Mechanical Properties of Laminated Structured Nano Composites and Its Sensibility

Mechanical Properties of Laminated Structured Nano Composites and Its Sensibility

Special Issue – 2018

International Journal of Engineering Research & Technology (IJERT)

ISSN: 2278-0181

NCANA – 2018 Conference Proceedings

and Its Sensibility

Abstract

Vibha 1, Rinkey Sahu2, Omprakash Thakare3 , Prabhat Kumar Giri4

Department of Mechanical Engineering

RSR Rungta Engineering College of Engineering and Technology, Bhilai, India

In this, the tensile ,shear rmodulus and Poisson's ratio of a woven orthotropic nano composite plate was determined by vibration data. Plates used in the experiment are 16 layers S2-glass/epoxy composite produced by vacuum assisted wet lay-up. The nano composite plane were obtained by the addition of 0%,1%,2%, 5% and 10% nano clays in weight to the epoxy matrix. Finite Element model of the composite plane combined with a gradient method was applied to obtain an approximate numerical solution to experimental data in order to estimate the mechanical properties. Two different modal procedures were employed: the Laser An emometry and Hammer test. A modal analysis was made in both cases to determine structural mode shape and associated frequencies, modal and mechanical properties for different nano clay composite planes, and assessing its sensitivity to Modal Analysis. This paper emphasizes on mechanical properties of nano composite materials .

Keywords

Modal analysis, mechanical properties, nano composites, finite elements, inverse methods.

1. Introduction

The nano composite is a laminated structure where nano particles are inserted into epoxy matrix, such procedure can improve some of the mechanical properties of the laminate. Another attractive aspect of a nano composite structure is the reduction of damage due to impact loadings. Among researchers who have studied the effect of nano particles, Yasmin et al. (2003) and Isik etal. (2003) also found an increase in the elastic modulus and toughness.

A more comprehensive study on clay- epoxy nano composites was undertaken by Haqueand Shamsuzzoha (2003), which evaluated both mechanical and thermal properties. Their main conclusions were that thermo-mechanical properties mostly increase with low clay loadings (1-2% inweight), but decrease with higher clay loadings ( 5% in weight). In addition, the use of nano clays also decreases the coefficient of thermal expansion (CTE).

They also observed a degradation of properties at higher clay loadings. This phenomenon could be due to the phase-separated structures and defects in cross-linked structures. For laminated composite and layered structures such as plasma sprayed coatings the vibration technique has proven to be an appropriate method (Lauwagie et al., 2008). The dynamic response of a sys- tem depends on geometric and material properties. This principle and the development of new techniques have made it possible to determine the material properties from vibration measurements. Usually the in plane engineering constants Ex, Ey, xy and Gxy are obtained from flexural vibration measurements of a plate.

There are various methodologies reported

in the literature (Lauwagie et al., 2008; Ayorinde and Yu, 2005; Hwang and Chang, 2000), but all of them use modal analysis for experimental mode identification and employ an optimization method to approximate the actual results to theoretical or Finite Element models. In this work, the procedure proposed by Hwang is used. A commercial code, Ansys, which also offers the function of design optimization, is employed to model the woven laminate orthotropic plate.

Two modal procedures are employed, Doppler Anemometry and a modified Hammer Test. The Laser Doppler Vibrometer method is reliable, fast, and less sensitive to environmental conditions, it does not dependent on operator skills and can be easily confined to spaces with a controlled environment. In this method the testing plate must be coupled to the force sensor which is linked to the excitation shaker, with the result that this mounting adds an extra mass to system. To deal with this, additional mass inertia and rotatory inertia were included in the Finite Element model. The traditional Hammer Test was performed and results were compared.

Batista (2005) also used the method proposed by Hwang and Chang (2000), the method works quite well for isotropic and orthotropic plates. However, for angle ply laminates, due to the complexities of mode shapes some constants are not well identified.

The objective of this paper was to study how nanoparticle concentration may affect material properties. In order to isolate influences other than nanoparticle loadings, all manufacturing parameters were kept fixed, with the exception of the nano clay concentration. An additional objective was to determine the sensitivity of the inverse method

to vibration testing method.

