Review on Manufacturing of Fibre Metal Laminates and Its Characterization Techniques

International Journal of Mechanical Engineering and Technology (IJMET) Volume 8, Issue 10, October 2017, pp. 561–578, Article ID: IJMET_08_10_063 Available online at http://iaeme.com/Home/issue/IJMET?Volume=8&Issue=10 ISSN Print: 0976-6340 and ISSN Online: 0976-6359

REVIEW ON MANUFACTURING OF FIBRE METAL LAMINATES AND ITS CHARACTERIZATION TECHNIQUES

K.Logesh Research scholar, Department of Mechanical Engineering, Sathyabama University, Chennai, Tamil Nadu, India

V.K.Bupesh Raja Professor & Head, Department of Automobile Engineering, Sathyabama University, Chennai, Tamil Nadu, India

Vipin H Nair, Sreerag K.M, Vishvesvaran K.M and M.Balaji UG Scholar, Department of Mechanical Engineering, Veltech Dr.RR & Dr.SR University, Chennai, Tamil Nadu, India

ABSTRACT Fibre Metal Laminates (FML) is new class of materials which are in high demand because of its superior mechanical and metallurgical properties. Such materials can be manufactured by a variety of ways depending on size required, end application and cost affordability. However FML are susceptible to defects which are governed by factors such as type of skin and core material selected, preparation method used, post treatment and load applied. Possible defects can be overcome by following care while preparing the material as per end requirements. FML can be used for applications which demand low weight to high strength ratio such as aeronautics, automobiles, marine and structures. Keywords: Fibre Metal Laminates, Skin, Core, Preparation Method, Mechanical Properties, Post Treatment. Cite this Article: K.Logesh, V.K.Bupesh Raja, Vipin H Nair, Sreerag K.M, Vishvesvaran K.M and M.Balaji, Review on Manufacturing of Fibre Metal Laminates and its Characterization Techniques, International Journal of Mechanical Engineering and Technology 8(10), 2017, pp. 553–560. http://iaeme.com/Home/issue/IJMET?Volume=8&Issue=10

1. INTRODUCTION Advancements in the field of materials and manufacturing have brought forward new kinds of materials. Laminate materials are new class of composite materials which have been developed recently. Such materials are tailor made to be used for specific applications. The first fibre metal laminate was developed during 1967. It was found that in comparison with a

http://iaeme.com/Home/journal/IJMET 561 [email protected] K.Logesh, V.K.Bupesh Raja, Vipin H Nair, Sreerag K.M, Vishvesvaran K.M and M.Balaji typical aluminium sheet, a laminate of same thickness made of fibre and aluminium had twice the fracture toughness [1]. Like a typical composite material, laminate materials are generally produced to enhance the overall properties such as low density and corrosion resistance of the fabricated components [2-3]. However the properties of such materials get shared to give benefits as well as drawback such as low fatigue resistance and high moisture absorption [4- 14]. The innumerable combination of materials that can be combined to create a composite material, makes it open ended to research and development. Such materials are used extensively in aeronautics, automobiles and structural materials [15-19]. In this paper, sandwich material, which is a type of composite material is considered and discussed. A sandwich material consists of layers of its composition arranged to replicate a sandwich, such as plywood. Fig.1. shows the morphology of typical sandwich materials. It consists of a skin which acts as the matrix, while the interlayer acts as the reinforcements. Like any composite material, the composition of the sandwich material can be selected based on the end requirement, i.e, the properties desired from the produced composite. There can be several layers between the outer skins in the sandwich material.

