 Open Access
 Total Downloads : 19
 Authors : Jitender Kumar, Dr. Rajesh Kumar
 Paper ID : IJERTCONV1IS02014
 Volume & Issue : NCEAM – 2013 (Volume 1 – Issue 02)
 Published (First Online): 30072018
 ISSN (Online) : 22780181
 Publisher Name : IJERT
 License: This work is licensed under a Creative Commons Attribution 4.0 International License
Estimation of Loss Factor of Viscoelastic Material by Using Cantilever Sandwich Plate
Estimation of Loss Factor of Viscoelastic Material by Using Cantilever Sandwich Plate
1Jitender Kumar, 2Dr. Rajesh Kumar
1Geeta Engineering College (Panipat) 2SLIET Longowal, Punjab 1jitd2007@rediffmail.com
I INTRODUCTION
A viscoelastic material is characterized by possessing both viscous and elastic behaviour. A purely elastic material is one in which all the energy stored in the sample during loading is returned when the load is removed. As a result, the stress and strain curves for elastic materials move completely in phase. For elastic materials, Hookes Law applies, where the stress is proportional to the strain. A complete opposite to an elastic material is a purely viscous material. This type of material does not return any of the energy stored during loading. All the energy is lost as pure damping once the load is removed. In this case, the stress is proportional to the rate of the strain, and the ratio of stress to strain rate is known as viscosity (Âµ). These materials have no stiffness component, only damping. For all others that do not fall into one of the above extreme classifications, we call viscoelastic materials. Some of the energy stored in a viscoelastic system is recovered upon removal of the load, and the remainder is dissipated in the form of heat. The cyclic stress at a loading frequency is outofphase with the strain by some angle8 (where 0 <8</2). The angle 8 is a measure of the materials damping level; the larger the angle the greater the damping.The loss factor is also given by the relation: rJ = tan8.
Viscoelastic materials are widely used in passive control of vibration by free layer damping and constrained layer damping. So it becomes necessary to obtain their dynamic characteristics. Oberst (1952) proposed to apply a thin layer of viscoelastic material to the surface of flexible structures for passive vibration control, called unconstrained (free layer) damping and the dissipation of energy occurs due to the alternate extension and compression of the VEM layer. Kerwin (1959) introduced the constrained viscoelastic damping, in which the viscoelastic layer is covered in turn by a high tensile stiffness constraining layer. The constraining layer induces shear strain in the viscoelastic layer, and thus greater damping is produced. These socalled sandwich structures are very effective in controlling and reducing the vibration response of flexible and light structures. After this work, Ungar and Kerwin gave a formulation for the loss factor in terms of energy, which has become the basis for the evaluation of the loss factor and the parametric design of damped composite structures. Loss factor can be determined by several different methods, which are divided in two categories: frequency domain and time domain tests. Examples of the frequency domain methods are the halfpower point and the magnificationfactor methods, and examples of the time domain methods are logarithmic decrement and hysteresis loop methods.
In the present paper the damping property of the viscoelastic material is evaluated. For this purpose first the sandwich structure having viscoelastic silicon rubber sandwiched between two aluminium metal plates is prepared. Then the loss factor of the cantilever sandwich structure is determined by using logarithmic decrement method. By using the loss factor of the cantilever sandwich specimen the loss factor of the viscoelastic core material is estimated by using ASTM E756 norms.
II THEORY

Logarithmic decrement method: The loss factor of the sandwich specimen is determined by using logarithmic decrement method. Logarithmic decrement is defined as the ratio of any two successive amplitudes on the same side of the mean line. As per the definition logarithmic decrement for two successive amplitudes x1 and x2 is given as
8 = ln x1 x2
2.1
For under damped system the equation for amplitude is given as
x = c4eEwt cos (J1 E2 wt + </2) 2.2
Here c4 and </2 are constants which are determined from the initial conditions, is the damping ratio.
Let t1 and t2 denote the times corresponding to two successive amplitudes. We can find the ratio of amplitudes x1 and x2 as
x1 = eEw(t1t2) cos (1 E2wt1 + </2) 2.3
x2 cos (1 E2wt2 + </2)
Let us assume t2= t1+td
2
Where td = d is the period of damped vibration. The term
cos (wdt1 + </2) as J1 E2 w = w
Where x1= amplitude at the starting position
Xn+1= amplitude after n cycles

