ENHANCING THE PROPERTIES OF COMPOSITE MATERIAL (ALSIC,TIB2) FOR AERO SPACE APPLICATIONS

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1 ENHANCING THE PROPERTIES OF COMPOSITE MATERIAL (ALSIC,TIB FOR AERO SPACE APPLICATIONS NAGALLI RAGHU Research Scholar Shri JJT university Jhunjunu Rajasthan Abstract: DR. S. CHAKRADHARA GOUD Principal Springfield's Engineering College Chandrayangutta, Hyderabad The applications of aluminum matrix composite materials are growing continuously in the field of automotive and aerospace because of their superior physical, mechanical and tribological properties as compared to base alloy.although aircraft utilizes numerous elements in their construction, the most important of these is aluminum because of its low density, good cast ability, high strength, corrosion resistant and good fatigue strength. Aluminum based composites reinforced with micro/nanosic, AlO3, B4C, TiB, ZrO, SiO and graphite particles, changes the micro-structural characteristics that develop superior mechanical and physical properties appropriate for automotive/aerospace applications.composite materials with metal matrix material e.g. aluminum or magnesium are finding broad level applications in many industries because of their lower density, better wear and corrosion resistance, high strength to weight ratio, good formability, high, high thermal shock resistance, high modulus, high fatigue strength etc. Key words:aerospace, composite materials, ALSIC, TIB, fabrication 1.0 Introduction: A composite material is a heterogeneous mixture of two or more homogeneous phases which are bonded together. The capabilities of composite material in part integration is noteworthy as several metallic components are being successfully replaced by a composite. Wood is good example of a natural composite and paper is a composite made of cellulose fibers and other examples for synthetic composite includes automobile tires, glass fibre-reinforced plastics (GRP s, cutting tool material (cemented carbide. Properties of composite materials are high stiffness to density ratio, high strength to density ratio and high corrosion resistance. Due to this higher specific stiffness and strength, composite parts are lighter than their counterparts 18

2 Figure 1 Composite Material Composites are a combination of at least two different materials with an interface separating the constituents. The suitability of these composite materials for a given application however lies in the judicious selection of synthesizing or processing technique, matrix and reinforcement materials. Matrices can be selected from a number of metal or alloy candidates such as aluminum alloys, and the reinforcement material can have different size and morphology as well as material. These reinforcements can be combined with different matrix materials, which will result in a large number of possible composite material systems..0 LITERATURE REVIEW Ramesh, C.S et al (010 In situ TiB reinforced Al 6063 composites have been successfully synthesized through the chemical reaction between Al 10%Ti and Al 3%B master alloys in the Al 6063 alloy using liquid metallurgy route. The amount of TiB formed in the composite is estimated using gravimetric analysis. Mechanical properties in terms of micro, ultimate tensile strength and modulus of elasticity have been improved by 1%, 47% and 65% respectively in comparison with matrix alloy. Further, ductility in terms of percentage elongation of the composites was found to increase by about 368% when compared with the matrix alloy. The improvement in ductility may be associated with the grain refinement of the composite with an increase in the content of Al 3%B master alloy. Natarajan, S et al (010 A low cost system of Al 6063 xtib (x=0,5,10wt.% in situ metal matrix composites (MMCs were prepared by the reaction mixture of KTiF6 and KBF4 with molten alloy. These in situ prepared composites were characterized by using scanning electron microscope, X-ray diffract meter, and micro analysis. The dry sliding wear behaviour of the prepared composite was investigated by using a Pin on Disc method at different applied loads of 9.8, 19.6 and 9.4N for various temperatures (100, 00 and 300 C. The study at room temperature was also carried out for comparison purpose. The results indicate that the wear rate decreases with the increase in the weight percentage of TiB, while it increases with the increase in the applied load. Rana RS et al (014 manufactured AA 5083 alloy Micron and Nano SiC composites using ultrasonic-assisted stir-casting. Different weight % of Micron SiC (3, 5, 8, 10 wt % & Nano 19

3 SiC (1,, 3 and 4 wt % were utilized for the synthesis of composites. Properties like density, elastic modulus, tensile strength, compressive strength, elongation, and for both aluminum alloy micron and NanoSiC composites were measured. The microstructure characterization of both micron and NanoSiC composites were carried out. Results showed that porosity increases with the increase in weight percentage of SiC. Al Nano SiC shows higher values of elastic modulus, tensile strength and compressive strength compared to Al Micron SiC composites. Hardness of composites increases with the increase in weight percentage of SiC. SEM micrograph indicates a uniform dispersion of SiC particles with some agglomeration in places. The use of ultrasonic vibration on the composite during melting had not only refined the grain microstructure of the matrix, but also enhanced the distribution of sub-micron and nano-sized particles. 3.0 METHODOLOGY Mechanical testing Hardness, categorized as a mechanical property of the material, is defined as the resistance offered by the material to indentation, i.e. permanent deformation and cracking, was determined using a Vickers (Hv micro- test machine. The test is a simple, easy and non-destructive method which is an important and widely used test for the purpose of quickly quantifying or evaluating the mechanical properties of monolithic metals, their alloy counterparts and even composite materials based on metal Compression Test A compression test determines behavior of materials under crushing loads. The specimen is compressed and deformation at various loads is recorded. Compressive stress and strain are calculated and plotted as a stress strain diagram which is used to determine elastic limit, proportional limit, yield point, yield strength and compressive strength. 4.0 Results and discussions: Observations from the In-situ Tensile Tests It is important to note that the given percentage elongation of the different in-situ specimens given troughout the results are not accurate values. For instance should the Ti6Al4V-alloy only accomodate approximately 0.8% elastic deformation according to the litterature, while the the stress-strain curves obtained in Figure 50 in section 5.5 indicated an elastic elongation of up to 3%. The wrongly indicated elongation by the traction-software will be discussed. However, it is the qualitative information from the in-situ tensile tests which is of interest. Note that the insitu specimens tensiled were extracted from different positions in the blocks.. In addition did Orientation Longitudina l Vickers -Hv Trial-1 Trial- Trial-3 Trial- 4 (Kg/mm (GPa D1(μm D(μm Hv(Kg/mm

