SOME RESEARCH ON FINITE ELEMENT ANALYSIS OF COMPOSITE MATERIALS

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1 The 3 rd International Conerence on DIAGNOSIS AND PREDICTION IN MECHANICAL ENGINEERING SYSTEMS DIPRE 12 SOME RESEARCH ON FINITE ELEMENT ANALYSIS OF Valeriu DULGHERU, Viorel BOSTAN, Marin GUŢU Technical University o Moldova gutumarin@ymail.com ABSTRACT The aim o this paper is to veriy the accuracy o composite materials data input into ANSYS Parametric Design Language or numerical analysis. For this purpose some specimens o laminated composite were subjected to bending moment and deormations were measured. The same time the specimens in ANSYS APDL were analyzed and compared the experimental data in order to establish the degree o accuracy. Keywords: deormations, composites, bending, specimens, FEM analysis 1. INTRODUCTION 1.1. Properties o glass/polyester composites Rotor blades o laminated ibre glass composites with polyester resin as the matrix material are still widely used today. The glass used in blade construction is E-glass, which has good structural properties in relation to its cost [2]. The plate elements orming the spar o a GFRP blade are normally laminates consisting o several plies, with ibres in dierent orientations to resist the design loads. Within a ply (typically 0,25 0,6 mm in thickness), the ibres may all be arranged in the same direction, unidirectional or they may run in two directions at right angles in a wide variety o woven or non-woven abrics. Although the strength and stiness properties o the ibres and matrix are well deined, only some o the properties o a ply can be derived rom them using simple rules. Thus, or a ply reinorced by UD ibres, the longitudinal stiness modulus, E 1, can be derived accurately rom the rule o mixtures ormula: E1 E V Em (1 V ), [GPa] (1) where E is the ibre modulus (74 GPa or E-Glass), E m is the matrix modulus (in the range 4 GPa) and V is the ibre volume raction [3]. Transverse modulus, E 12, is determined by the The 3 r d International Conerence on ormula: 1 E E, [GPa] (2) Em (1 V ) V E The in-plane shear modulus o a ply, G 12, can be estimated rom: 1 G G, [GPa] (3) Gm (1 V ) V G where G m is the shear modulus o polyester (G m = 1.4 GPa); G is the shear modulus o E-glass (G m = 30 GPa) The Poisson coeicient can be obtained rom ormula: V mv (4) Clearly, longitudinal stiness and strength are both limited by the ibre volume raction obtainable. For hand lay-up, ibre volume contents o 30 40% are typical, but the use o vacuum bagging, in which trapped air and excess volatile compounds, such as residual solvent, are extracted, consolidates the composite and allows a volume raction o 50% or more to be achieved. 1

2 SOME RESEARCH ON FINITE ELEMENT ANALYSIS OF 2. EXPERIMENTAL ANALYSIS 2.1. Preparation o Test Pieces The pieces were obtained rom a laminated plate which in turn was manuactured by Vacuum Assisted Resin Transer Molding (VARTM) [4], Figure 1. Fig. 2 Test laminate structure Fig. 1 Vacuum Assisted Resin Transer Molding Fig. 3. Test specimen Laminate speciication employed in the specimen design is the ollowing: 4 layers o Unidirectional glass abric with 600 g/m2 [0 E-glass ibers (2400 tows) and 90 E-glass ibers (300 tows)]; in the middle one layer o Chopped Strand Mat with 810 g/m2. The process o vacuum resin transer was perormed at 0,7 atmospheres. So was obtained 2.6 mm thick laminate with 67% iber volume raction. Ater process o curing o about 10 days, rom plate were cut 250 mm x 25 mm test specimens, igure 2 and Bend Testing Two specimens were ixed by one end between table and another plate on a portion o 60 mm as shown in Figure 4. Then specimens were bent with a electronic spring balance to 1, 2, 3, 4 and 5 kg orce. At the same time or each load level were measured displacements. There is a little dierence between results obtained or each specimen. The results are presented in Table 1. Fig. 4. Specimen loading Table 1 Test results Force, N Displacement, mm Specimen 1 Specimen The 3 r d International Conerence on

