Application of the Laplace transformation for the analysis of viscoelastic composite laminates based on equivalent single-layer theories

International Journal of Aeronautical and Space Sciences.
2012.
Dec,
13(4):
458-467

This is an Open Access article distributed under the terms of the Creative Commons Attribution Non-Commercial License (http://creativecommons.org/licenses/bync/ 3.0/) which permits unrestricted non-commercial use, distribution, and reproduction in any medium, provided the original work is properly cited.

- Received : October 30, 2012
- Accepted : November 26, 2012
- Published : December 30, 2012

Download

PDF

e-PUB

PubReader

PPT

Export by style

Article

Metrics

Cited by

TagCloud

In this study, the linear viscoelastic response of a rectangular laminated plate is investigated. The viscoelastic properties, expressed by two basic spring-dashpot models, that is Kelvin and Maxwell models, is assumed in the range to investigate the influence of viscoelastic coefficients to mechanical behavior. In the present study, viscoelastic responses are performed for two popular equivalent single-layered theories, such as the first-order shear deformation theory (FSDT) and third-order shear deformation theory (TSDT). Compliance and relaxation modulus of time-dependent viscoelastic behavior are approximately determined by Prony series. The constitutive equation for linear viscoelastic material as the Boltzmann superposition integral equation is simplified by the convolution theorem of Laplace transformation to avoid direct time integration as well as to improve both accuracy and computational efficiency. The viscoelastic responses of composite laminates in the real time domain are obtained by applying the inverse Laplace transformation. The numerical results of viscoelastic phenomena such as creep, cyclic creep and recovery creep are presented.
where
t
is time, τ is time variable of integration, and σ
_{ij}(t)
and ε
_{kl}(t)
are the time-dependent stress and strain, respectively.
J_{ijkl}(t)
is the compliance and
Q_{ijkl}(t)
is the relaxation modulus which can be approximately determined by Prony series:
where the relaxation modulus
E_{ijkl,0}
,
E_{ijkl,p}
and the coefficient
a_{p}
can be determined from experimental relaxation curves.
In the present study, the viscoelastic material is modeled by following both Maxwell and Kelvin models. The relaxation modulus for the Maxwell model (Eq. 3) and the compliance modulus for the Kelvin model (Eq. 4) are expressed as time-
Geometry and coordinates of rectangular laminated plates.
dependent simpler forms:
By taking the Laplace transform with respect to time, the Boltzmann superposition integral equation in the Laplace domain can be derived as:
where ( )* are the parameters in the Laplace domain.
It is well recognized that the form of the Boltzmann superposition integral equation in the Laplace domain for viscoelastic material is similar to that of Hook’s law in linear elastic constitutive equations. Hence, it is possible to solve the problem of viscoelastic laminate in the Laplace domain with the same elastic counterpart.
h
, and the length L. The geometry and coordinates of the laminated composite plate are shown in
Fig. 1
. Based on the Reissner-Mindlin plate theory which analyzes for firstorder transverse shear deformation, the time dependent displacement field across the laminate thickness can be expressed in the following form:
where
u
_{α}
^{0}
and
w
are displacements defined at the mid-plane of the laminated plates.
Due to the linearity of the Laplace transform, the displacement field in the Laplace domain can be written as,
In the present theory, the virtual work principle for quasistatic viscoelastic problems is described as:
where
v
is viscoelastic solid volume, and
a
is the surface on which the distributed loads
p
is applied.
Substituting the displacement fields into the virtual work principle and applying Laplace transform, the equilibrium equations can be obtained:
where stress resultants are defined as follows:
The resultants in the Laplace domain can be expressed as follows:
where stress resultants
A^{r}_{αβγδ}
are defined as follows:
For both static and harmonic loadings, the cylindrical bending behavior of the composite plate is analyzed. Thus, all of the equilibrium equations are reduced to the one dimensional form. The displacement variables are assumed as a trigonometric form by considering the simply supported boundary. In the time domain, the displacement and transverse load can be chosen to be of the forms:
where
α=n/L;p_{n}(t)
is the external load;
p_{n}(t)= P_{n}
sin(
ωt
) for harmonic loading, and
p_{n}(t)
=
P_{n}