4 Transverse D1(μm D(μm Hv(Kg/mm Orientation Vickers -Hv Trial-1 Trial- Trial-3 Trial- 4 (Kg/mm (GPa Longitudina D1(μm l D(μm Hv(Kg/mm Transverse D1(μm D(μm Orientation Hv(Kg/mm Vickers -Hv Trial-1 Trial- Trial Trial (Kg/mm (GPa Longitudina D1(μm l D(μm Hv(Kg/mm Transverse D1(μm D(μm Hv(Kg/mm the specimens contain different numbers of deposited layers. See Figure below. The conditions for comparing the deformation mechanism are therefore not identical. 1

5 Figure 4.10 The T00 specimens contain two deposits, while T600 only contains one. This is expected to give microstructural variations between the specimens. The above figure shows the sample made of mixture materials A1 SIC, Fly ash & Husk which shows the material in solid state. The above figure demonstrates the example of metal network composite with deference rates of Al AISIC-79%, TiB - 6%, Fly cinder 8%, Alo3-3%, Magnesium % and Hexachloromethene 4% which a predetermined acquired composite

6 The above figure demonstrates the example of metal framework composite with deference rates of Al %, fly slag - 8%, Husk 6%, Alo3-3%, Magnesium % and Hexachloromethene 4% which a predetermined got composite. The above figure demonstrates the example made of blend materials A1 SIC& TiB and Fly ash fiery debris which demonstrates the material in strong state fracture Surface One in-situ specimen from block T00 was dedicated for tensile testing only to reveal the fracture mode present in the material. The information provided from a fracture surface can contribute to understand more of the deformation mechanisms present in the material. The specimen failured at approximately 9070MPa. NB! This calculation was based on initial cross section area. The fracture surface can be seen in Figure below. The center part of the fracture surface had a faceted appearance. The specimen failured at the end of the specimens. Specimen T00 after failure 3

7 Fracture surface TENSILE TEST: S.No Sample Designations U.T.S (Mpa 1 ALSIC 10 Sample Sample 16 4 Sample 3 14 Above table is tensile test report be half of our testing specimens which are varying just a small difference of 3-4 MPa for different samples. 130 TENSILE Series AL6o61 SAMPLE-1 SAMPLE- SAMPLE-3 The above graph shows the variations of different samples subjected to tensile test. 5.0 Conclusions: 4

8 The present exciting aluminum-based composite/processing and manufacturing technologies, which are promising for automotive and aerospace applicationsthe new materials, fabrication technology starting from metal powders has a huge potential to develop pioneering materials by more economical production systems, which will contribute to the development of highly efficient industrial technologies. The of the composites including with UTS, impact strength, wear resistance, thermal properties were reviewed and on conclusion, it is discovered that as the reinforcement contents increased in the matrix material, the of the composites also increased with increase in tensile strength and decrease in elongation. Selection of exact material in aviation industry is role specific however certain properties such as high specific modulus, good fatigue performance, and high wear and corrosion resistant are seen as universal requirements. Al/ SIC MMC look promising. References: 1. Sahin, Y et al (013, Preparation and some properties of SiC particle reinforced aluminium alloy composites, Materials & Design, ISSN: , Volume No: 4, Issue No: 8, PP: Balaji, P., Arun, D. JegathPriyan, I. Madhan Ram, E. Manikandan (005, Comparative Study of Al 6061 Alloy with Al 6061 Magnesium Oxide (MgO Composite, International Journal of Scientific & Engineering Research, ISSN: , Volume No: 6, Issue No: 4, PP: Dinaharan I, Kalaiselvan K, Murugan N (017, Influence of rice husk ash particles on microstructure and tensile behavior of AA6061 aluminum matrix composites produced using friction stir processing, Composites Communications, ISSN: , Volume No: 3, Issue No:, PP: Fatchurrohman, N., S. Sulaiman, M.K.A. Ariffin, B.T.H.T Baharuddin, A.A. Faieza (01, Solidification Characteristic Of Titanium Carbide Particulate Reinforced Aluminium Alloy Matrix Composites, Journal of Engineering Science and Technology, ISSN: , Volume No: 7, Issue No:, PP: Hajizamani, M., Baharvandi, H (011, Fabrication and studying the mechanical properties of A356 alloy reinforced with AlO3-10% Vol. ZrO nanoparticles through stir casting, Advances in Materials Physics and Chemistry, ISSN: , Volume No: 1, Issue No:, PP: Jain P.K (009, Ultrasonic Cavitation Assisted Fabrication and Characterization of A356 Metal Matrix Nano composite Reinforced with Sic, B4C, CNT, AIJSTPME, ISSN: , Volume No:, Issue No:, PP: