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The properties of natural fibers such as poor ultraviolet (UV) resistance and hydrophilicity that reduce the durability of composites limit their usage as reinforcements in polymer matrix composites. To compensate this, new types of composites are proposed in the present study. The tribological behaviors of multiphase composites with polyaspartic polyurea matrix produced by vacuum assisted resin transfer molding (VARTM) technique with jute reinforced, filled by graphene nanoplatelets (GNPs) and titanium dioxide (TiO2) nano-fillers at high temperatures are investigated. The wear tests were performed under 10, 20, and 30 N loads, at 60% humidity and temperatures of 100°C, 125°C, and 150°C using a heat moduled pin-on-disc tribotester with an AISI 4140 counter-surface disc having an average surface roughness value of 1.033 µm. The tests were carried out under dry friction conditions along 6000 m sliding distance at a sliding speed of 2 m/s. The results show that the wear damage types changed according to the nano-filler type. Wear loss and specific wear rate increased with increasing temperature and load in almost all types of composites. Using nano-filler caused irregularities in the change of the friction coefficient. [ABSTRACT FROM AUTHOR]

Accidents in the industry, especially in the field of aerospace, are quite common. Damages like tears cracks and holes occur especially when small sand particles present in the airfield collide with the body and wings of an airplane during takeoff and landing. This torn, cracked, or pierced region should be repaired gently. Damaged parts are frequently small regions for which repair is more suitable than complete replacement as workmanship; cost and time are an important concept in today’s world. A gap occurs between the patches if double-bonded patches are used in the repair of the damaged parts. In this study, the region between patches in a joint with and without intermediate parts was modeled and its effect on strength was examined numerically and experimentally. The effects of patch thickness, overlap length, adherent thickness, and gap length on the strength of the joints with and without intermediate part was compared. The results show that the intermediate part does not have any influence on the strength of the lap joint such that double strap joints without intermediate part have higher failure load. Additionally, it is seen that the failure load decreased with increasing patch thickness and increased with the thickness of the adherent. [ABSTRACT FROM AUTHOR]

In this work, elasto-plastic stress analysis of single lap joints with and without protrusion in adhesive bondline subjected to tension and bending was carried out using 2D non-linear finite element analysis and confirmed experimentally. AA 2024-T3 aluminum adherends were bonded with SBT 9244 film adhesive. The protrusion was obtained by extending the adhesive film by 2 mm from the overlap length at both overlap ends. Three different adher-end thicknesses and overlap lengths for each loading and bondline type were used. The joints with and without protrusion, for comparison, were loaded with the same load for each adherend thickness and overlap length. Finally, it was observed that the protrusion reduces the strength in the joint under tension, while the protrusion increases the strength in the joint under bending. [ABSTRACT FROM AUTHOR]

In this study, stress analysis of double-strap joints used to fasten parts, particularly in aircraft and automotive industries and in the repair of damaged parts, was done using the finite element method. In classical double-strap adhesive joints, patch parts are bonded to the outer surface and these parts resist air flow. To decrease this effect and for constructive and aesthetic requirements, patch parts were embedded into the adherends. The effects of embedded patch parts on failure loads and stress distributions were investigated experimentally and numerically. For this purpose, AA 2024-T3 aluminum adherends with four different thicknesses (4.8, 5.6, 6.4 and 7.2 mm) were bonded as double patches with 0.4, 0.8 and 1.2 mm spring steel patch thicknesses and 20, 40 and 60 mm overlap lengths. The stress analyses were done under plain strain assumption. To verify the finite element model, experiments were carried out. The results show that adherends and patch thicknesses as well as overlap length all have considerable influence on failure loads and stress distributions. [ABSTRACT FROM AUTHOR]

This paper presents an approach to predicting the failure and strength of joints bonded with a film-type adhesive (FM 73) using non-linear finite element method. First, lap-shear tests on Single-Lap Joints (SLJs) with different adherend thicknesses and overlap lengths were carried out and fracture surfaces of the SLJs were examined by scanning electron microscopy (SEM). Then, the stress analyses in the SLJs using a non-linear finite element method were performed by considering both the geometrical non-linearity and non-linear material behaviors of both adhesive and adherend (AA2024-T3), and Finite Element Analysis (FEA) results were compared with experimental results. Two different failure loci were seen when the failure surfaces of the SLJs were examined and both the stress analyses and experimental results showed that a catastrophic failure occured around the central zone of the overlap due to the effect of shear stresses, while the failure at the free edges of the adhesive layer originated from the peel stress in tension. [ABSTRACT FROM AUTHOR]

The use of adhesive bonding as fastener presents very high usage potential, especially for different environments. However, the designers do not have enough data yet to address the changes in the mechanical properties of adhesives in the course of time. In this study, the ageing of film-type adhesives, Structural Bonding Tapes (SBT) 9244 and 9245, which are different in thickness and possess pressure-sensitive and visco-elastic properties, was investigated. First, the bulk adhesive specimens were prepared and exposed to two different environmental conditions until saturated. In the same time, single lap joints with two different adhesive layer thicknesses, consisting of AA2024-T3 as the adherend, were exposed to the same environmental conditions for exposure times of 90 days. The immersion environments were 100% relative humidity (RH) and 3.5% NaCl solution. At the end of exposure time, the failure surfaces were examined by Scanning Electron Microscopy (SEM) after the strength of joints was determined with the lap shear test. Both SBT adhesives absorb more water from 100% RH than from 3.5% NaCl solution and, therefore, they deteriorate rapidly in 100% RH. In addition, as the thickness of adhesive layer increases, the loss in the strength increased. [ABSTRACT FROM AUTHOR]

In this work, elasto-plastic stress analysis of a Single Lap Joint (SLJ) subjected to bending moment was investigated using 2D non-linear Finite Element Analysis (FEA). The SLJs, consisting of hardened steel as the adherend bonded by two adhesives, one stiff and one flexible, with very different mechanical behaviors were analyzed. In order to determine the effect of geometrical parameters on the performance of the SLJs, four different adherend thicknesses and overlap lengths for each adhesive were used. For verification of the analysis, the FEA results were compared with experimental results. It was observed that there was a significant effect of adherend thickness on the strength of the joint with both adhesives. However, the load carried by the SLJ with the flexible adhesive increased with increasing overlap length. [ABSTRACT FROM AUTHOR]