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1. Materials And Testing Procedure

   The nano composite prepared for this work was a S2-glass/epoxy-clay. The epoxy formulation was based on two parts, part A (diglycidyl ether of bisphenol A) and part B – an aliphatic amine hardener (triethylenetetramine). The nano clay particles used in this study are organically modified montmorillonite in a platelet form, while the S2-glass fiber has a plain-weave woven fabric configuration with a density of 180 g/m2 from Texi glass. The S2- glass/epoxy-nano clay composite is a laminate plate with 16 layers and a 65% fiber volume fraction, orientation [0]16, orthotropic. The nano composite synthesis followed the methodology proposed by Avila et al (2006a) and (2006b). In order to be able to investigate the nano particles influence on vibration analysis and its mechanical properties, samples with 0%, 1%, 2%, 5% and 10% of nano clay with respect to thematrix mass were employed. All plates were rectangular and had the same dimensions: 136mmx116mmx2.4mm.

   1. Modal Analysis

      The vibration analyses were performed to determine the mode shapes, natural frequencies and the damping coefficient. The first vibration testing were performed using a Laser Doppler Vibrometer, model OFV-303.8 and controller model OFV 3001 S from Politec, a Hewlett Packard data acquisition system model 35670A, a mini-shaker, a power amplifier and force transducer from PCB. The tested plates were suspended using a fine nylon wire and excited by a random signal (white noise). A piezoelectric force transducer was used as reference for the FRFs, which was bonded to the plate and linked by the stinger to the shaker. The point force, the position in which the force transducer was fixed, were the same point for all experiments, the experimental set-up is shown in Fig. 1. The velocity of the plate surface was measured using a grid of 35 points by the laser Doppler vibrometer.

      Figure 1 Experimental set-up for Laser Doppler Vibrometer method

      The data acquisition system processed the signal response of the measurement point, generating the Mobility (velocity/force) Function Response Frequency (FRF) for each

      International Journal of Engineering Research & Technology (IJERT)

      ISSN: 2278-0181

      NCANA – 2018 Conference Proceedings

      point of the plate. A modal analysis program was used to identify the mode shape using the 35 FRFs for each plate, such program is based on polynomial interpolation and employs the Chebyshev Orthogonal Polynomials method (Arruda et al., 1996).

      A second modal technique was also employed. In this second experiment tests were performed using te same plates and measurement points. But in this case, an Impact Hammer with a built- in force transducer was used, making it possible to excite the structure measuring the applied force. The experimental set-up can be seen in Fig. 2. The hammer force is measured at each grid point and the plate acceleration response (rms) is measured by the accelerometer at a fixed point, same position for all plates. Due to the reduced size of the plates, it was used a miniature accelerometer from PCB type 352A71 with mass of 0.64 grams, which represents 100 times less weight than the plates, while the excitation hammer is PCB model 086C05.

      Figure 2 Experimental set-up for hammer method

      Using a hammer impact and one accelerometer to perform modal analysis, it can be done fixing the accelerometer and moving the impact point or fixing the impact point and moving the accelerometer. Despite the accelerometer mass being very light weight, 0.64 grams, compared with the plate mass, the best way was observed to fix the accelerometer position and to move the impact point. In fact, even been very light weight, the change in accelerometer position drifted a little the natural frequencies what degenerate the mode shape analysis. So the best way to obtain the mode shape was to fix the accelerometer position and to move the impact point (Hu and Wang, 2009). The modal analysis program employed to analyses the results was the same as for the previous case.

   2. Inverse Method

! The procedure used to identify the mechanical properties is based on the inverse method, where were combined a gradient

method and a Finite Element Model of the composite plate. The optimization is a zero- order approach method, offered as a tool of the FE commercial code, and following the Hwang procedure (Hwang and Chang, 2000; Hwang et al., 2009). The state variablesn are related to the difference between FE, fnEF, and experimental modal nth frequency fn:

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Fn n

Fn n

EF-F

100 (1)

Fn

The cost function F is defined as:

International Journal of Engineering Research & Technology (IJERT)

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On Table 1 there was summarized the modal Doppler results, the natural frequencies

i=O

i=O

F(Exy, Gxyuxy) I,n n

(2)

and the associated damping coefficients for each experimental mode in the frequency

Where mechanical properties are Tensile Modulus Exy, Shear Modulus Gxy and the Poisson's ratioxy. Besides it was used the default values for the Ansys optimization.

In both methods, Laser Doppler and Hammer, the FE routine employed shell elements to model the plates, the shell element shell181 which is an Ansys element that has four nodes and six degrees of freedom in each node and which allows multi layers to model laminate structures.

The shell181 element is based on the Mindlin-Reissner theory, which is usually referred to as first order shear deformation theory. The Finite Element model also employed the mass21 element to consider the effect of mass and rotary inertia of the force transducer bonded to the plate.

