Keywords: ILSS, Flexural Strength, Hybrid Polymer Composite, Curing, Epoxy Resin 5052, Vacuum Bagging.

Transcription

1 American International Journal Reearch in Science, Technology, Engineering & Mathematic Available online at ISSN (Print): , ISSN (Online): , ISSN (CD-ROM): AIJRSTEM i a refereed, indexed, peer-reviewed, multidiciplinary and open acce journal publihed by International Aociation Scientific Innovation and Reearch (IASIR), USA (An Aociation Unifying the Science, Engineering, and Applied Reearch) An Invetigation on Hybrid Polymer Baed Compoite (E Gla fibre Carbon fibre Graphite Particulate with Epoxy rein 5052) for Flexural and Inter Laminar Shear Stre for Different Thickne Dr. M. Nayeem Ahmed 1, Mr. Mohammed Salman Mutafa 2 Preor and Head 1, Department Mechanical Engineering, KNSIT, Bengaluru, INDIA. Aitant Preor 2, Department Mechanical Engineering, KNSIT, Bengaluru, INDIA. Abtract: Hybrid compoite are conidered material great potential for engineering. One advantage hybrid polymer compoite material for the deigner i that the propertie a compoite can be controlled to a coniderable extent. The preent experimental tudy aim at learning the flexural behavior and ILSS hybrid polymer baed reinforced compoite (E Gla fiber Carbon fiber Graphite Particulate with Epoxy rein 5052)by varying the the compoite. Vacuum bagging technique wa adopted for the ation hybrid compoite. Flexural and ILSS tet i carried out a per ASTM tandard. Keyword: ILSS, Flexural, Hybrid Polymer Compoite, Curing, Epoxy Rein 5052, Vacuum Bagging. I. Introduction Hybrid compoite are manufactured by combining two or more fiber in a ingle matrix. Hybridization in order to ue to tailor the material to exact need under deign[1]. Epoxy rein i ued in thi hybrid compoite becaue it provide a unique balance chemical and mechanical propertie combined with extreme proceing veratility. In all cae, thermoet rein may be tailored to ome degree to atify particular requirement [2]. Epoxie are one type thermoetting polymer that are more expenive and have better mechanical propertie and reitant to moiture than the polyeter and vinyl rein [3]. At preent epoxy rein are widely ued in variou engineering application, uch a electrical indutrie, commercial and military aircraft indutrie. In order to improve their proceing and product performance and to reduce cot, variou filler are introduced into the rein during proceing [4]. Hybrid laminated compoite are prepared by tacking heet Gla/carbon fiber to required orientation to form angle ply laminate. An individual tructural gla fibre i both tiff in tenile and compreion [5]. They found from the detailed hear tre contour it wa poible to dicover the point maximum tre in a region within one away from the upporting roller for all three laminate. Experiment carried out on inter laminar hear behavior typical polymer matrix compoite under high train rate hear loading by N.K. Naik etal[6]. It i oberved that the inter-laminar hear trength increae with increaing hear train rate within the range hear train rate conidered. The claical laminate theory and the higher-order hear deformation theory, are ued to predict the inter-laminar hear tree in the cro-ply laminate by C.Y. Lee e tal[7]. They found that the approach uing the higher-order hear deformation theory ha improved accuracy for the analyi thick ymmetric laminate over the approach uing the claical laminate theory. II. Experimental Procedure Material Carbon fiber (37%) E gla fiber (30%) Graphite (3%) Epoxy rein LY 5052(30%) were ued to ate hybrid polymer compoite laminate. Preparation hybrid polymer compoite The fibre (reinforcement material) and matrix material (Rein and Hardener) contain moiture aborbed from atmophere. Therefore the fibre, rein & hardener hould be heated for approximately 60 minute at the temperature 60 0 C in an oven, o that the moiture aborbed can be removed. Preparation Fibre Now, the volume fraction fibre and rein i calculated baed on matrix to reinforcement ratio and then calculate the weight baed on denity. After thi, the ratio reinforcement (In cae hybrid compoite) i evaluated and the number required for each fibre to obtain the required, with matrix material i calculated. AIJRSTEM ; 2015, AIJRSTEM All Right Reerved Page 284