for a static loading case. By substituting Eq. (17) into equilibrium equations, the algebraic relations in the Laplace domain can be obtained as follows:
where [
K
]
_{5×5}
is the numerical global stiffness matrix with the detail expression which will be shown in the Appendix.
By applying the inverse Laplace transform to Eq. (18), the algebraic relations in the real time domain can be obtained as follows:
where
f_{5}(t)
is the time dependent function of force which can be determined for two basic viscoelastic models and both static and harmonic loads.
From Eq. (19), the solutions of (
U
_{n,1}
^{0}
,
U
_{n,2}
^{0}
,
ϕ
_{n,1}
,
ϕ
_{n,2}
,
W_{n}
) are determined, then the displacements are calculated by substituting the obtained solution into the displacement fields. Therefore, all of the displacement, stress and strain of laminated composite plates can be determined.
where
u_{α}
^{0}
and w are displacement variables defined at the mid-plane of the laminated plates.
Being identical to Eq. (6)-(7), the displacement fields in the Laplace domain can be written as:
The number of the unknown variables is reduced by applying top and bottom surface traction free boundary conditions as follows:
Similar to FSDT analysis, substituting the displacement fields into the virtual work principle and applying Laplace transformation, the equilibrium equations can be obtained as follows:
where the added stress resultants are defined as:
The resultants in the Laplace domain can be expressed as follows:
where stress resultants
A^{r}_{αβγδ}
are defined similarly in the FSDT and
G^{r}_{αβγδ}
are defined as follows:
Executing the same procedure as the FSDT case, the algebraic relations can be obtained as follows:
where [
K
]
_{5×5}
is the numerical global stiffness matrix with the detail expression which will be shown in the Appendix.
By applying the inverse Laplace transform to Eq. (32), the algebraic relations can be obtained as follows:
From Eq. (33), the solutions of (
U
_{n,1}
^{0}
,
U
_{n,2}
^{0}
,
ϕ
_{n,1}
,
ϕ
_{n,2}
,
W_{n}
) are determined, then the displacements are calculated by substituting the variables into the displacement fields. Therefore, all of the displacement, strain and stress of laminated composite plates can be determined.
where
L
denotes the direction of the fiber and
T
denotes the direction perpendicular to the fiber. The shear correction factor for FSDT is chosen as
k
=5/6. The viscoelastic coefficient
a_{M}
for the Maxwell model and
a_{K}
for the Kelvin model are assumed as:
To show the influence of the viscoelastic coefficient to mechanical behavior especially transient time, the coefficients
a_{M}
and
a_{K}
are assumed in the following range:
for both static and harmonic loadings.
The displacements are normalized by the following nondimensional values:
where
S
represents the length to thickness ratio, which is defined by
S=L/h
.
The numerical examples consider both static and harmonic loads which are shown in
Fig. 2
. The static loading, which is constant with respect to time, is presented as follows:
where
u(t)
is the Heaviside unit step function which presents the recovery process of viscoelastic creep, and the recovery time
t
_{0}
=12
s
. The harmonic loading is presented as follows:
where
ω
is the frequency which is chosen to be small enough for the static problem (
ω
=1
s
^{-1}
).
W
for the creep and creep-recovery process based on FSDT and TSDT. The letter
E
means the analysis for the elastic solution;
V
indicates the analysis for the viscoelastic case. The responses of both FSDT and TSDT methods have good agreements for the deflection behavior of the Maxwell and Kelvin models. For the Maxwell model, the value of nondimensional deflection increases linearly with respect to time from We (
W_{e}
=2.409 with FSDT and
W_{e}
=2.699 with TSDT), which is the nondimensional deflection in the elastic case. For the
Time- dependent function of static and harmonic loads.
Kelvin model, at transient time, the value of deflection
W
of the mid-plane increases from 0 to
W_{e}
exponentially. For the creep-recovery process, the deflection
W
of the Maxwell model drops suddenly at
t_{0}
= 12
s
, and maintains that value constantly; the one for the Kelvin model decreases from
W_{e}
to 0. The difference between the FSDT and TSDT is the value of
W_{e}
derived from the linear elastic response. All of the above mechanical behaviors have good agreements with the linear viscoelastic creep and recovery responses which were presented by Flugge (1975).
Fig. 4
shows the time-dependent nondimensional inplane displacement
U
_{1}
for the Maxwell model based on the FSDT and TSDT. The elastic solution of FSDT is the straight line, but that of TSDT is the cubic line. The in-plane
