# Nonlinear Free and Forced Vibration Behavior of Shear-Deformable Composite Beams with Shape Memory Alloy Fibers

Authors: Ren Yongsheng; Du Chenggang; Shi Yuyan
Journal: Shock and Vibration
 (2016)

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## Abstract

The nonlinear free and forced vibration of the composite beams embedded with shape memory alloy (SMA) fibers are investigated based on first-order shear deformation beam theory and the von Kármán type nonlinear strain-displacement equation. A thermomechanical constitutive equation of SMA proposed by Brinson is used to calculate the recovery stress of the constrained SMA fibers. The equations of motion are derived by using Hamilton’s principle. The approximate solution is obtained for vibration analysis of the composite beams based on the Galerkin approach. The parametric study is carried out to display the effect of the actuation temperature, the volume fraction, the initial strain of SMA fibers, and the length-to-thickness ratio. The shear deformation is shown to have a significant contribution to nonlinear vibration behavior of the composite beams with SMA fibers.


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## Body

## 1. Introduction

In the last two decades much progress has been made on the research of shape memory alloy (SMA) composite structures. By the design of the smart composite structures with highly integrated SMA actuators, the vibration control of complex flexible structures with rigorous weight limitations such as aerostructures has become possible. SMA is able to generate a relatively large deformation at a low temperature, but deformed SMA will return to their original shape upon heating. Prestrained SMA fibers are embedded within composite structures. When an electric current passes through SMA fibers, resistance heat is generated in the fibers and a large internal force is induced into the structures due to the return of fibers to their original shape. The force induced and the change in the mechanical properties of SMA fibers can be used in improving deflection, buckling, flutter, and vibration characteristics of composite structures.Zou [1] derived the incremental finite element motion equation for the nonlinear composite laminate embedded with SMA fibers, and the bending, thermobuckling, and postbuckling for the SMA reinforced composite laminate under transverse loading were discussed. Linear and nonlinear flutter behaviors of SMA reinforced composite laminates were studied by Kuo et al. [2] employing finite element method and approximate data from the SMA curves. Park et al. [3, 4] presented the finite element model for nonlinear flutter and vibration of composite laminates plates by using the approximate experimental fitting of SMA. Li et al. [5] studied free vibration of thermally pre/postbuckled circular thin plates with embedded SMA fibers. Shiau et al. [6] investigated the effect of SMA on the free vibration behavior of buckled cross-ply and angle-ply laminates by varying the SMA fiber spacing using the finite element method. Ren and Sun [7] investigated large amplitude flexural vibration of the orthotropic composite plate with embedded SMA fibers using the Galerkin approximate and harmonic balance methods. Asadi et al. [8, 9] investigated nonlinear free vibration, primary/secondary resonance, and thermal postbuckling of SMA fiber reinforced hybrid composite beams with symmetric and asymmetric layup; nonlinear von Kármán strain field was employed.However, most of the previous studies were performed based on finite element modeling of the geometric nonlinear structures [1–4, 6]. It can be seen that few researches presented analytical solutions for vibration analysis of SMA composite plates and beams accounting for the shear deformation. Furthermore, it is found that the thermomechanical behavior was described by the expression of approximate fitting or use of the approximate data obtained from the curves of SMA [2–4, 6].The objective of this work is to present a framework for analyzing smart composite beams with integral SMA active fibers for meeting the specific design requirements of the slender beam-like structures in aerospace and mechanical engineering structures, such as airplane wings and automotive drive shafts.The present analysis extends the previous work done for large amplitude vibration modeling of passive laminated composite beam with axially immovable ends [10, 11]. It also extends the closed-form solution of SMA fiber reinforced hybrid composite beams formulation presented by Asadi et al. [8] by taking into account the effects of the transverse shear. The resulting model is expected to correctly predict the dynamical behavior of for moderately thick and thick composite beams, accounting for the presence of SMA active fibers.In the current work, an analytical solution is presented to study the large amplitude vibration of composite beams with embedded SMA fibers. The one-dimensional constitutive equation of SMA proposed by Brinson [12] is used to calculate the recovery stress generated with SMA fibers. The first-order shear deformation beam theory and the von Kármán strain geometric nonlinearity as well as Hamilton’s principle are utilized to derive the nonlinear governing equations of motion. Using an analytical approach based on the Galerkin method, a closed-form solution of governing equations is derived. The closed-form solution is then applied to nonlinear free and forced vibration analysis of the composite beams. The parametric study is carried out to display the effect of the actuation temperature, the volume fraction, the initial strain of SMA fibers, and the length-to-thickness ratio. The shear deformation is shown to have a significant contribution to nonlinear vibration behaviors of the composite beams.


