delaminations are found to be stable in laminates with lower number of delaminations and unstable in laminates with higher number of delaminations. Increase in size of delaminations increases the deformations but reduces the delamination driving force whereas increase in number of delaminations increases both deformations and driving forces. The trends change in case of laminates with symmetrical damage. Shape of delamination is also found to influence the deformations and driving forces. The finite element model is validated. Research limitations/implications – There is scope for validating the numerical results reported in the paper by theoretical models. Practical implications – Checking the stability of delaminations and their effect on deformation behavior of the laminate helps is assessment of safety and remaining life of the laminate. If failure is predicted, preemptive action is taken by using repair patch ups at identified critical locations in order to avoid failures in service conditions. Originality/value – The paper offers the following benefits: use of cohesive zone method that is readily possible in finite element procedures and is relatively simple, fast and reasonably accurate is demonstrated; suitability of using J integrals over paths crossing non-homogeneous and property mismatched material layers is tested; and influence of the type and the extent of damage in the laminate on its deformation behavior and delamination driving forces is found. This type of work has not been reported so far.

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Section: Glare Under Uni-axial Tensionmentioning

confidence: 99%

Numerical investigations on delaminated Glare under uni-axial tension

Bhat

Narayanan

2016

International Journal of Structural Integrity

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“…Various methods can be used to analyze and mechanical modeling of FMLs (Bhat and Patibandla, 2013;Kashfi et al, 2019;Majzoobi et al, 2018;Sharma et al, 2017). Moussavi-Torshizi et al (2010) employed analytical modeling and finite element simulation to predict the stress-strain relationship of glass/Kevlar fibers reinforced FMLs.…”

Section: Introductionmentioning

confidence: 99%

Modeling and experimental study on the mechanical behavior of glass/basalt fiber metal laminates after thermal cycling

Azghan

Bahari-Sambran

Eslami‐Farsani

2021

International Journal of Damage Mechanics

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In the present study, the effect of thermal cycling and stacking sequence on the tensile behavior of fiber metal laminate (FML) composites containing glass and basalt fibers was investigated. To fabricate the FML samples, fibers reinforced epoxy composite were sandwiched between two layers of 2024-T3 aluminum alloy sheet. 55 thermal cycles were implemented at a temperature range of 25–115°C for 6 min. The tensile tests were carried out after the thermal cycling procedure, and the results were compared with non-thermal cycling specimens. Scanning electron microscopy (SEM) was employed for the characterization of the damage mechanisms. The FMLs containing four basalt fibers’ layers showed higher values of tensile strength, modulus, and energy absorption. On the other hand, the lowest strength and fracture energy were found in the asymmetrically stacked sample containing basalt and glass fibers, due to weak adhesion between composite components (basalt and glass fibers). The lowest tensile modulus was found in the sample containing glass fibers that was due to the low modulus of the glass fibers compared to basalt fibers. In the case of the samples exposed to thermal cycling, the highest and the lowest thermal stabilities were observed in basalt fibers samples and asymmetrically stacked samples, respectively. In accordance with the experimental results, a non-linear damage model using the Weibull function and tensile modulus was employed to predict the stress-strain relationship. The simulated strain–strain curves presented an appropriate agreement with the experimental results.

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“…As a successful type of Fiber Metal Laminates (FMLs), GLARE (Glass fiber reinforced aluminum laminates) combines the advantages of both metal and composites (Mrzljak et al., 2020). GLARE laminates have been applied in some structural parts of civil aircrafts such as the fuselage skin of Airbus A380 (Guan et al., 2009) and the bulk cargo floor of Boeing B777 (Chai and Manikandan, 2014) due to good impact damage resistance, fatigue properties (Bhat and Patibandla, 2013), corrosion resistance (Wang, 2020), and anti-fire performance (Li et al., 2020). GLARE is fabricated by hot-pressing of alternate multi-layers of aluminum alloy sheet and unidirectional glass fiber/epoxy resin prepreg, the bonding strength of the interface determines interfacial stress transfer degree (Gonzalez-Canche et al., 2018) and has an obvious influence on the interlaminar as well as the comprehensive properties (Hu et al., 2020; Ji et al., 2020).…”

Section: Introductionmentioning

confidence: 99%

Short beam shear damage analysis of GLARE laminates based on digital image correlation and finite element analysis

Chen

Yang

Wang

et al. 2021

International Journal of Damage Mechanics

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The short beam shear performance of GLARE 3A-3/2 laminates with adhesive layers was investigated by combining the short beam test and the digital image correlation technique. The failure behavior was further analyzed based on finite element simulation and micro failure morphology. The results show an 8% and 58% difference in the short beam strength and bending displacement at failure of laminates along two orthogonal directions; The damage behavior of laminates is determined by the bottom unidirectional glass fiber reinforced plastic (GFRP) layers. The two typical failure modes are matrix and fiber fracture in the GFRP layer caused by local bending deformation, and interlaminar delamination between GFRP layers; The distribution of surface strain [Formula: see text] indicates the damage initiation and evolution process. The simulation result of the finite element model established in ABAQUS/Explicit shows consistency with digital image correlation analysis, which provides an effective method to predict the damage behavior of specimens with different ply structures.

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Examination of small crack normal to multiple elasticity and plasticity mismatched interfaces in residually stressed fiber metal laminate (Glare): Theoretical and numerical approaches

Cited by 6 publications

References 19 publications

Numerical investigations on delaminated Glare under uni-axial tension

Numerical investigations on delaminated Glare under uni-axial tension

Modeling and experimental study on the mechanical behavior of glass/basalt fiber metal laminates after thermal cycling

Short beam shear damage analysis of GLARE laminates based on digital image correlation and finite element analysis

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