Hybrid MMCs are a new class of materials that exhibit superior characteristics and functional response when compared to monolithic alloys and mono-reinforced MMCs, and thus have tremendous potential for widespread application in modern industrial and engineering applications. Since the manufacturing fraternity is proliferating, a cyclic evaluation of understanding the behavior of hybrid MMCs and their evolution is needed. Therefore, to address this necessity, this paper presents a detailed review of hybrid MMC manufacturing methods, materials (MATRIX and reinforcement) used, physicomechanical, tribological, and corrosion properties, and challenges associated with hybrid MMCs. This retrospective investigation presents the state of the art of hybrid MMC materials in the categories involving MATRIX materials and their alloys, ceramics reinforcements and secondary reinforcements, and the applications and formation of microstructures. This paper also discussed the overview and the status of various MATRIX and reinforcement materials in manufacturing hybrid MMCs using different fabrication methods. Further, the significant challenges associated with the fabrication of hybrid MMCs using different manufacturing methods, such as distribution of reinforcement, wettability, and other common limitations identified in the literature, are presented. This paper provides a broad-spectrum attitude on hybrid MMCs techniques, challenges, and future research directions.

In this work, the production and properties of Al 6061/SiC COMPOSITES, made using a squeeze casting method, were investigated. SiC performs were manufactured by mixing SiC powder, having a 16 and 22 mm particle size, with colloidal silica as a binder. 6061 Al melt was squeeze cast into the pores of the SiC perform to manufacture a DRA composite containing 30v/o reinforcement. The aging behavior, tensile properties and fracture mechanism of the cast material were studied. The results show that higher hardness, yield strength, tensile strength and Young's modulus can be obtained by the addition of SiC particles to 6061 Al alloy, whereas tensile elongation decreases. This is mainly caused by a thermal mismatch between the METAL MATRIX and the reinforcement, which leads to a lower grain size of the MATRIX with more dislocation density. It was also found that the precipitation kinetics of GP zones in the composite material was accelerated, owing to the heterogeneous nucleation capability of metastable phases on the SiC particles. Decreasing the SiC particle size resulted in better mechanical properties and a faster aging response. Nevertheless, the decohesion of the interface between the METAL MATRIX and SiC particles led to the formation of voids which, subsequently, coalesced to generate the ductile rupture of the METAL MATRIX.

The scientific importance of nanoCOMPOSITES is being increased due to their improved properties. This paper is divided into two parts. First, Al-Al2O3 nanocomposite was produced by using ball milling technique followed by cold compaction and sintering. Microstructure and morphology studies were done through SEM, TEM, and EDX analyses on the produced powder. The mechanical properties of the produced composite were determined by the tensile test. Also, nano-indentation experiment was conducted on the produced composite to determine its hardness. Second, a 2-D axisymmetry model was implemented in ANSYS software to simulate the nano-indentation experiment on pure aluminum and Al-Al2O3 nanocomposite. A conical indenter with 70.3o was considered in simulations. The results show that, a homogenous distribution of the reinforcement in the MATRIX was achieved after 20 h milling. The elastic modulus, yield strength, and the hardness of the produced composite were increased compared to the pure METAL. The finite element (FE) simulation results showed a good agreement with the experimental results for nano-indentation experiment. The scatter of the FE results from the experimental results in the pure METAL was smaller than that observed for the nanocomposite.

The elastoviscoplastic behavior of METAL MATRIX COMPOSITES with various fiber aspect ratios subjected to multi-axial loading is studied by a 3D time-dependent micromechanical model in the presence of interfacial damage. The representative volume element of the COMPOSITES consists of three phases, fiber, MATRIX and fiber/MATRIX interphase. The effects of thermal residual stresses induced from the manufacturing process are included in the analysis. The fiber and interphase are assumed to be elastic, while the MATRIX exhibits elastic-viscoplastic behavior with isotropic hardening. The Bodner-Partom viscoplatic theory is used to model the time dependent inelastic behavior of the MATRIX. The Needleman model is employed to analysis interphase damage. While predictions based on undamaged interphase are far from the reality, the predicted thermomechanical behavior including interphase damage and thermal residual stresses demonstrate very good agreement with experimental data.