2 Ahmed et al., American International Journal Reearch in Science, Technology, Engineering & Mathematic, 10(3), March-May, 2015, Preparation Reinforcement Baed on the precribed rein hardener ratio, weight rein and hardener required obtaining the deired volume fraction matrix and reinforcement i calculated. The rein and hardener i taken in a cleaned container and i tirred for about 5 minute, o that the rein i mixed completely with the hardener. Now the matrix (Rein + Hardener) i ready for ation. In cae the hybrid compoite, mix the reinforcement with the rein (in thi tudy, i taken). The determination fibre volume ratio can be derived from the fibre/rein weight ratio. The approach i a follow: Data Carbon fibre: 204gm Gla fibre: 202gm Specimen calculation for the preparation Lamina calculation Compoite Prepared Table1 - calculation for pecimen preparation Carbon fibre, E-gla fibre, Graphite with Epoxy rein. compoition Caron fibre + E - gla fibre + + Epoxy Required Thickne lamina carbon fibre gla fibre weight No No Of each Of each matrix = 30% weight weight = 3% weight weight the laminate Thickne calculation compoition Table 2: Thickne calculation for pecimen preparation carbon fibre, E-gla fibre and with epoxy rein Compoitio n Caron fibre + E - gla fibre + + Epoxy Required Thickne lamina Thickne carbon fibre No Thickne each Thickne gla fibre No Thickne each Thickne matrix = 30% Thickne = 3% The compoite are manufactured uing Vacuum Bag Moulding proce. The et up Vacuum bag Moulding and compoite i hown below. the laminat e a) Vacuum Bag Moulding Pot Fabrication Procedure: After the ation laminate, it ha to be ubjected to pot curing, o lamina ha to be kept under two preure plate and ubjected to curing in a programmable oven, the pot curing cycle for the polymer compoite i a dicued here. AIJRSTEM ; 2015, AIJRSTEM All Right Reerved Page 285

3 Ahmed et al., American International Journal Reearch in Science, Technology, Engineering & Mathematic, 10(3), March-May, 2015, Pot Curing: In general, uncured epoxy rein have only poor mechanical, chemical and heat reitance propertie. However, good propertie are obtained by mixing the linear epoxy rein with uitable curative to form three-dimenional cro-linked thermo et tructure. Thi proce i commonly referred to a curing. Curing epoxy rein i an exothermic reaction and in ome cae produce ufficient heat to caue thermal degradation if not controlled. b) Epoxy curing furnace (for pot curing compoite laminate). Pot Curing Cycle for Epoxy Rein The FR Compoite laminate i kept in an oven at room temperature and program the oven to ramp up and dwell for pot curing lamina according to the chedule a follow: 1. Ramp up the temperature to 50 0 C from room temperature in 15 minute 2. Now maintain the contant temperature 50 0 C till next 30 minute 3. Then again raie the temperature form 50 0 C to 70 0 C in next 15 minute 4. Now maintain the contant temperature 70 0 C till next 60 minute 5. Then ramp up the temperature from 70 0 C till 85 0 C in next 15 minute 6. Now again maintain the contant temperature 85 0 C till next 120 minute 7. Now witch f the heater and keep the laminate to cool down to room temperature in the oven itelf. III. Flexural Tet Thi wa performed according to ASTM D 790 tet method. The lot ued for teting conited five ample for different contitution. The tet wa conducted on three ample 2mm, 3mm and 4mm each. The data Obtained from the mechanical teting wa ued to calculate the elatic propertie and bending trength the laminate. Peak load & bending trength were determined. c) 3 point bending tet compoite, Specimen loaded in machine. IV. Shear Tet Inter laminar hear failure i mot readily een in the three-point bending hort beam, a method commonly ued to meaure what i uually referred to a the inter laminar hear trength, or ILSS, although thi i ten regarded a unatifactory becaue the tate tre i not pure hear. In the diagram in Figure (d), if the level horizontal hear tre at the mid plane point M reache the inter laminar hear trength, τ IL, the compoite before the tenile tre level at T reache the compoite trength, σ c, then the beam will fail a hown. If the beam i longer than a certain critical length, however, it will fail in a normal bending mode by a tenile failure initiating at the mid-point the outer face. d) Schematic illutration inter laminar hear failure in a unidirectional laminate. Specimen preparation Inter Laminar Shear Stre (ILSS) Tet: According to ASTM 397 for ILSS tet, the pecimen preparation and dimenion are a follow: AIJRSTEM ; 2015, AIJRSTEM All Right Reerved Page 286

