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The mechanical properties and vibration damping characteristics of cross-ply laminates ([90°/0°/90°] and [0°/90°/0°]), [0°/45°/0°], four-layered angle ply laminate ([90°/0°]s) and Quasi-isotropic laminates ([0°/90°/45°]s, [0°/45°/90°]s,) containing 50 ± 2 wt% of banana fibres in polyester matrix were investigated. The experimental results indicate that the tensile strength, Young’s modulus, impact strength, and the natural frequency were superior for [0°/90°/0°] laminates. In the case of flexural properties, the Quasi-isotropic laminates displayed better performance than the other configurations. Tensile fractured specimens were examined under a scanning electron microscope (SEM) to understand the difference in failure behavior due to the inter-ply orientation in the laminate.

This article introduces an investigation of path planning with ply orientation information for automatic fiber placement (AFP) on open-contoured mesh surface. The new method makes use of the ply orientation information generated by loading characteristics on surface, divides the surface into several zones according to the ply orientation information and then designs different fiber paths in different zones. This article also gives new idea of up-layer design in order to make up for defects between parts and improve product’s strength.

This article reports an investigation of path planning with multi reference paths for robotic fiber placement (RFP) on open-contoured mesh surface. The new method considers the ply orientation information determined by loading characteristics, divides one surface into different parts according to the ply orientation information and then designs different initial reference paths in different parts. This article also proposes new up-layer design in order to make up for defects between parts and improve strength.

The mechanical performance of a composite structure is influenced by residual stresses induced during curing and post-processing. Therefore, residual stress evaluation is important especially as layers increase in laminated composites. The general aim of this study is to present a fundamental relation between residual stresses (due to manufacturing process) and the relative angle between plies (±θ) in a two-layered, carbon-fibre reinforced epoxy-resin laminate. The residual stresses along the loading direction were determined using the X-Ray Diffraction technique at different locations in a specimen. The maximum numeric value obtained was compared with the residual stress obtained from the Abaqus software using Universal Tensile Test data for failure.

Composite laminates are used in many applications in industries like aerospace and aircraft due to their extremely high strength to weight ratio and corrosion resistance properties. The composite laminates are difficult to machine materials, which results into low drilling efficiency and drilling-induced delamination, thus it is important to develop a suitable CFRP material with different ply orientation to overcome the difficulties related in machining of composite materials. The focus of present work presents a comparative study involving experimental characterization with different ply orientation to understand the effect of cutting parameters on the thrust force, delamination extent and exit hole diameter during conventional drilling of carbon fiber reinforced polymer. Processing parameters such as, feed rate plays dominant role in delamination than spindle speed in both ply orientation. The analysis shows that conventional drilling with [0/90]16 ply yields lower delamination and hole size variation than [(0/45/90/-45)]4s ply orientation.

The main concern of this work is to investigate the influence of number and orientation of ply on tensile properties of hybrid composites. Hybrid composites are those materials which consist of two or more distinct fibers embedded in the same matrix. For this analysis, the elastic behavior of individual fiber-reinforced composite lamina is required. The properties of a single lamina of composites can be determined by the micromechanical homogenization. From this analysis, it is seen that elastic modulus, Poisson's ratio, and shear modulus are the functions of the volume fraction of the fiber and matrix. These properties can be further used for analysis of hybrid composite laminate. In this work different hybrid composites material with a different number of plies and orientations are used to simulate with finite element software. At first, a 3D model of three-ply is used for the simulation. The other model with four, five and six-ply has been used. The influence of number and orientation of ply on tensile properties of hybrid composites is the main goal of the work. The comparison of stiffness between different ply models has established that the number ply influences the strength of hybrid composites. From this work, it is seen that as number ply increases the tensile strength also increases. For the investigation of the influence of the ply orientation, different orientations of ply are used. From different simulation results, it is seen that ply orientation with 00 is the best for the tensile strength.

In the present work the effect of the different ply orientations and nano filler on the bearing strength and failure mode of the pin joints is investigated both experimentally and numerically. Glass-epoxy composite laminates were prepared with [0°/45°/90°], [0°/45°/0°] and [0°/90°/0°] ply orientations. Nanoclay filler with 1, 2, 3, 4 and 5wt% were added in the epoxy for the said orientations to prepare the pin joints. Results show that the strength of the pin joints is drastically dependent on both ply orientations and nanofiller wt%. The joint geometry i.e., the distance from the free edge of specimen to the diameter of the hole (E/D) ratio and width of the specimen to the diameter of the holes (W/D) ratio were also investigated which effected the failure mode of the joints. Tsai-Wu failure theory along with the characteristics curve method was used for the prediction of failure modes numerically.

With the advancement of composite materials and their manufacturing technologies, composites, recognized for their high specific strength, excellent electrical insulation, superior corrosion resistance, and enhanced designability, are garnering increasing attention. To investigate the flexural behavior of laminated composite beam structures, finite element simulation analysis was employed. The specific work conducted is as follows: 1) Due to the complex architecture and anisotropic properties of laminates, ABAQUS software was utilized for modeling and simulating the laminated composite beam structures. The deformation contour was obtained, allowing for the determination of the maximum deflection. 2) The influence of geometric parameters on deflection was summarized by conducting simulations with variations in the length and thickness of the laminated beams. 3) Simulations were performed by altering the fiber ply orientation angles and the elastic modulus ratio of the laminates. Trend curves were plotted using Origin software, and the effects of these material parameters on deflection were summarized.

This study proposes a non-deterministic robust topology optimization of ply orientation for multiple fiber-reinforced plastic (FRP) materials, such as carbon fiber–reinforced plastic (CFRP) and glass fiber–reinforced plastic (GFRP) composites, under loading uncertainties with both random magnitude and random direction. The robust topology optimization is considered here to minimize the fluctuation of structural performance induced by load uncertainty, in which a joint cost function is formulated to address both the mean and standard deviation of compliance. The sensitivities of the cost function are derived with respect to the design variables in a non-deterministic context. The discrete material optimization (DMO) technique is extended here to accommodate robust topology optimization for FRP composites. To improve the computational efficiency, the DMO approach is revised to reduce the number of design variables by decoupling the selection of FRP materials and fiber orientations. In this study, four material design examples are presented to demonstrate the effectiveness of the proposed methods. The robust topology optimization results exhibit that the composite structures with the proper ply orientations are of more stable performance when the load fluctuates.

This work aims to explore crashworthiness of square aluminum/CFRP tubes with different hybrid schemes under quasi-static axial loading condition, and maximize their crashworthiness by performing multi-objective discrete robust optimization design. In the present study, metal/CFRP hybrid tubes with two hybrid schemes and their corresponding individual tubes are manufactured. The crushing process and crashworthiness indictors of all specimens are experimentally investigated under quasi-static axial crushing load. According to the experimental results, the AC hybrid tubes, made of outer aluminum square tube and internally adhered CFRP layers, show excellent energy-absorbing characteristics. Subsequently, numerical simulations are performed for the AC hybrid tubes to further investigate the effects of aluminum wall thickness, CFRP layer number and ply orientation on the energy-absorbing characteristics. It is found that the total energy absorption increases with the increasing tubal wall thickness of aluminum and CFRP layer, and ply orientation makes great contribution to the overall deformation modes and energy-absorbing characteristics of AC hybrid structures. Finally, a multi-objective discrete robust optimization has been conducted to optimize AC hybrid structures for the optimal crashworthy performance.