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Öğe Comparison of Hashin and Puck criterions for failure behavior of pin loaded composite plates(John Wiley and Sons Inc, 2024) Doğan, Caner; Kaman, Mete Onur; Erdem, Serkan; Albayrak, MustafaIn 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. © 2024 Wiley-VCH GmbH.Öğe Design and production of new type reinforced U-profile composite panels(Toros University, 2024) Uslu, Merve; Kaman, Mete Onur; Yanen, Cenk; Albayrak, Mustafa; Dağ, Serkan; Erdem, Serkan; Turan, KadirIn aircraft design, factors such as fuel efficiency, lightness and durability are critical due to the effect of various loads. Therefore, the use of "U" profile beams, which are stronger in terms of strength, provides versatile advantages. In this study, a reinforced composite panel was designed and fabricated by adding support beams to the "U" profiles to maintain the safety and integrity of aircraft structures. Glass fiber and epoxy resin were employed in the composite production process. The vacuum infusion method was employed for composite production, with molds specifically designed for the "U" profile and "I" support beams. Following production, the compatibility of the "U" profile, "I" support beam and sub-composite base forming the composite panel was evaluated. It was determined that the produced "I" support beam constituted only 18.8% by weight of the composite panel.Öğe Effects of translaminar edge crack and fiber angle on fracture toughness and crack propagation behaviors of laminated carbon fiber composites(Walter De Gruyter Gmbh, 2024) Asan, Ahmet Murat; Kaman, Mete Onur; Dag, Serkan; Erdem, Serkan; Turan, KadirIn this study, the translaminar fracture toughness of carbon fiber laminated composites with different layer sequences was investigated experimentally and numerically for different crack directions. In the numerical study, first of all, the critical stress intensity factor was determined by using the M-integral method. Three-dimensional model and M-integral analysis were achieved in the ANSYS finite element package program. The non-local stress fracture criterion was used to in order to find failure curves of the materials. Then, in order to find the crack propagation directions numerically, the solid model was transferred to the LS-DYNA program and progressive failure analysis was performed. Fracture toughness decreased by 9.92 % with the change of crack angle from 15 degrees to 90 degrees. As the fiber angle changed from 0 degrees to 45 degrees, it decreased by 9.17 %. The biggest error between the experimental and numerical study results was found at alpha = 45 degrees, with a rate of 12.3 %.Öğe Investigation of mechanical behavior of reinforced u-profile composites under low velocity impact(Ahmet ÇALIK, 2024) Uslu, Merve; Kaman, Mete Onur; Albayrak, Mustafa; Yanen, Cenk; Dağ, Serkan; Erdem, Serkan; Turan, KadirIn this study, the impact resistance of reinforced composite panels with unsupported, and U profile supported by I profile was numerically examined. For this purpose, firstly, unsupported glass fiber/epoxy composite panels were designed, and then I-profile composite supports were added to these panels. The impact strength, and damage behavior of supported, and unsupported specimens under low-velocity impact were compared numerically. In the analysis, the MAT22 material card, also known as the Chang-Chang damage model for composite material, was used in the LS-DYNA program. As a result of the analysis, maximum damage load of the unsupported specimen is determined to be approximately 294 N. It was determined that by adding an I profile to the structure, the maximum damage load increased to 543 N. It was seen that the added I profile supports increased the maximum contact force of the composite structure by approximately 85%. Fiber breakage damages were observed in both supported, and unsupported specimens. However, with the use of I profile support, the damaged area was further reduced. It has been determined that under low-velocity impact, supported specimens exhibit more rigid material behavior than unsupported specimens.Öğe Investigation of the translaminar fracture behavior of the fiber-reinforced composites stitched perpendicular to their plane(Springer Heidelberg, 2024) Asan, Ahmet Murat; Kaman, Mete Onur; Dag, Serkan; Erdem, Serkan; Turan, KadirTo increase the fracture toughness, the two-dimensional laminated textiles can be stitched with fibers throughout their thickness. But the stitch properties effect the mechanical behavior of the composite plates. Because of this reason, in this study, translaminar toughness of carbon fiber composites stitched with different densities and angles is investigated for the first time, experimentally and numerically. In the experimental study, fracture tests are performed according to ASTM E1922 standard and critical load; crack tip opening displacements and fracture toughness values are determined. In the numerical study, the critical stress intensity factor is determined using the M-integral method and the displacement correlation method. Modeling and fracture toughness analyses are performed in ANSYS finite element package. In order to find the crack propagation directions numerically, the model prepared in ANSYS is transferred to the LS-DYNA program and progressive failure analysis is performed. Stitching the layered composites perpendicular to the plane has increased the fracture toughness by 23.5-80.6% for plain-woven composites and 1.41-9.38% for UD composites. Fracture toughness values have increased with increasing stitch density. This increase is highest in the specimen stitched in the longitudinal direction where the toughness increased by similar to 15.4% with 100% increase in stitch density. The highest fracture toughness is obtained with double-directional stitching with a stitch density of 1.25 mm. It is determined that the designed heterogeneous model gives more accurate results than the homogeneous model by similar to 1-6%.