4 Ahmed et al., American International Journal Reearch in Science, Technology, Engineering & Mathematic, 10(3), March-May, 2015, f) Specimen dimenion for ILSS tet h) Specimen mounted for ILSS tet Tet Procedure: The and width the tet pecimen are meaured before conditioning. The pecimen i placed on a horizontal hear tet fixture o that the fiber are parallel to the loading noe. The loading noe i then ued to flex the pecimen at a peed 0.05 inche per minute until breakage. The force i then recorded. Calculation are performed to determine hear trength. V. Obervation Table FLEXURAL TEST Flexural tet data for Carbon fiber (37%) E gla fiber (30%) Graphite (3%) Epoxy rein LY 5052(30%) hybrid polymer compoite laminate by varying laminate. Table 3 Flexural tet data Hybrid Polymer Compoite laminate. Specimen no. Bending Average Bending Thickne Maximum load Average ` INTER LAMINAR SHEAR TEST ILSS tet data for Carbon fiber (37%) E gla fiber (30%) Graphite (3%) Epoxy rein LY 5052(30%) hybrid polymer compoite laminate by varying laminate. Table 4 - ILSS tet data Hybrid Polymer Compoite laminate Graph: Specimen no. Thickne Maximum Shear load Average Shear Average Shear Carbon + E gla + Graphite Particulate + Epoxy Rein mm 3 mm 4 mm Graph 1 : Comparion Flexural trength for different 2mm,3mm and 4mm. AIJRSTEM ; 2015, AIJRSTEM All Right Reerved Page 287

5 Ahmed et al., American International Journal Reearch in Science, Technology, Engineering & Mathematic, 10(3), March-May, 2015, Carbon fibre + E gla fiber + Graphite Particulate + Epoxy Rein mm 3 mm 4 mm Graph 2: Comparion Interlaminar Shear for different 2mm, 3mm and 4mm. VI. Reult and Dicuion Graph 1: From the Graph 1 it i een that hybrid polymer compoite deliver the high flexural trength, thi i becaue carbon & E-gla fiber with make the trong inter laminar bond, which reit the bending load. It i alo tudied and een that the bending trength the compoite laminate depend on it, a the the compoite increae, it flexural trength decreae it i becaue the ratio deformation outer face to the inner face i high in thicker ection which caue the tenion in lower part and reult in failure. But for maller ection it flexe and tolerate the load acting on it, ince the ratio deformation outer face to inner face i le it can withtand the higher load, thu improve the flexural trength. But it can be een that the 3 mm thick laminate how leer trength than the 4 mm one, thi i becaue the tarvation rein in 3 mm thick laminate. Graph 2: From the Graph 2, it i een that the hybrid Polymer Compoite exhibit high hear trength a the exitence epoxy 5052 which make the trong inter laminar bond in the compoite, in addition act a the filler and fill the pace between warp and weft reulting in trong inter laminar bond and hence increaing the inter laminar hear trength. It i oberved that ILS trength increae with the increae in the compoite. VII. Reference [1]. G. Kreti, a review the Tenile, Compreive, Flexural and hear propertie hybrid fibre reinforced platic, Compoite, Vol 18:1987. [2]. J. Harding and L.M Welh, A tenile teting technique for fibre-reinforced compoite at impact rate train, JMater Sci 18:1983. [3]. Chawla, K. Kumar, 1999 Mechanical Behavior Material, Prentice Hall, Inc. [4]. Calliter, W. D. and Rethwlch, D. G., 2007 Material Science and Engineering an introduction, 7th Edition, John Wiley and Son, Inc. [5]. J.Cho, Mechanical enhancement carbon fibre/epoxy compoite by nano platelet reinforcement, S. Direct 2007: [6]. N.K. Naik*, Addi Amelah, Venkatewara Rao Kavala, Veerraju Interlaminar hear propertie polymer matrix compoite: Strain rate effect Structure Panel, Aeronautic Reearch and Development Board, Minitry Defene, Government India, Grant No. DARO/08/ /M/I. [7]. C.Y.Lee & C.C.Huang Evaluation interlaminar hear tre by train meaurement on laminate urface, Department Mechanical Engineering, Da-Yeh Univerity, Da-Tuen, Chang-Hwa, Taiwan 515, and R.O.C. AIJRSTEM ; 2015, AIJRSTEM All Right Reerved Page 288