Time-dependent nondimensional deflection W with static loading.
Time-dependent nondimensional in-plane displacement U1 for the Maxwell model with static loading.
displacement
U
_{1}
for the Maxwell model is greater than that of the elastic solution in time.
Fig. 5
presents the timedependent nondimensional in-plane displacement
U
_{1}
for the Kelvin model based on the FSDT and TSDT, with the time from 0 to 12s and the time step Δ
t
=0.1
s
. The displacement for the viscoelastic solution of the Kelvin model increases from 0 to the bound of the linear elastic solution at transient time. After that, the elastic and viscoelastic cases have nearly the same responses.
Fig. 6
shows the influence of viscoelastic coefficients for the Maxwell and Kelvin model to the deflection of the midplane for the TSDT. For the Maxwell model, the angle
ϑ_{M}
between the viscoelastic line and horizontal elastic line can be determined as follows:
Time-dependent nondimensional in-plane displacement U1 for the Kelvin model with static loading.
Influence of viscoelastic coefficient to deflection based on TSDT with static loading.
where
K
is the stiffness matrix. When the value
a_{M}
decreases, the angle ϑ also decreases. Thus, the solution is close to the elastic one. In contrast, for the Kelvin model, when
a_{K}
increases, the deflection of the viscoelastic solution is closer to the elastic one for both creep and creep-recovery. In some cases, with a small value of
a_{K}
, the deflection
W
does not have enough time to obtain
W_{e}
. Thereby, there is an amount of difference Δ
W
known as viscoelastic damping.
W
based on the FSDT and TSDT, respectively. Both methods present similar viscoelastic behavior for Maxwell and Kelvin models. For the elastic model, which
Time-dependent nondimensional deflection W based on FSDT with harmonic loading.
Time-dependent nondimensional deflection W based on TSDT with harmonic loading.
is represented as a continuous line, the displacement has the same phase with the harmonic loading Δ
φ
=0. For both viscoelastic models, there are phase delay Δ
φ_{M}
and Δ
φ_{K}
. For the Maxwell model, the center of deflection changes from 0 to
W_{M}
depending on the Maxwell viscoelastic coefficient
a_{M}
and the frequency
ω
of harmonic loading. The amplitude of deflection fluctuation of the viscoelastic solution is greater than the elastic one. The difference depends on the
a_{M}/ω
ratio. For the Kelvin model, the amplitude of fluctuation is smaller than that of the elastic model.
Fig. 9
presents the time-dependent nondimensional in-plane displacement
U
_{1}
for the Maxwell and Kelvin models based on the TSDT at the time when the inplane displacements have the maximum or minimum values. From these lines, the region of fluctuation of the
Amplitude of nondimensional in-plane displacement U1 based on TSDT.
Influence of the viscoelastic coefficient to the amplitude of deflection.
viscoelastic response for both Maxwell and Kelvin models are distinguished clearly. The fluctuation region of the elastic case is limited by two continuous lines; the one of viscoelastic case with the Maxwell model is limited by the discontinuous line, and the one with the Kelvin model is limited by the two dot-dashed lines. The amplitude of
U
_{1}
for the Kelvin model is smaller than the one of the elastic model. For the Maxwell model, there is a center difference which depends on both the viscoelastic coefficient and frequency of external loading.
Fig. 10
shows the effect of the viscoelastic coefficient to the amplitude of deflection in the case of harmonic loading. The upper figure is for the Maxwell model and the lower one is for the Kelvin model. With the small value of
a_{M}/ω
, the influence of the viscoelastic coefficient is insignificant, and the amplitude ratio of the Maxwell and elastic model is approximately 1. This ratio of amplitude increases when
a_{M}/ω
increases.
Fig. 11
presents the influence of the viscoelastic coefficient to the phase delay of the deflection in the case of harmonic loading. The upper figure of
Fig. 11
for the Maxwell model shows that when increasing the value of ratio
a_{M}/ω
, the phase delay increases linearly. In contrast, as presented in the lower figure of
Fig. 11
for the Kelvin model, the phase delay decreases when increasing the ratio
a_{K}/ω
.
Influence of the viscoelastic coefficient to the phase delay.
K
:
♣ The second row of stiffness matrix
K
:
♣ The third row of stiffness matrix
K
:
♣ The fourth row of stiffness matrix
K
:
♣ The fifth row of stiffness matrix
K
:
♣ The second row of stiffness matrix K:
♣ The third row of stiffness matrix K:
♣ The fourth row of stiffness matrix K:
♣ The fifth row of stiffness matrix K:
♣ For harmonic loading

