To fabricate ultra-fine grain structures containing high strength, accumulative roll bonding is a kind of severe plastic deformation (SPD). In the present study, magnetic Al/ Fe2O3 COMPOSITES reinforced with 0, 2. 5% and 5Wt. % of Fe2O3 particles have been manufactured via ARB. A uniform distribution of Iron oxide particles was achieved after the 8th cycles of ARB. Mechanical properties include (hardness, elongation, toughness) and also, magnetic and electrical properties such as magnetic saturation, magnetic permeability and magnetic residuals were studied. The presence of Fe2O3 particles improved the mechanical, electrical and magnetic properties of this kind of LAMINATED COMPOSITES. Vibrating sample magnetometer was utilized to study the magnetic properties of samples vs No. of steps.

With advanced COMPOSITES increasing replacing traditional metallic materials, the material inhomogeneity and inherent anisotropy of such materials lead to not only new attributes for aerospace structures, but also introduce new technology to damage tolerant design and analysis.The deleterious effects of changes in material properties and initiation and growth of structural damage must be addressed. The anisotropic and brittle properties make this requirement a challenging to composite structural designers. Accurate, reliable and user-friendly computational methods, design and analysis methods are vital for more damage tolerant composite structures.Both durability and damage tolerant methodologies must address the possible changes in mechanical properties and the evolving damage accumulations that may occur during the vehicle’s service lifetime. Delamination is a major failure mode in LAMINATED COMPOSITES and has received much research attention. It may arise out of manufacturing defects, free edge effects, structural discontinuities, low and high velocity impact damage, and even bird strikes. Early pioneering work established that the reduction in strength following delamination damages placed severe limits on the design allowable for highly loaded components such as aircraft wing and fuselage structure. In the present article, we provide a state-of-art survey on damage tolerant design correlated failure behavior and analysis methodologies of LAMINATED COMPOSITES. Particular emphasis is placed on some advanced formulations and numerical approaches for efficient computational modeling and damage tolerant analysis of LAMINATED COMPOSITES.

In this paper, progressive damage and global failure of composite laminates under quasi-static, monotonic loading are investigated using 3D continuum damage mechanics.For this purpose, a finite element program has been developed using an eight-node 2D layered element including layer-wise plate theory. Damage analysis of a single orthotropic layer under various uniform in-plane and transverse loading conditions, and laminate problems with diffuse damage under simply supported and distributed transverse loading conditions are performed. The effects of modeling parameters such as hardening rules and mesh densities along the laminate thickness and in-plane surface on the progressive damage response and global failure are also investigated.

In this paper, we will study the calculation of the optimized weight of LAMINATED COMPOSITES under a load equals their ultimate strength. A variety of fracture criteria have been defined for this class of composite in literature; in this study we use Tsai- Hill theorem as the fracture criterion. The base of this theorem is the Classical Lamination Theory (CLT). A DOT algorithm is employed as the optimization technique with a direct use of real variables. Since optimization is a very time consuming process, we will use Radial Basis Function Neural Networks (RBFNN) to predict output. The optimization process continues in FORTRAN environment until the optimum result is achieved.

In recent decades polymeric COMPOSITES have received considerable attention from different industrial sectors due to their outstanding properties. Despite the multi-purpose properties, polymers undergo creep even at room temperature which is considered as a disadvantage for their long-term applications.Numerous methods have been suggested by researchers in order to predict creep in polymeric COMPOSITES. In this article, a brief review is conducted on fundaments of creep in polymers and different theoretical methods presented for creep modeling in long fiber reinforced LAMINATED COMPOSITES are categorized. Then, a new method for evaluating long-term creep in polymeric COMPOSITES relying on short-term experimental data on pure resin is developed. The developed model is just in need of simple tension-creep tests on pure resin as input and creep behavior of pure resin is evaluated accordingly. Then, the results are used to estimate creep behavior a single composite laminate and finally creep behavior of LAMINATED COMPOSITES with arbitrary lay-up configurations is theoretically characterized. In parallel, the capability of micromechanical rules in estimating creep behavior of COMPOSITES using its constituent's behavior is investigated. A comparison between published experimental observations and theoretically obtained results imply on proper performance of developed modeling procedure for analyzing creep phenomenon in polymeric COMPOSITES.