In Gagnejaetal. (2001), there are theoretical discussions and experimental results concerning length to thickness ratios of composite structures and the FE type chosen

range that appears. For the 2%, 5% and 10% nano clay composite plates, the analysis identified spurious modes that were detached. On Tab 1 those identified as spurious modes are designated by sm* on the right upper side of the mode frequency.

Analyzing the reference Resin and 1% Nano composite plate, it is possible to observe that the mode shapes did not show any unexpected behavior and the mechanical

Analyzing the reference Resin and 1% Nano composite plate, it is possible to observe that the mode shapes did not show any unexpected behavior and the mechanical

for this study. Besides, the mass of the force

transducer must be included in the FE representation in order to obtain good results due to the fact that the mass of the plates are considerably small, around 64 grams each.

3. Results 3.1

The structure was modeled by 320 shell elements in a regular quadrilateral mesh and by one concentrated mass element. A traditional mesh test was performed to confirm FEM precision in the experimental frequency range. The results showed that there was no difference between the experimental mode shapes for1%, 2%, 5% and 10% nano clay composite and those of the reference resin plate, Fig. 3; the main difference being with regards to modal frequency.

Figure 3 (continued) Mode shapes for Resin plate. On the left side the experimental mode shapes, on right the same modes at the end of the inverse approximation method.

properties were obtained by direct application of the inverse method, while for 2% nano composite plate two modes, 4 and5, presented a similar shape, Fig 4. That behavior does not make sense theoretically or experimentally and it had not been observed in the previous cases.

th

th

Mental 4th mode (578.0Hz) ,at center the experimental optimized FE mode shape.

Figure 4 Mode Shapes for 2% nano composite plate. At the left side the experimental spurious 4th mode (655.3 Hz) and on the right, the final optimized FE mode shape.

The finite element simulation showed a low frequency coupling mode between the

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plate and the force transducer, below the first mode shape natural frequency, for all plate simulations. This coupled frequency mode was similar to a rigid body mode as the transducer was modeled as a punctual element with mass and rotational inertia but without dimensions. This FE low frequency mode offered an answer to the similar modes: it was a coupling mode between the experimental apparatus and the elastic plate.

The coupling mode between the test plate and the force transducer was named 'spurious mode', but in reality it was neither spurious nor an experimental or analysis error. This mode is termed as spurious because it is merging with the natural vibration set frequencies of the plate and disturbing the analysis.

Due to the complexity of model contacts and connections, a numerical model to deal with the dynamical coupling between the plate and force transducer, elastic stinger and shaker was not implemented. So the dynamical coupling appeared somewhat similar to a low frequency rigid body mode. The nano composite mass in the matrix changed the elastic properties of the plates and the coupling frequency mode moved inside the range of the experimental plate natural frequencies as the nano clay mass and mechanical properties changed for each plate matrix composition.

Some published works, such as the work of Hwang et al. (2009), have presented methods for dealing with missing frequencies in measurement frequencies sets or those sets with natural frequencies with large errors due to measurement problems. The Hwang work deals with incomplete set of experimental data and selects the best one with minimal cost function F, where the procedure uses a genetic algorithm program. The main idea was employed in this work. The solution presented here is to find the best plate mode set, each set with similar modes, by comparing the error between the experimental mode frequencies and those frequencies at the end of the optimization process.

In other words, the optimization was not done for all frequencies in a single process. A new mode frequency was included in the previous set, the minimization was performed and elastic properties found. The latest elastic properties were used as an initial value in a new minimization process where the next mode frequency was to be included in this updated set, each minimization run is named as iteration. The latest iteration was performed using a small toleance for the cost function F, Eq. 2, for all cases F <|10-2|.

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Table 2 and Table 3 show the frequency error for each mode set in the minimization procedure for the 2% content nano clay plate. Table 2 presents the error for each natural

frequency in each iteration. In this case, the fourth mode frequency is supposed to be the

578.0 Hz, the similar mode shape with 655.3 Hz frequency being removed from the frequency set, so there are six actual modes. Table 3 presents the same error evolution considering the fifth experimental mode frequency (655.3 Hz) as actually fourth mode frequency, with mode with 578.0 Hz being discarded from these analyses.

Figure 5 On upper line the mode shapes for 5%, 10% nanoclay plate on the bottom line. In the left column the experimental spuriousmodes (336.0 Hz) for 5% nanocomposite and below (329.8 Hz) for 10% nanocomposite. In the center column the experimental best fitfor the 2nd mode 430.1 Hz for 5% and

425.5 Hz for 10% nanocomposite, both out of phase by 180°. At right the final optimized FEmode shape.

Table 3 shows highest error while Tab. 2 shows the lowest errors for the fourth mode and for the sum of errors. Thus, the fourth mode with frequency 578.0 Hz was used to determine the elastic properties shown on Tab.