Composite Laminates
;
Viscoelastic
;
Equivalent Single-layered Theories
;
Laplace Transformation
;
Maxwell Model
;
Kelvin Model.

1. Introduction

Composite materials have various applications in many engineering structural fields. Especially, aerospace structures require high stiffness and strength to weight ratio. These applications have required accurate prediction of the thermo-mechanical behavior of composite laminates for the design and analysis of structural composite. Therefore, advanced composites have been used continuously and have been expanded in their application for the last three decades. Numerous theories (Pagano, 1969; Pagano, 1970; Reddy, 2004) have been developed for the accurate analysis of laminated composite structures. Several equivalent single layer (ESL) plate theories (Reddy, 2004) are developed by assuming the form of the in-plane displacement field as a linear combination of unknown functions and the thickness coordinate. The first ESL theory is a classical laminated plate theory (CLPT), based on the Kirchoff-Love plate assumption that the in-plane displacement remains normal to the centerline of the plate after deformation. Improved theory over CLPT is a first-order shear deformation theory, which considers the transverse shear deformation of the plate which requires the shear correction factor. Even though the FSDT is more reliable than the CLPT, it still cannot accurately predict the mechanical behaviors for the laminated composite plates. Thus, more advanced theories have been required, and a series of the smeared higher order theories (Lo et al, 1977; Reddy, 1984) have been developed for the laminated composite plates. For instance, the third-order shear deformation theory uses a cubic polynomial for the in-plane displacement field. In TSDT, there is no need to use the shear correction factor. Among the advanced theories, efficient higher order plate theory (EHOPT), developed by Cho and Parmerter (1993), demonstrates the best performance among displacement-based zig-zag theories. It has been recognized that the zig-zag pattern of in-plane displacement provides the accuracy analysis of deformation and stress.
Meanwhile, in all of the above ESL theories, the material properties of composite laminates have been considered as linear elastic materials. In reality, composite laminates are inhomogeneous materials which are composed of a viscoelastic matrix and elastic fibers as reinforcement (Yi, Pollock, Ahmad and Hilton, 1994). Hence, like other viscoelastic materials, the mechanical behavior of fiber reinforced composites leads to creep strain, stress relaxation and time-dependent failure. These viscoelastic behaviors are critical when the composite laminates are in high temperature or vibrating conditions. Several researches (Hilton and Yi, 1993; Aboudi and Cederbaum, 1989) have analyzed the dynamic response of composite laminates considering the viscoelastic effects. For example, Srinatha and Lewis (Srinatha and Lewis, 1981) suggested a numerical procedure which solved an integral problem using the trapezoidal integration method for the Boltzmann superposition integral. As a result, the accuracy of the results depends on a time step Δt. However, it requires extensive computational time to obtain the reliable results by reducing the size of each time step, especially for long-term problems. Other researchers (Chen, 1995; Hilton and Yi, 1993) solved the problem of computational cost by using the Laplace transformation for a viscoelastic beam. The results in the real time domain were obtained by the inverse Laplace transformations based on numerical calculation.
In the present study, the mechanical behavior of viscoelastic composite laminates is investigated using the Laplace transformation based on the FSDT and TSDT. By applying Laplace transformation instead of the direct time integrations of the Boltzmann superposition integral and directly inversing the equations in the Laplace domain to the real time domain, the accuracy increases significantly as much as that of elastic counterparts. In addition, since the viscoelastic constitutive equation has the form of integration, the top and bottom stress free conditions cannot be directly applied in the TSDT model. Thus, based on the Laplace transformation, top and bottom stress free conditions are successfully applied in the Laplace domain, which makes the theoretical formulation very simple. The present theory considers viscoelasticity in two basic models: Maxwell and Kelvin for viscoelastic phenomena such as creep, cyclic creep and recovery. More complex models with extended Prony series can be developed from these basic models.
The presented and discussed numerical results focus on: (1) the comparison of deflections by using the FSDT and TSDT for elastic composite laminates; (2) the deflection of both elastic and viscoelastic composite laminate; (3) the influence of viscoelastic coefficients to dynamic responses of composite laminates; (4) the in-plane displacement of viscoelastic composite laminates.
2. Mathematical formulation

