Simulation of the effect laminate sequence on delamination mode-I with elastic couplings

Alhussein, Mustafa; Ameer, Zuhair; Hamzah, Ahmed Fadhil

doi:10.29354/diag/150547

Cited by 2 publications

(2 citation statements)

References 33 publications

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“…In the available literature, there is a limited number of papers devoted to delamination problems in composite laminates with elastic couplings. In [ 22 ], the researchers presented numerical study of the double cantilever beam laminates exhibiting different types of elastic couplings. Results of simulations revealed that the ply stacking sequence in DCB model had a significant effect on the strain energy release rate distributions along specimens’ width.…”

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Research of Delamination Process in CFRP Laminates with Bending-Twisting Elastic Couplings

Rzeczkowski

Samborski

2022

Materials

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This paper aims at experimental and numerical research of delamination process in carbon/epoxy composite laminates with different fiber orientation angles in stacking sequence exhibiting the bending–twisting elastic couplings. Experimental specimens were subjected to the double cantilever beam (DCB) tests according to the ASTM D5528 regulations. Values of the mode I strain energy release rates were calculated by using three different data reduction schemes: the modified beam theory, the compliance calibration method and the modified compliance calibration. Determination of delamination initiation point was conducted in twofold way: by visual observation of crack tip using high resolution camera and by utilization of the acoustic emission technique. Numerical analyss were prepared in Abaqus/CAE Software environment by using the virtual crack closure technique (VCCT). The numerical beam model consisted of SC8R continuum shell elements. Obtained outcomes revealed that extensive fiber bridging phenomenon occurring during delamination process pronouncedly affected propagation values of strain energy release rate (GIprop) and numerically obtained load–displacement curves. Nevertheless, in initial stage of delamination, results obtained by using the VCCT were in agreement with experimental data. The greatest value of the mode I fracture toughness equal 0.56 N/mm was obtained for the BT45 laminate.

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Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Research of Delamination Process in CFRP Laminates with Bending-Twisting Elastic Couplings

Rzeczkowski

Samborski

2022

Materials

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“…They found that an increase in crack speed meant more toughness. Mustafa et al [16] analysis of the Mode-I for numbers of stacking sequences (carbon fiber/epoxy). shown the results, the distribution of the 𝐺 Ic obtained along the delamination front was affected by the ply-angle.…”

Section: Introductionmentioning

confidence: 99%

An experimental investigation of fracture modes and delamination behavior of carbon fiber reinforced laminated composite materials

Alhussein¹,

Ameer²,

Hamzah³

2022

Diagnostyka

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Mechanically, composite laminates perform exceptionally well in-plane but poorly out-of-plane. Interlaminar damage, known as "delamination," is a major issue for composite laminates. Results from Mode-I and Mode-II experimental testing on twill-woven carbon fiber reinforced (CFRP) laminates are analyzed in this paper. Composite Mode-I fracture toughness was determined using three different methods in accordance with ASTM D5528: modified beam theory, compliance calibration, and a codified compliance calibration. Two methods, the Compliance Calibration Method and the Compliance-Based Beam Method, were used to determine the Mode-II fracture toughness in accordance with ASTM D7905. Stick-slip behavior is quite evident in the composite's Mode-I fracture toughness test findings. The MBT technique's 𝐺 Ic values for initiation and propagation are 0.533 and 0.679 KJ/m 2 , respectively. When comparing the MBT approach to the industry-standard ASTM procedure for determining fracture toughness Mode-I, the MBT method was shown to be highly compatible. Furthermore, the 𝐺 IIc values for the CBBM technique are 1.65 KJ/m 2 for non-pre cracked and 1.4 KJ/m 2 for pre-cracked materials. The CBBM method shows a good method to evaluate fracture toughness Mode-II, due to not needing to monitor the length of the crack during delamination growth to get the value of the fracture toughness.

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Simulation of the effect laminate sequence on delamination mode-I with elastic couplings

Cited by 2 publications

References 33 publications

Experimental and Numerical Research of Delamination Process in CFRP Laminates with Bending-Twisting Elastic Couplings

Experimental and Numerical Research of Delamination Process in CFRP Laminates with Bending-Twisting Elastic Couplings

An experimental investigation of fracture modes and delamination behavior of carbon fiber reinforced laminated composite materials

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