Due to the significant increase in demand for materials with new capabilities, the use of composite materials is increasing. These materials have unique properties such as high wear resistance and a high strength-to-weight ratio, and are used by engineers in various industries, particularly in the aerospace and automotive sectors. Due to the METALlic nature of these materials, the machining process is an integral part in achieving the shape and properties of the final product. Among composite materials, aluminum-based COMPOSITES are the most widely used in industry. In this study, a methodical was conducted, study including statistical modeling using the response surface method and deriving regression equations of the effect of spindle rotation speed, feed rate, and depth of cut on surface roughness, METAL removal rate, and tool wear during machining of A359/B4C/Al2O3 MATRIX aluminum composite. It was found that an increase in spindle rotation speed, feed rate, and cutting depth increased METAL removal. The best combination of parameters that was found to simultaneously minimize the surface roughness and maximize the METAL removal rate and minimize flank wear was a spindle speed of 600 rpm, a feed rate of 0. 075 mm/rev, and a cutting depth of 0. 20 mm

The physical, mechanical and tribological behavior of Aluminum (Al) alloy LM13 reinforced with Nanosized Titanium Dioxide (TiO2) particulates were investigated in this study. The amount of nano TiO2 particulates in the composite was varied from 0. 5 to 2% in 0. 5 weight percent (wt. %) increments. The Al-LM13-TiO2 METAL MATRIX COMPOSITES (MMCs) were prepared through the liquid METALlurgical method by following the stir casting process. The different types of Al LM13-TiO2 specimens were prepared for examining the physical, mechanical, and tribological characteristics by conducting ASTM standards tests. Microstructural images, hardness, tensile, and wear test results were used to evaluate the effect of TiO2 addition on Al LM13 samples. Scanning Electron Microscope (SEM), Energy Dispersive Spectroscopy (EDS), and X-Ray Diffractometer (XRD) were used to examine the microstructure and distribution of particulates in the MATRIX alloy. In the Al LM13 MATRIX, microstructure analysis indicated a consistent distribution of reinforced nanoparticles. The attributes of the MMCs, including density, hardness, tensile strength, and wear resistance, were improved by adding up to 1 wt. % TiO2. Fractured surfaces of tensile test specimens were examined by SEM studies. The standard pin-on-disc tribometer device was used to conduct the wear experiments,the tribological characteristics of unreinforced MATRIX and TiO2 reinforced COMPOSITES were investigated. The COMPOSITES’ wear resistance was increased by adding up to 1 wt. % of TiO2. The wear height loss of Al LM13-TiO2 composite increased when the sliding distance and applied load were increased. Overall, the Al LM13 with one wt. % of TiO2 MMCs showed excellent physical, mechanical and tribological characteristics in all the percentages considered in the present study.

The aim of this paper is investigation of progressive damage in a METAL MATRIX composite lamina usingcoupling of micromechanical method and continuum damage mechanics viewpoint. Themicromechanical method is a representative volume element- based method known simplified unit cellmethod which possesses the capability of investigating progressive damage and plastic behavior in therepresentative volume elements. The studied damage is isotropic and anisotropic based on continuumdamage mechanics viewpoint. Composite system under investigation is Carbon/Aluminum composite.The MATRIX behavior is considered as isotropic and elastoplastic and the fiber behavior is transverselyisotropic and elastic. The fiber arrangement within the MATRIX is regular. The MATRIX elastoplasticbehavior model is included as bi-linear behavior and solution method is successive approximationmethod. According to available previous studies, Silicon-carbide/Titanium composite system is notedfor validation and comparison with experimental data. Also, the effect of fiber volume fraction on thedamage progression routine is studied. The results show that by increasing the longitudinal andtransverse loadings, the damage variable grows the fiber direction and perpendicular to the fiberdirection and the axial and transverse Young's modulus decrease subsequently. Also, the results provethat in longitudinal loading, considering anisotropic damage, damage progression in the fiber directionis more than its growth, perpendicular to the fiber direction. Whereas, under transverse loading, damagegrowth in perpendicular to the fiber direction is faster.

Fatigue of the components is a critical aspect that needs to be addressed for effectively using the Aluminium METAL MATRIX COMPOSITES in a variety of applications, especially the aircraft components, since the damage that occurs due to fatigue is progressive and may lead to overall failure of the structure of the aircraft. Henceforth in the present work, the fatigue behavior of Aluminium AA 5083 MATRIX reinforced with varying weight percentage of silicon carbide viz., 3, 5, 7 and 9 and varying weight percentage of fly ash viz., 2, 3, 4 and 5 and fabricated enroute the process of stir casting at four different parameters viz., the stirring speed of 50, 100, 150 and 200 rpm, and the stirring duration of 15, 20, 25 and 30 min are evaluated. The main purpose of fatigue characterization accomplished in accordance with ASTM F1160 standards on a typical RR Moore rotating beam fatigue testing machine is to distinctly evaluate the life cycle of components that are fabricated from METAL MATRIX COMPOSITES and eventually develop a framework model for the significant study of fatigue strength of the structure with persistent striations all along the interstitial of aluminium-silicon carbide-fly ash interfaces. Fatigue is a stochastic process rather than a deterministic one, thus in the present work, Analysis of Variance (ANOVA) is carried out to establish the authenticity of the results and validate them. The results and plots are presented with suitable rationale and inferences considering the stress range, stress amplitude and number of cycles to failure.