- 2.1. Constitutive equation for linear viscoelastic material

Instead of Hook’s law, the stress-strain relation for linear viscoelastic materials can be expressed by Boltzmann superposition integral equations:
Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

- 2.2. First-order shear deformation theory

In this paper, we consider a linear plate model with the thickness
Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

- 2.3. Third-order shear deformation theory

Following the third-order transverse deformation, the time dependent displacement can be expressed in the following forms:
Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

3. Numerical results and discussion

To compare the present analysis with the results of the previous study and other theories, the [0/90/0] laminated composite plate is chosen as an illustrative numerical example. The material properties of the ply are:
Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

- 3.1. Numerical result for static loading

Fig. 3
shows the nondimensional deflection
Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

- 3.2. Numerical result for harmonic loading

Fig. 7
and
8
show the time-dependent nondimensional deflection
Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

4. Conclusion

The mechanical behaviors of linear viscoelastic composite laminates have been analyzed by applying the Laplace transform without any integral transformation or any time step scheme. The numerical examples for static and harmonic loading under the quasi-static assumption show the creep responses of viscoelasticity for both the FSDT and TSDT cases. For the harmonic loading, the results of both basic models demonstrate the phase delay and the change of amplitude of deflection compared to the elastic one. For static loading, the Kelvin model has a better analysis for creep responses than that of the Maxwell model, especially in transient time.
For more efficient analysis, a higher-order cubic zig-zag theory such as efficient higher order plate theory (Cho, 1993), needs to be developed in the environment of viscoelastic behavior. In addition, a time-dependent relaxation modulus needs to be expresses through general Prony series which was developed in the present study for basic Maxwell and Kelvin models. These are currently under process.
- Appendix A. Components of the stiffness matrix K of FSDT:

♣ The first row of stiffness matrix
Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

- Appendix B. Components of the stiffness matrix K of TSDT:

♣ The first row of stiffness matrix K:
Lager Image

Lager Image

Lager Image

Lager Image

Lager Image

- Appendix C. The functions of f5(t):

♣ For static loading
Lager Image

Lager Image

Acknowledgements

This work was supported by WCU (World Class University) program through the National Research Foundation of Korea funded by the Ministry of Education, Science and Technology *(R31-10083).

Aboudi J.
,
Cederbaum G.
1989
“Analysis of viscoelastic laminated composite plates”
Composite Structures
12
243 -
256

Cederbaum G.
,
Aboudi J.
1989
“Dynamic response of viscoelastic laminated plates”
Journal of Sound and Vibration
133
(2)
225 -
238

Chen T. M.
1995
“The hybrid Laplace transform/finite element method applied to the quasi-static and dynamic analysis of viscoelastic Timoshenko beams”
International Journal for Numerical Methods in Engineering
38
509 -
522