7. The fifth mode shape, with frequency of

655.3 Hz, was considered a coupling mode between the experimental apparatus and the elastic plate for this 2% content nano clay plate and deemed to be a spurious mode.

As it was shown on Tab. 1 the same behavior was observed for plates with 5% and 10% of nano particle content. On Table 4 is presented the final iteration for both plates with the best frequency set. The 5% nano clay content plate modes with 336.0 Hz and

430.1 Hz have a similar mode shape, and the experimental third mode, 430 Hz, presented a better fit at the end of optimization process. For the 10% nano particle plate, the second and third modes are similar also, and the third mode, with 425.5 Hz, had, similarly, the best approximation. In Tab. 7 are the final properties for the best set for the minimization process as presented in Tab. 2, Tab. 3, and Tab. 4.

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1. Hammer excitation method

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   This method is described in Section (2.1), and

   the excitation was performed by a hammer impact on each point of the grid and the response measured at a fixed point by a mini-accelerometer. The Finite Element model employed was that of the previous case.

   The only difference was that the plate structure was modeled by 1190 shell elements plus a concentrated mass element. This regular quadrilateral mesh was used to match the mass element position, accelerometer mass, with a node on the mesh. The accelerometer position was chosen so as to provide the best signal for all excitation points.

   The modal properties in Table 5 display several differences when compared with Tab.

   1. The main difference are related to the natural frequencies, because the force transducer used on Doppler Vibrometer test had a large mass, so the experimental assembly had a large mass and low natural frequencies.

   The damping coefficient changed with the frequencies and resin matrix contents in both experiments. The damping factor is sensitive to frequency for the great majority of materials. As the excitation force and technique to implement it is different in each experiment and the frequencies are quite dissimilar in each mode, it is difficult to compare the damping results.

   However, for the hammer method, the damping coefficient has the same numerical magnitudeorder for each mode independent of the material used in this experimental procedure. For theDoppler Vibrometer method the damping coefficient presents dispersion without a trend.

   Table 6 presents the final individual error n for each mode n at the final minimization process that approximates the FE model mode frequencies to experimental natural frequencies by chang- ing the mechanical properties, such as planar Elastic Modulus Exy [GPa], shear Modulus Gxy [GPa] and Poisson coefficient xy.

   Table 6 Frequency mode error n at the end of the best set minimization process.

   Plat !

   Res	0,43 1,20	1,26	1,14	1,03	0,35	5,70
   Nano	0,02 0,48	0,13	0,09	0,10	0,53	0,55
   Nano	0,39 0,11	0,43	0,72	0,02		0,87
   Nano	0,12 1,22	1,26	1,27	0,73		5,24
   Nano	0,07 0,76	0,55	0,16	0,42		1,08

2. Mechanical properties

On Tab. 7 are the mechanical properties for the Doppler Vibrometer Method(1), and for Hammer Method, method(2). In Tab. 7, the Shear Modulus shows good agreement between the two methods. There is an increase in the Shear Modulus with nano clay mass up to 5% content and a de- creasing tendency for the highest content. With the exception of the 2% nano composite content that, in both experiments, showed a different behavior, the difference between the results for the two methods is less than 6.5% for the Shear Modulus.

On Tab. 7 the Elastic Modulus showed a noticeable difference when comparing both methods. The Elastic Modulus in the Doppler Method(1) presented a continuous and remarkable improvement with the nano clay content, while in the Hammer Method(2) there is a 4.3% improvement from resin to 1% nano clay and almost the same value was maintained for the other specimens. The 2% nano composite plate displayed a slight decrease for the Hammer method. These unexpected results for the 2% nano composite in the Elastic Modulus and Shear Modulus for both methods may be due to problems in the specimen preparation.

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Figure 6 Mode Shapes for 1% nano composite plate, hammer method. At the left column the experimental mode shapes at right the FE mode at the end of optimization process

For both methods the maximum Elastic Modulus value occurs for the 5% nano composite plate, and for this specimen, the difference between the methods also attains its maximum. For the two plates, the Resin and 1% Nano clay plates, where the Doppler method does not display the 'spurious modes', the difference between the methods is constant, being around 17%. An ex-planation for this difference is that the transducer prevents the plate flexure on the attachment region in Doppler Vibrometer method. The plate was modeled to consider te mass and transducer inertia in a single point but not to consider the improvement in the plate stiffness on the attachment region.