Figure 1 A typical laminate material [20]

1.1. History of Laminate Materials The earliest known literature about the use of bonded laminate structures dates back to 1950 [21]. It was revealed that Fokker Aero-structures of Netherlands made first attempts to prevent emergence of fatigue cracks by using laminated materials. It was identified that its performance was better than monolithic structures made up of same materials. Research on Fibre metal laminates (FML) was coined by Aerospace Engineering in Delft University of Technology, Netherlands. They developed a fibre metal laminates comprising of Aramid fibres in Aluminium laminates (ARALL) [22-23]. It was commercialized during 1982 with two variations: ARALL 1 with AA7075 as the laminate and ARALL 2 with AA2024 as the laminates. Later two more types of ARALL came into existence and commercialized respectively. More research on FML brought forward Carbon reinforced Aluminium laminates (CARALL). In 1989, Glass Laminate Aluminium Reinforced Epoxy (GLARE) was developed and patented [24]. It was later commercialized in 1991 [25]. Generally E-glass fibres are used to make GLARE.

1.2. Classifications of FML Numerous research activities in FML have given rise to many different kinds of laminated materials. Figure 2 shown below reveals the classifications of FML. Based on the layup of the reinforcements a FML can be of two types: Unidirectional Hybrid Laminate (UDHL) and Cross-ply Hybrid Laminates (CPHL). Comparatively the CPHL is better in terms of impact performance and damage resistance [26]. Fig.3 shows the general layup of reinforcements and metal laminates of a sandwich material. In case of UDHL the fibres will be either oriented in 00 or 900 orientations. In the CPHL fibres will be twined similar to the form of textile fabrics.

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Based on the material used as the laminate, FML can be of the following types: Titanium based FML, Magnesium based FML and Aluminium based FML. CARALL, GLARE and ARALL are classes of Aluminium based laminates. There are four types of ARALL and six types of GLARE, each having specific properties depending upon the types of aluminium used to fabricate the same [22-23]. The materials chosen as the laminate is such that it contributes to the reduction in weight of the FML without sacrificing its superior mechanical properties such as high strength, yield strength, impact resistance, etc. Titanium has the advantage of strength to weight ratio, however it is not preferred for low applications. The mechanical properties such as impact resistance and hardness of magnesium is lower than aluminium and titanium, hence it is preferred only for applications which do not required high strength. Aluminium has some advantages like strength to weight ratio, fatigues and corrosion resistance[24-27]. Applications of aluminium metal laminates includes aero structures and automobile components [21-24][28-31]. Based on the types of reinforcements used FML are of the following types: Kevlar reinforced laminate, CARALL and GLARE. Kevlar has the benefit of extremely light weight however being costly makes its applications restricted to scientific research and government aided projects. Glass and carbon fibre has the advantages of low cost yet reliable hence highly preferred for commercial applications [22]. Based on the layup of the laminates and reinforcements in FML can be of the following types: 2/1 laminate in which there will be one layer of reinforcement sandwiched between two metal laminates and 3/2 laminate in which there will be three layers of metal laminates separated by two layers of reinforcements. The fibre may be oriented in different directions between the laminates [32-34]. Figure 4 shows a 3/2 laminate.

Figure 2 Classification of Fibre Metal Laminates

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Figure 3 Layup of reinforcements and metal laminates in FML [35]

Figure 4 3/2 laminate materials [36]

2. FABRICATION OF FML FML are prepared with an aim of reducing the overall weight without sacrificing the beneficial properties on a specific application [24][37]. Fabrication of FML consists of four steps: pre-treatment, preparation of prepreg, production of FML and post treatment.

2.1. Pre treatment The skin has to be pre-treated in order to enable proper bonding of the metal laminate with the reinforcements. The skin and the fibre reinforcements have to be cut to the required dimensions before carrying out the pre-treatment processes [38]. Modification of surface properties of the skin or metal laminate is carried out by mechanical abrasion and degreasing by using solvents [25][39]. The procedures for pre-treatment were explained with the following steps [40]: • Degreasing the metal laminates by immersing it in Methyl Ethyl Ketone (MEK) solution, • Cleaning with water, • Creation of micro roughness using a 400 and 200 grit abrasion papers. Any contaminants were wiped out using tissue papers, • Etching for 10 minutes at room temperature by immersing it in a 5% NaOH solution, • Rinsing with hot water, • Etching the metal laminate for 12 minutes in sulfochromic solution. (ASTM standard D2674-72, 2004) and (ASTM standard D2651-01, 2004) standards were used during the etching process,