3 MECHANICAL TESTING OF A HYDROGEN EMBRITTLED STEEL 3. NUMERICAL MODELING AND ANALYSIS OF THE SPECIMEN The specimen was modeled with ply input data obtained by the ormulas presented in the introduction and [1, 7] and are shown in Table 2. Numerical simulations were perormed in ANSYS Parametric Design Language [5, 6]. The specimens were modeled with 250 SHELL99 8-node layered shell elements (igure 5 and 6) [9]. The middle layer o CSM was considered as a material with linear isotropic properties. Table 2 Summary o material properties or a ply employed in the specimen design Property E-Glass Fiber/ Polyester Composite Fiber orientation UD CSM Fiber Volume Fraction 67% 50% Tensile Modulus E 11, GPa Transverse Modulus E 12, GPa 8,5 12 Shear Modulus G 12, GPa 3,87 Poisson's ratio, υ 12 0,3 0,28 Poisson's ratio, υ 21 0,06 0,28 Fig. 6. Finite element model o specimen and loads deinition Fig. 7. Sample displacement vector sum or 50 N bending Fig. 5. SHELL99 Geometry Modeled specimen was subjected to the same orces as the real test piece. Loads deinition is shown in Figure 6. Displacements and tensions that arise in tested specimen are shown in Figures 7 and 8 or 50 N load. Comparison o test results and inite element analysis results are shown in Figure 9. The 3 nd International Conerence on May 31 June 1, 2012, Galaţi, Romania Fig. 8. Sample von Misses stress or 50 N bending 3

4 SOME RESEARCH ON FINITE ELEMENT ANALYSIS OF The FEA results are presented in the table below. Table 3. FEA results Displacement, Force, N mm Fig. 9. Samples comparison o testing and numerical analysis results or displacements REFERENCES 1. Banu M., 2007, Tehnologia Materialelor Compozite, Curs, pp Available rom, Tehnologia- Materialelor-Compozite, Accesed: 18/11/ Burton T., Sharpe D., 2001, Blade materials and properties, Wind energy handbook, John Wilei&Sons, LTD, pp , West Sussex, England. 3. Gay D., et at., 2003, Composite Materials Design and Applications, CRC Press, pp Hermann Thomas M., et at., 2006, Fabrication, Testing and Analysis o Anisotropic Carbon/ Glass Hybrid Composites. Volume 1: Technical Report, Sandia National Laboratories, pp Madenci E., Guven I., 2006, The Finite Element Method and Applications in Engineering Using Ansys, Springer, pp Nakasone Y., et at., 2006, Engineering Analysis With ANSYS Sotware, Elsevier, pp Rosato Donald V. and Rosato, Dominick V., 2004, Reinorced Plastics Handbook, 3 rd edition. Elsevier Science, pp Vasiliev Valery V., Morozov E., 2001, Mechanics and Analysys o Composite Materials, Elsevier Science, pp Wetzel Kyle K., et at., 2006, The WEI6K, a 6-kW 7 m Wind Turbine, Final Technical Report, pp CONCLUSIONS Dierence between measured and simulated displacements values is about 20%. Cause such a dierence could be ply input data inaccuracy. Using the rule o mixture can be obtained correct values or material properties o layered unidirectional composite. From results o numerical analysis the ollowing acts have been observed: - or the middle layer o CSM the linear isotropic material properties do not aect the specimen FEA results. For tensile modulus E 11 equal to 1 and Poisson's ratio equal to 0,1 were obtained the same results as the values given in Table 2. What matters is the thickness o this layer. 4 The 3 r d International Conerence on

5 The 3 rd International Conerence on DIAGNOSIS AND PREDICTION IN MECHANICAL ENGINEERING SYSTEMS DIPRE 12 The 3 r d International Conerence on 5

SOME RESEARCH ON FINITE ELEMENT ANALYSIS OF COMPOSITE MATERIALS

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