Optimization and analysis of dry sliding wear process parameters on cellulose reinforced ABS polymer composite material

Purpose This study aims to the optimization using three factors and three-level parameters (sliding speed [rpm], sliding distance [m/s] and load [N]) of design matrix were adapted to Box–Behnken design using design expert v8.0 software. Based on the parameters, to develop the linear regression equation and to find the significant considerable wear process parameters based on output responses like wear loss (WL) and coefficient of friction (COF) value of polymer matrix composites (PMC) specimen of Acrylonitrile-butadiene-styrene (ABS)/cellulose composite (80 wt% of ABS and 20 wt% of cellulose). Design/methodology/approach The fabrication of the ABS/cellulose composite sample was carried out by the simple hands-on stir process method. As per the American Society for Testing and Materials G99 standard, the sample was made by the molding process. The wear analysis was made by multi tribotester TR25 machine and validated the developed model by using statistical software design expert v.8.0 and numerical tools like analysis of variance. The surface morphology [field emission scanning electron microscopy (FESEM) analysis] of the sample was also observed using the Quanta FEG-250 FESEM instrument. Findings The parameters like sliding speed, sliding distance and load are independently affected the COF value and WL of the 80% of ABS matrix and 20% cellulose reinforced composite material. The regression equations were generated by the coefficient of friction value and WL, which predicted the minimum WL of 80% of ABS matrix and 20% of cellulose reinforced composite material. The worn surface analysis result exposes the worn path and equal distribution of reinforcement and matrix on the surface of composite material. Originality/value The literature survey revealed a small number of studies available regarding wear analysis of ABS matrix and cellulose reinforced composite materials. In the present work, to fabricate and evaluate the wear performance of PMC (80% of ABS and 20% of cellulose) depends on the WL and COF value. The maximum and minimum COF value (µ) of 80% of ABS and 20% of cellulose composite material is 4.71 and 0.28 with the optimized wear process parameter by 1,000 mm of sliding distance, 0.25 (m/s) of sliding speed and 9 N of load.

The effect of lamina configuration and compaction pressure on mechanical properties of laminated gigantochloa apus composites

This study aims to investigate the mechanical properties of bamboo apus (gigantochloa apus) as a natural reinforced composite material. Bamboo’s laminates of gigantochloa apus were used as reinforcement on the epoxy resin matrix. The parameters examined in this study are the configuration of lamina and compaction pressure. Laminate configuration varies in the number, thickness and direction of the lamina. Compaction pressures of 1.5 MPa, 2 MPa, and 2.5 MPa were used to fabricate the Laminated Bamboo Composites (LBCs). The stem of bamboo with a length of 400 mm was split to obtain bamboo lamina with a size of 400×20 mm. The thickness of bamboo lamina is varied between 1 mm, 1.5 mm, and 2 mm. The bamboo lamina is then preserved by watering it with a preservative solution in the form of 2.5 % sodium tetraborate solution and dried in an oven until the water content reaches 10 %. LBCs were made with a hand lay-up method. After the LBCs were molded, they were pressed with 3 variations of dies compaction 1.5 MPa, 2 MPa and 2.5 MPa. The tensile and bending tests were carried out on the LBCs. Tensile testing is performed in accordance with ASTM standard D3039 and the bending tests were conducted based on ASTM standard D7264. The results show that at each compaction pressure, the highest tensile and bending strength was achieved by LBCs with a thickness of 1 mm of bamboo lamina and 7 layers of bamboo laminates. The LBC with thinner bamboo lamina reinforcement and more layers has the highest tensile strength and bending strength, even it has a lower mass fraction. The LBCs with laminates oriented 0° exhibited greater tensile and bending strengths than the LBCs with laminates structured –45°/+45° and 0°/90°. The LBCs with the 0° laminates direction is matrix fracture followed by lamina fracture. In the 0°/90° direction, matrix fracture is followed by delamination in the 90° and 0° laminates direction. Delamination and lamina clefting were observed in LBCs with laminates oriented +45°/–45°.

Investigate the Crashworthiness of high-velocity bird impact on three different designed model wings by using Coupled Eulerian-Lagrangian approach

Bird strike is a significant threat to the parts of the flying aircrafts. The wing is a central part, which provides stability to the aircraft. Mostly at wing, bird attack the leading edge. Worldwide aviation regulation FRA, EASA, required 4Ib bird strike on the wing of aircraft, and after this bird strike, aircraft is able to be safely landed. This study aims to investigate the resistance of the wing against the bird strike and damage analysis of the high-velocity bird collision on the model wing, inner structure, spar, and ribs. By using the Coupled Eulerian-Lagrangian (CEL) approach in ABAQUS/Explicit. Our contribution 1) bird strike on a wing with assembled inner structure by aluminium and outer skin composed of unidirectional fiber-reinforced composite material. 2) bird strike on-wing which is similar with the first test in which the difference is of spar designed layers of horizontal plates like a comb. 3) bird strike on-wing which is similar with second model wing difference in this wing put an aluminium leading edge on the skin leading-edge, final to analyze the damage of bird impact on the wing, the velocity of bird strike is 200m/s and analyze the behavior of the bird at this velocity. Resistance behavior of composite skin After penetration in the wing, analyze the impact on the spar and stress on the inner structure. Analysis of the kinetic and internal energy graph and Comparison all of these results and check the performance, which gives an excellent result at this velocity. based on these results suggest which inner part is sensitive.

Speed Controlled Composite Fabrication Using DC Motor

Fabrication process determines the composite quality. Conventional method such as dry- and hand lay-up are commonly used. Dry lay-up method has known to be more controllable and produce less defect composites with good mechanical property. However, this method is more expensive. On the other hand, hand lay-up which is more simple and less expensive, is uncontrollable as well as produces more defect and poorer mechanical properties of composites. In this study, we creates instrument which is able to control wet lay-up fabrication process of Fiber Reinforced Composite Material (FRCM). Instead of using uncontrollable human hands, this instrument utilizes speed controllable paint roller which distributes the resin though all matrix. The result shows that the produced composites have more homogenous resin distribution, smaller size defects, and exhibits stronger mechanical properties compare to the one produced by hand lay-up method. This study is expected to open further innovations on low cost composite fabrication.