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• Producing porous layers of pseudoboehmite aluminum oxyhydroxide (ALOOH) on the metal laminate by immersing it in hot water for one minute, • Coating the surface of the metal laminate using an organosilane adhesion promoter, γ- Glycidoxypropyltrimethoxy silane (γ-GPS), • Drying in an oven at 1000C for one hour. It was noted that the coating improved the strength and durability of the adhesive. The metal laminate used for his study was aluminium.

2.2. Preparation of the prepreg The preparation of FML is preceded by the manufacture of prepregs[25]. A single sheet of fabric reinforcement can be cut to the desired size and held in a mould [41]. The mould is the connected to resin feed and a vacuum source as shown in Fig.4. The transfer of resin from source towards the vacuum enables ingression of the resin into the fibre. This is called as resin ingression technique. In order to delay the curing of the resin with the fibre, the mould is transferred to a deep freezer and held for 24 hours at -180C. The prepreg which is the uncured resin impregnated fibre is wrapped in a polythene sheet and frozen for future use. Prepreg produced in this manner was called as just-in-time prepreg (JIPREG). The prepregs can be stored without any changes in its properties upto 20 days.

2.3. Production of the FML There are many methods available to produce a FML: hand layup, stamp forming, autoclave and Resin Transfer Moulding (RTM). There are several types of RTMs, the popular ones are Structural Resin Injection Moulding (SRIM), Vacuum Assisted Resin Injection (VARI), Vacuum Assisted Resin Transfer Moulding (VARTM) and Resin Film Infusion (RFI).

2.3.1. Hand layup In case of the hand layup technique as shown in Fig.5 the reinforcement will be prepared just before it is to be used. The reinforcement material mostly in the form of fabric, fibres or powders will be mixed with a suitable resin to enhance its bonding with the skin. As soon as the reinforcements is mixed with the resin. It will be placed between the skins. Then light to moderate pressure is applied to the skins in the form of pressing by hand or a roller. The applied pressure compresses the prepreg and enables proper bonding between the skin and the reinforcements. Enough time is allowed to enable proper bonding. The hand layup technique is used for creating large laminates which are to be used for low cost and light load applications [42-43].

Figure 5 Hand layup technique

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2.3.2. Stamp forming Stamp forming is similar to the above method except that heavy force is applied to bond the laminate and prepreg as shown in Fig.6. In this method layers of laminate and the prepreg are arranged as desired over the cavity of a blank. The cavity resembles the final desired shape of the finished laminate. It is then pressed using a round tipped tool into the blank. The applied pressure forces the prepreg to get bonded to the laminate. The layers are held in a die, blank holder and punch setup. The shape of the produced part is determined by the design of the die and punch [44]. Pressure is applied from both sides of the mould. Hence this method is also called as press forming or stamp forming depending upon the direction of the applied force [25][45].

2.3.2. Stamp forming Stamp forming is similar to the above method except that heavy force is applied to bond the laminate and prepreg as shown in Fig.6. In this method layers of laminate and the prepreg are arranged as desired over the cavity of a blank. The cavity resembles the final desired shape of the finished laminate. It is then pressed using a round tipped tool into the blank. The applied pressure forces the prepreg to get bonded to the laminate. The layers are held in a die, blank holder and punch setup. The shape of the produced part is determined by the design of the die and punch[44]. Pressure is applied from both sides of the mould. Hence this method is also called as press forming or stamp forming depending upon the direction of the applied force [25][45].

Figure 6 Stamp forming technique [46]

2.3.3. Autoclave Autoclave method as shown in Fig.7 is a traditional method used for production of FML. The stored prepregs are taken out of the deep freezer and its temperature is allowed to get to room temperature. Then it is separated from the polythene sheets and stacked with the pretreated metal laminates. Since the layers are stacked by hands, the autoclave method is otherwise names as hand forming technique. The number of layers depends upon the end requirements as desired such as 2/1 laminate, 3/2 laminate or 4/3 laminates. It is then placed in autoclave chamber and vacuumed. Pressure is then applied along with heat to enhance the bonding between the laminate and the prepreg [41]. This method is simple in design and do not require a power feed during manufacturing and parts can be fabricated quickly. However it has some drawbacks such as: not suitable for preparing larger parts, high operating costs, prior knowledge in curing and properties of the resin, fibre and metal laminate.

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Figure 7 Autoclave method [47]

2.3.4. Structural Resin Injection Moulding (SRIM) In this method resin is prepared separately while the fibre reinforcements and the skin materials are placed inside a mould. Most cases the reinforcements are arranged sandwiched between the skin materials. The resin is then injected or pumped under high pressure over the reinforcement [48]

2.3.5. Vacuum Assisted Resin Injection (VARI) VARI has the benefit of low cost production of FML and also the ability to manufacture large sized parts [49]. In the VARI, the layers of perforated reinforcements and metal skins are arranged as desired. It is then placed inside a one sided mould and covered by flexible film resembling a mould cavity. Peel plies are provided to enable easy removal of the finished laminate materials as shown in Figure 8. The process is carried out by removing the air from inside the cavity by using a vacuum pump attached at one of the longer ends of the arrangement. It is then followed by pumping of hot resin from the other end. The resin flows inside the cavity because of the pressure difference and gets infused with the reinforcement [50].After curing for some hours a FML with the desired properties will be obtained.

Figure 8 Schematic Representation of VARI [51]

2.3.6. Vacuum Assisted Resin Transfer Moulding (VARTM) VARTM technique has a similar construction of the VARI. Fig.9 shows the construction of VARTM and the important parts [52-54]In VARTM the vacuum pump creates a much greater negative pressure than the VARI. Resin is sucked into the mould cavity because of pressure difference between the cavity and the resin holder. The quality of the FML depends upon the

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Figure 9 Illustration of VARTM [56]

2.3.7. Resin Film Infusion This method has some similarity in construction as compared to autoclave method. It consists of a single mould cavity in which pellets of resin is placed over the reinforcement. Heat is supplied to the setup, which melts the resin and distribute over the reinforcements [57]. The quality of the FML depends upon the temperature supplied, the pressure inside the mould cavity and the viscosity of the resin to flow and distribute evenly into the reinforcements.

2.4. Post treatment Post treatment is referred to the curing of the FML after the resin is introduced into the reinforcements. The curing time differs, depending upon various factors mentioned below. • Pre treatment employed • Type of the resin used i.e., semisolid or liquid during the time of infusion into the reinforcements. • Whether prepreg is used or not i.e., if the preparation method uses prepregs then the resin had been already infused into the reinforcement. Hence the post treatment employs higher heat required to enable resign flow into the pre treated skin material. • Type of the reinforcements and the skin materials used.

3. INVESTIGATION OF FML CHARACTERIZATION FMLs are generally subjected to the following types of testing: impact test, tensile test, flexural test, fire retardant characteristic. While conducting tests on FML, care should be taken on the scaling effect. Literature review revealed that scaled model and full sized model gave drastically different results. This was because of variation in parameters such as thickness of fibre laminate, material removed from the metal layer, mass and overall thickness between scaled and full sized model [58- 61].

3.1. Impact strength The study of force-time on the laminate revealed three notable occurrences. First is the materials resistance against impact damage. Second is the fluctuation in force which indicates decrease in local bending stiffness. Third is the maximum bearing load before the material cracked to the impactor. The major cause of failure is delamination. It was observed that the

http://iaeme.com/Home/journal/IJMET 568 [email protected] Review on Manufacturing of Fibre Metal Laminates and its Characterization Techniques load and the ply direction influenced the failure of the laminates. Lower load to cross ply and 90o orientation of fibre gave better resistance to damage [62].