But the biggest difference between the two methods refers to the Poisson Coefficient. This property has a very low value when compared with the Shear or Elastic Modulus, and this difference presents some numerical problems when the Poisson's Ratio is evaluated. From Tab. 7 it is obvious that the data from the Doppler Method is very different from usual values. The results from Hammer Method are closer to expected values.

The Poisson's Ratio is very sensitive to aspect ratio between the width and length of the plate, and this is related to the coupled deformation in two orthogonal directions (Lauwagie et al.,2003). This means that coupled modes presenting bending in both orthogonal directions, that is torsional-bending modes, are the best mode shapes to identify the Poisson Coefficient. The three last mode shapes on Fig. 6 are the best to identify the Poisson's Ratio when they are well defined (Lauwagie et al., 2010). The Poisson Coefficient is related to well-identified experimental coupled mode shapes and good consistency between them.

The Figure 6 presents the six mode shapes for 1% nano clay plate, for highest content plateonly the first five mode shapes were identified, Tab. 5. In Fig. 3, for the Doppler Method, all mode shapes seem to be deformed by the presence of sensor mass and do not have a well-defined coupled bending mode. These poorly defined torsional-bending modes may explain the poor results for Poisson's ratio obtained by this procedure.

And the plate stiffness, on the force transducer attachment region not considered in FE model, is again an explanation for these results.

There are also a relation between the cost function low value (total frequency mode error 2,on Tab. 6) and the best results for the Poisson's ratio for the Hammer method (2), Tab. 7. Of course a low value for 2 does not mean that the Poisson's coefficient is correct but for high values of cost function F the Poisson's ratio is untrusted, and this was observed for all cases presented in this work.

4. CONCLUSIONS

The results summarized on Tab. 7 suggest that the behavior of the shear modulus is probably linked to the improvement in shock resistance with the nano clay content matrix plate. This tendency was previously associated with the increase in the damping coefficient (Avila et al., 2006a), but in this work the high damping coefficient was linked to 'spurious modes'.

The Hammer Method is the more reliable, the errors between the experimental frequencies and those obtained from the Finite Element model are the smallest. Results obtained by this technique showed a limited growth in the Elasticity Modulus value with the improvement of nano particles mass in the matrix of the composite. As the Elasticity Modulus is more dependent on fiber properties than the properties of the matrix, those results are considered coherent with the theory.

The laser vibrometer measurements showed a more significant increase in the Elasticity Modulus, but the presence of 'spurious modes' in the range of natural frequencies of the plate it showed that the Finite Element model does not accurately describe the phenomenon. As a consequence, this method presented the greatest errors at the end of the error minimization process.

It was also observed that, using this methodology, the pure resin and 1% nano content plates did not display spurious modes inside experimental frequency range, but they did show a 17% difference in the Elasticity Modulus value when compared with those obtained by means of the Hammer procedure. The Laser Doppler Vibrometer technique has several desirable features and, to make the model more realistic, probably the plate stiffness on the force transducer attachment region can be considered in FE model. There is also the problem of the excessive mode distortion resulting in unreliable values for Poisson's ratio.

The Shear Modulus was less sensitive to the problems observed for Elastic Modulus and Poison's ratio experimental values. The Shear Modulus presented close values for both methods, with the dispersion of values within the expected. The Elasticity modulus depends

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on, at least, twoflexural modes of vibration, on longitudinal and transverse axes, the Poisson's ratio depends on the tree well defined torsion-bending modes, and the Shear Modulus property is linked to the first mode shape, a torsion mode (Ayorinde and Yu, 2005; Lauwagie et al., 2010), that is well defined and of easy measurement and identification. It also seems to be less sensitive to transducer at- tachment problems. The added stiffness by the transducer is a plausible explanation for the observed difference, between the two methods, for Young's modulus and Poisson's ratio, but there was not a remarkable influence on the shearing module.

This robustness of the Shear Modulus measurements may be an important aspect for choosingmechanical properties for monitoring production or, in some applications, the structural health of components. Although the great majority of the test specimens for elastic properties determination are square or rectangular plates, there is no direct relation between properties and mode shapes. Mode shapes change according to width to length aspect ratios, fiber or principal axis orientation (Ayorinde and Yu, 2005; Lauwagie et al., 2008), experimental set-up and so on. So a complex structure must be carefully analyzed to take advantage of the best Mode Shapes for the desirable elastic properties.

The inverse method using a FE model proved to be a powerful, fast and very flexible method of analysis. In both measurement methods, there are problems with the mass of the transducers and, in both cases, mass and rotational inertia had to be considered in FE model. The cost function F, seems to be an indicator to assess the quality of the numerical approximation of the Poisson's coefficient.

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