ASTM E756 norms for evaluating loss factor of damping material
From experiment the loss factor of the sandwich plate
cos [wd(t1 + td) + </2]
w
cos (wdt1 + </2) cos [wd(t1 + 2rr) + </2]
d
= cos (wdt1 + </2)
2.5
d
is determined by using the logarithmic decrement
method. Then the loss factor of the viscoelastic core material from the cantilever sandwich plate is estimated by following the ASTM E756 norms. The following expression is used to estimate the loss factor of the damping material:
cos [wdt1 + 2rr) + </2]
Again considering equation 2.3 and using equation 2.5 in it, we have
/3 = ArJS
[A B 2(A B)2 2(ArJS)2]Where
A = (fSfn)2(2 + DT)(B/2)
2.9
x1 Ew(t t t )
Ewt
EW27r
x2 = e
1 1 d = e
d = e Wd
B = 1[6(1 + T)2]
x1 EW27 r
27rE
D =
x
= eJ1E2W = eJ1E2 0 1
2
8 = ln x1 = 2rrE
2.6
T = H1H
x2 1 E2
When the value of the is very small the above equation can be written as
8 = 2rrE 2.7
If the system executes n cycles, the logarithmic decrement can be written as
Where D is the density ratio, fn is the resonance frequency for mode n of base plate (Hz), fs is the resonance frequency for mode s of sandwich plate (Hz), H is the thickness of base beam, H1 is the thickness of damping material, T is the thickness ratio,
/3 is the shear loss factor of damping material, rJS is the loss factor of sandwich plate, 1 is the density of damping material, is density of base material and s is
index number: 1,2,3..(s= n)
1 x1
= n ln xn+1 2.8
III EXPERIMENTAL PROCEDURE
In the present work sandwich plate having 3 mm thickness of viscoelastic core material is used. Aluminium plates of 1mm thickness are used as the face plate and silicon rubber is used as core material. The silicon rubber is bonded to the aluminium plates with the standard epoxy resin araldite having Youngs modulus 2432 MPa and density is 1.17 g/cm3. The plate dimensions are 90 mm in length and 90 mm in width. Then these test specimens are excited with the help of electro dynamic shaker under sweep sine and free vibration mode. Agilent Function generator 3322A was used to generate the required sine function to excite the shaker. The vibrational response of the specimens was recorded using one piezoelectric accelerometer with sensitivity 10mV/g. For data acquisition National Instruments SCXI 1000 chassis with SCXI 1530 Integrated Electronic Piezoelectric acceleration measurement module was used. The experimental set up is shown in figure 3.1. Sweep sine test is used to determine the natural frequencies of these specimens and free vibration test is used to determine the loss factor. The loss factor of the bare aluminium plate and the sandwich plates are determined by logarithmic decrement method. Then theloss factor of the viscoelastic core material is evaluated from the cantilever sandwich specimens by following the ASTM E756 norms and using equation 2.9.
Name of material 
Thickness 
Density 
Aluminium (base material) 
1 mm 
2700 kg/m3 
Silicon rubber (damping material) 
3 mm, 6 mm, 9 mm 
950 kg/m3 
Table 3.1: Summary of geometrical and physical properties of base material and damping material
VI RESULT AND DISCUSSION
The vibration response of the specimen obtained under sweep sine and free vibration test are shown in figure
4.1 From free vibration test at 3rd mode the damping
ratio and loss factor of sandwich plate is obtained by logarithmic decrement method and then the loss factor of the damping material is obtained by ASTM E756 norms as shown in table 4.1
Figure 4.1 Vibration response of sandwich plate (a) response of forced vibration (b) response of free vibration
Table 4.1 Loss factor of the sandwich plate and damping material
Name of specime n 
Thicknes s of rubber 
Dampin g ratio of sandwic h plate 
Loss factor of sandwic h plate 
Loss factor of damping materialevaluat ed from sandwich plate 
Cantilev er sandwic h plate 
3 mm 
0.01926 
0.03853 
0.1790 

CONCLUSION
Evaluation of the loss factor of the viscoelastic (damping) material by cantilever sandwich plate is a suitable method. For sandwich composite beams/plates, this approximation is acceptable only at higher modes and it has been the practice to ignore the first mode results. The sandwich beam technique usually is used for soft viscoelastic materials with shear moduli less than 100 MPa.

REFERENCES

Ahmed Maher, Fawkia Ramadan and Mohamed Ferra. Modeling of vibration damping in composite structures. Composite Structures. 1999, 46: 163 170.

Altramese Lashe RobertsTompkins. Viscoelastic analysis of sandwich beams having aluminum and fiberreinforced polymer skins with a polystyrene
foam core. Thesis, Master of Science, Texas A&M University, 2009.

ASTM E. Standard test method for measuring vibration damping properties of materials. American Society for Testing and Materials, 2010,75605.

Baz A. and Chen T. Control of axisymmetric vibrations of cylindrical shells using active constrained layer Damping. ThinWalled Structures. 2000, 36: 120.

Balamurugan V. and Narayanan S. Activepassive hybrid damping in beams with enhanced smart constrained layer treatment. Engineering Structures. 2002, 24: 355363.

Beards C.F. Structural vibration: analysis and damping. John Willey and Sons, 1996.

Bilbao A., Aviles R., Agirrebeitia J. and Ajuria G. Proportional damping approximation for structures with added viscoelastic dampers. Finite Elements in Analysis and Design, 2006,volume 42: issue 6: 492 502.

Bohn C., A. Cortabarri, Artel V. H. and Kowalczyk
K. Active control of engineinduced vibrations in automotive vehicles using disturbance observer gain scheduling. Control Engineering Practice. 2004, 12: 10291039.

Chen W. and Deng X. Structural damping caused by microslip along frictional interfaces. International Journal of Mechanical Sciences. 2005, 47: 1191 1211.

Chris Warren. Modal analysis & vibrations applications of Stereophotogrammetry techniques. Thesis, Master of Science, University Of Massachusetts Lowell, 2010.

Chul H. Park and Baz A. Comparison between finite element formulations of active constrained layer damping using classical and layerwise laminate theory. Finite Elements in Analysis and Design, 2001. 37: 3556.

ChungYi Lin and LienWen Chen. Dynamic stability of spinning pretwisted sandwich beams with a constrained damping layer subjected to periodic axial loads. Composite Structures. 2005, 70: 275286.

Denys J. Mead. The measurement of the loss factors of beams and plates with constrained and unconstrained damping layers: A critical assessment. Journal of Sound and Vibration. 2007, 300: 744762.

Dongchang Sun and Liyong Tong. Effect of debonding in active constrained layer damping patches on hybrid control of smart beams. International Journal of Solids and Structures. 2003, 40: 16331651.