3.2. Tensile Strength Tensile test conducted on different FMLs revealed that failure in FML occurred because of many factors including the metal used as laminate, type of fibre, sequence of laminate prepereg stacking, geometry of impact, percentage of post stretching, etc. Material properties like Young’s modulus, yield stress, strain hardening coefficient, anisotropic parameter and the true stress v/s true strain curve are the basic input parameter required for the pre-processing of the deep drawing process and hence need to be procured from the tensile test [63]. Analysis of pre stress on GLARE, ARALL and CARALL revealed that GLARE could with stand greater stress. The mode of failure was due to fibre and also the laminate material. Improving the stiffness and strength of laminate material proved to have a drawback. The metal exhibited brittleness and the failure originated low energy absorption and low damage resistance characteristics. Fig.10 shows the relation between various reinforcements on failure on comparing with the base metal. It can be found that GLARE exhibited superior resistance to failure that other materials [64].

Figure 10 Force vs deflection for various core materials [65-66] Inclusion of magnesium as the composition in the laminate gives some advantages such as low density, magnetic resistance and corrosion resistance, along with reduction in crack resistance and residual strength [67]. The ratio of Metal Volume Fraction (MVF) is unique to FML is shown in equation (1). It is the ratio between the overall thicknesses of the laminate to the thickness of metal layer. MVF = Thickness of laminate (1) Thickness of metal layer It was suggested that increasing the thickness of the fibre reinforcement improves impact resistance of the laminate. Hence in every laminate a slight larger thickness of the resin and fibre reinforcement is maintained. There is no optimum thickness ratio allocution to determine and limit the MVF. However care should be taken to maintain lower density. Otherwise the reason to go for laminate material cannot be justified. Many literatures are available to correlate the MVF with density [68-71]. FML may experience stress due to unequal thermal contraction especially while using autoclave method preparation. It was found that the metal and reinforcement show different behaviour under static loading and dynamic loading respectively [70] [72-74]. Such laminate will have low energy absorption and premature failure. This can be overcome by stretching the metal layer to plastic state while the reinforcement remains in elastic region [75].

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Tensile test was conducted using UTM on a rectangular specimen in contrast with the traditional method of using ASTM standards. The test revealed that the strain to failure on FML was same in comparison with composite material. However the same was greater than in comparison of FML with the base metal. This is justified by the bonding strength which added to the tensile strength of FML [76]. Figure 11 and Figure 12 reveals the above explained result.

Figure 11 Stress strain curve (0-90 FML) [76]

Figure 12 Stress strain curve (45 FML) [76]

3.3. Formability Cup test and hemispherical dome test are the two methods to determine the forming characteristics of the FML [54]. The test conducted on FML with different orientations revealed that the laminate with 0-90 orientation of reinforcements exhibited greater strength compared to that with ±45 orientations. This intimates that load distribution evenly along the rolling direction of the metal layer and the reinforcements. The most widely used test of sheet metal forming is the uni-axial tension test [77]. Plastic strain ratio (r) is used to determine the uni-axial tension as shown in equation (1). Plastic strain ratio is the resistance of steel sheet to thinning during forming operation. This is the ratio of the true width strain to the true thickness strain of the plastically strained sheet metal [78].

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r= εw / εt (1) Where,

εw - ln (w/w0)

εt - ln (t/t0) = ln (L0w0/Lw) w - Change in width

w0 - Original width t - Change in thickness

t0 - Original thickness Form strength of both FML configurations is approximately around 160 MPa. It can be noticed that the tensile strength of the [Al, 0-90] FML is approximately 150 MPa while that for the [Al, ±45] FML is approximately 130 MPa. Generally, the form strength of a material could be higher than its tensile strength [79-81]. This happens because during a tensile test, the whole specimen is subjected to a constant stress whereas during forming test, a relatively small region of the specimen experiences maximum stress. This difference in loading volume reduces the likelihood of failure in the sample as show in the Figure 13.

Figure 13 Stress vs strain on Al-FML [76] The Scanning Electron Microscopic (SEM) image of the specimen subjected to Erichsen cupping test is shown in Figure 14 [23].

Figure 14 SEM image of specimen subjected to Erichsen cupping test [23]

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3.4. Fire Retardancy Fire retardant characteristic is an important property for a FML.[23] conducted extensive research on the fire retardant characteristics on FML. A typical FML material should have the following characteristics while subjected to flame: • Should not be toxic to human, animals and plants, • Should not release any harmful evaporating gases, • Should not release any additional toxic, harmful or corrosive smoke gases in case of fire, • Should not negatively affect the flame retardancy.

3.4.1. Flammability The cone calorimeter investigation is very popular and standard method for ranking and comparing the flammability properties of polymeric materials. During the entire combustion process of the sample in a cone calorimeter, a constant external heat flux is maintained to sustain the combustion of the test sample i.e. the test method creates a forced flaming combustion scenario. Therefore, the test results from cone calorimeter are very important in flammability evaluation of any polymeric material [23]. UL94 testing is carried out following two standards: one is the vertical burn test (UL94 V) and the other is the horizontal burn test (UL94 HB). The LDPE/LDH nano-composites containing up to 16.2 wt% LDH did not pass any of the UL94 V specifications. All the samples started burning spontaneously after first 10 seconds flame application, which continued until the test specimen is completely burnt up to the sample holding clamp. This means that the nano-composites are not self-extinguishing [23].

3.5. Flexural Strength The flexural test is conducted analysis on flexural characteristics on FML AA8011/Polypropylene/AA1100. There are different standards to perform flexural tests. One such standard is ASTM D790 in which the specimen of 150 mm length, 30 mm width and 4 mm thick is subjected to a load at its centre[23]. The applied load and displacements were recorded and obtained using the formulas shown in equation (2) and (3) respectively. 2 σf = 3PL/2bd and (2) 2 εf =6Dd/L (3) Where, ‘L’ is the span length, ‘b’ is the width of the sandwich sheet, ‘d’ depth of the sandwich sheet Specifically, mechanical properties and failure modes of AA8011/Polypropylene/AA1100 sandwich sheets are characterized. Flexural strengths of three specimens cut from the sandwich sheets are summarized and the optimum values of load (P), maximum deflection (D), flexural stiffness (Sf), flexural stress (y) and flexural modulus (E) of sandwich sheets were found to be 140 kN, 28 mm, 8.23 MPa, 81.56 MPa and 323.81 MPa respectively [82- 87]. Figure 15 shows load-mid span deflection under three-point bending of the sandwich sheet by flexural test. It is revealed that the deflection of sandwich specimen increased almost linearly with load upto final failure. Hence it is determined that specimen could withstand flexural load. Much of the force is absorbed by the thick layer of epoxy resin and the

http://iaeme.com/Home/journal/IJMET 572 [email protected] Review on Manufacturing of Fibre Metal Laminates and its Characterization Techniques reinforcement than the skin material. The flexural tests reveal that, the sandwich sheet can be applied as outer shell of automobiles and aeroplanes [88-90].

Figure 15 Load-mid span deflection of the sandwich sheet in flexural test [66]

4. CONCLUSIONS • FML has more advantages such as low density, superior strength, and hardness over the composite material and base metal. Hence FML has found applications in many fields including, structures of aeronautical, automobile and marine. • There are many methods of preparing FML which can be selected based on the parameters such as cost and finish required from the process. • Specific properties can be induced on the FML by suitably selecting the reinforcements, MVF and fibre orientation. • Pretreatment on the metal and post treatment of FML can enhance the properties of the FML.

REFERENCES:

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[79] P.Sathyaseelan, K.Logesh, M.Venkatasudhahar, N.Dilip Raja, (2015) Experimental and Finite Element Analysis of Fibre Metal Laminates (FML’S) Subjected to Tensile, Flexural and Impact Loadings with Different Stacking Sequence , International Journal of Mechanical & Mechatronics Engineering IJMME-IJENS Vol:15 No:03. [80] K.Logesh, V.K.Bupesh Raja, B.Dinesh, M.Rajesh Kumar, S.Bharath, Experimental investigation and finite element simulation of tensile behaviour of AA5052/GF/AA5052 Fibre Metal Laminate (FML), International Journal of Mechanical Engineering and Technology, Volume 8, Issue 8, August 2017, pp. 324-333. [81] Mathew Alphonse, V.K.Bupesh Raja, K.Logesh, N.MuruguNachippan, IOP Conf. Series: Materials Science and Engineering 197 (2017) 012058 doi:10.1088/1757- 899X/197/1/012058. [82] N. Montinaro, D. Cerniglia, G. Pitarresi, Detection and characterisation of disbonds on Fibre Metal Laminate hybrid composites by flying laser spot thermography, Composites Part B 108 (2017) 164-173. [83] Logesh K, Bupesh Raja V.K, Velu R, Sreenivasa Theja B, (2015) Fire Retardant, Characteristics and evaluation of LDH Reinforced Composite Materials (FML’s) – An Overview , International Journal of Applied Engineering Research, ISSN 0973-4562, 10 (84), pp: 209-214. [84] Logesh K, Bupesh Raja V.K, (2015) Formability Analysis for Enhancing Forming Parameters in AA8011/PP/AA1100 Sandwich Materials , International Journal of Advanced Manufacturing Technology, DOI: 10.1007/s00170-015-7832-5, pp: 1-8. [85] K. Logesh and V.K.Bupesh Raja, (2017) Experimental Studies on Impact Strength of AA5052 -MWCNT/LDH Reinforced Hybrid Fibre Metal Laminate , International Journal of Mechanical Engineering and Technology, 8(7), pp. 784–794. [86] ASTM standard, D2674-72, (2004) Standard Methods of Analysis of Sulfochromate Etch Solution Used in Surface Preparation of Aluminium , Book of Standards, 15 (6). [87] ASTM standard, D2651-01, (2004) Standard Guide for Preparation of Metal Surfaces for Adhesive Bonding, Book of Standards , 15 (6). [88] Kahlili S.M.R, Mittal R.K, Gharibi Kalibar S, (2005) A Study of the Mechanical Properties of Steel/ Aluminium/GRP Laminates , Materials Science and Engineering, 412 (A), pp: 137 – 140. [89] K.Logesh, V.K.Bupesh Raja, Rubeshkhannaa Sivakumar, R. Krithick Vignesh and Nishant Kumar Nath, (2017) Experimental investigation on formability analysis, mechanical and corrosion behaviour of AA1100 sheet metal International Journal of Mechanical Engineering and Technology, pp. 900–909. [90] K. Logesh and V.K.Bupesh Raja, Experimental Studies on Impact Strength of AA5052 - MWCNT/LDH Reinforced Hybrid Fibre Metal Laminate, International Journal of Mechanical Engineering and Technology, 8(7), 2017, pp. 784– 794. [91] K.Logesh, V.K.Bupesh Raja, B.Dinesh, M.Rajesh Kumar and S.Bharath, Experimental Investigation and Finite Element simulation of Tensile Behaviour of AA5052/GF/AA5052 Fibre Metal Laminate (FML), International Journal of Mechanical Engineering and Technology (IJMET) Volume 8, Issue 8, August 2017, pp.324-333 [92] M.Venkatasudhahar, R.Velu, K.Logesh and R.Ganesh, (2017) Effect of Surface Modification and Hybridization of Coir Fiber on Mechanical Properties of Nylon/Epoxy Hybrid Composites , International Journal of Mechanical Engineering and Technology 8(8), pp. 264–281.

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