Cho M.
,
Kim J. S.
1997
“Improved Mindlin plate stress analysis for laminated composites in finite element method”
AIAA Journal
35
(3)
587 -
590

Cho M.
,
Oh J.
2003
“Higher order zig-zag plate theory under thermo-electric-mechanical loads combined”
Composites: Part B
34
67 -
82

Cho M.
,
Parmerter R. R.
1993
“Higher order composite plate theory for general lamination configurations”
AIAA Journal
31
(7)
1299 -
1306

Eshmatov B. K.
2007
“Nonlinear vibrations and dynamic stability of viscoelastic orthotropic rectangular plates”
Journal of Sound and Vibration
300
709 -
726

Flaggs D. L.
,
Crossman F. W.
1981
“Analysis of the viscoelastic response of composite laminates during hygrothermal exposure”
Journal of Composite Materials
15
21 -
40

Flugge W.
1975
Viscoelasticity
Springer
Berlin, Heidelberg

Hilton H. H.
,
Yi S.
1993
“Anisotropic viscoelastic finite element analysis of mechanically and hygrothermally loaded composites”
Composite Engineering
3
(2)
123 -
135

Jones R. M.
1975
Mechanics of Composite Materials
McGraw-Hill, Inc, City

Kim J. S.
,
Cho M.
2007
“Enhanced first-order theory based on mixed formulation and transverse normal effect”
International Journal of Solids and Structures
44
1256 -
1276

Lakes R.
2009
Viscoelastic materials
Cambridge University Press
New York

Li J.
,
Weng G. J.
1996
“Effect of a viscoelastic interphase on the creep and stress/strain behavior of fiber-reinforced polymer matrix composite”
Composite part B
27B
589 -
598

Lo K. H.
,
Christensen R. M.
1977
“A higher-order theory of plate deformation, part 2: laminated plates”
Journal of Applied Mechanics
44
669 -
676

Narayanan G. V.
,
Beskos D. E.
1982
“Numerical operational methods for time-dependent linear problems”
International Journal for Numerical Methods in Engineering
18
1829 -
1854

Pagano N. J.
1969
“Exact solutions for composite laminates in cylindrical bending”
Journal of Composite Materials
3
398 -

Pagano N. J.
1970
“Exact solutions for rectangular bidirectional composites and sandwich plates”
Journal of Composite Materials
4
20 -

Pandya B. N.
,
Kant T.
1988
“Finite element stress analysis of laminated composite plates using higher order displacement model”
Composites Science and Technology
32
137 -
155

Reddy J. N.
1984
“A simple higher-order theory for laminated composite plates”
Journal of Applied Mechanics
51
745 -
752

Reddy J. N.
2004
Mechanics of Laminated Composite Plates and Shells: Theory and Analysis
CRC Press, City

Srinatha H. R.
,
Lewis R. W.
1981
“A finite element method for thermoviscoelastic analysis of plane problems”
Computer Methods in Applied Mechanics and Engineering
25
21 -
33

Whitney J. M.
,
Pagano N. J.
1970
“Shear deformation in heterogeneous anisotropic plates”
Journal of Applied Mechanics
37
1031 -
1036

Yi S.
,
Pollock G. D.
,
Ahmad M. F.
,
Hilton H. H.
1994
“Effective transverse Young’s modulus of composite with viscoelastic interphase”
AIAA Journal
33
(8)
1548 -
1550

Citing 'Application of the Laplace transformation for the analysis of viscoelastic composite laminates based on equivalent single-layer theories
'

@article{ HGJHC0_2012_v13n4_458}
,title={Application of the Laplace transformation for the analysis of viscoelastic composite laminates based on equivalent single-layer theories}
,volume={4}
, url={http://dx.doi.org/10.5139/IJASS.2012.13.3.458}, DOI={10.5139/IJASS.2012.13.3.458}
, number= {4}
, journal={International Journal of Aeronautical and Space Sciences}
, publisher={The Korean Society for Aeronautical & Space Sciences}
, author={Sy, Ngoc Nguyen
and
Lee, Jaehun
and
Cho, Maenghyo}
, year={2012}
, month={Dec}