## 2. Formulations

The equations of motion for composite beams with embedded SMA fibers are obtained using the Hamilton principle, which is(1)∫t1t2δV+δWnc-δTdt=0,where δ
V, δ
T, and δ
W
n
c denote the virtual strain energy, the virtual kinetic energy, and the virtual work done by nonconservative forces, respectively.The strain energy is(2)V=12∫0L∫Aσxεx+τxzγxzdAdx.The strain-displacement equations considering von Kármán type of geometric nonlinearity and shear deformation can be written as(3)εx=ε-+zκ-+fz∂u1∂x,γxz=∂f∂zu1,where(4)ε-=∂u∂x+12∂w∂x2,κ-=-∂2w∂x2.Here, u
1 are unknown displacement functions of the midplane; f
(
z
) is a shape function describing the shear deformation across the thickness [10].The functionf
(
z
) obtained from different beam theories is presented in Table 1.Table 1
The shape function for different beam theories.
Beam theory
f
z
Euler-Bernoulli
0
Timoshenko
zThe off-axis stress-strain relation of SMA fibers hybrid lamina has the following forms [13]:(5)σxk=Q-11εx-Q-11cαxcΔT+m2Vsσr,τxzk=Q-55γxz,where σ
r denotes the effective recovery stress of SMA fiber which is obtained based on the one-dimensional model of SMA proposed by Brinson [12].The thermal expansion coefficientsα
x
c in (5) is given by(6)αxc=m2α1c+n2α2c,where α
1
c and α
2
c are the thermal expansion coefficient of the composite medium. m and n are the cosine and sine functions of the ply angle in each lamina, respectively. Also the off-axis stiffnesses can be expressed as Q
-
11
=
Q
11
m
4
+
2
(
Q
12
+
2
Q
66
)
m
2
n
2
+
Q
22
n
4, Q
-
55
=
m
2
Q
44
+
n
2
Q
55, and Q
-
11
c
=
Q
11
c
m
4 + 2
(
Q
12
c
+
2
Q
66
c
)
m
2
n
2
+
Q
22
c
n
4.The in-axis stiffnesses can be written as(7)Q11c=E1m1-ν12mν21m,Q12c=ν21mE2m1-ν12mν21m,Q21c=ν12mE1m1-ν12mν21m,Q22c=E2m1-ν12mν21m,Q66c=G12m,ν21mE2m=ν12mE1m,Q11=E11-ν12ν21,Q12=ν21E21-ν12ν21,Q21=ν12E11-ν12ν21,Q22=E21-ν12ν21,Q66=G12,ν21E2=ν12E1.The material properties of the composite beams embedded with SMA fibers can be written as(8)E1=E1mVm+EsVs,E2=E2mEsE2mVs+EsVm,G12=G13=G12mGsG12mVs+GsVm,G23=G23mVm+GsVs,Gs=Es21+νs,ν12=ν12mVm+νsVs,ρ=ρmVm+ρsVs,Vm+Vs=1,where the subscripts m and s denote the composite matrix and SMA fiber, respectively. The parameters E, G, ν, ρ, and V are Young’s modulus, the shear modulus, Poisson’s ratio, the material density, and the volume fraction, respectively.Using the one-dimensional SMA constitutive equation developed by Brinson [12], the expressions for the recovery stress of SMA fibers during heating and cooling can be, respectively, written as follows:during heating(9)σr=ΘT-T0+σ0,0≤T≤AsσEξε0-Eξ0ε0+Ωξξs-Ωξ0ξs0+ΘT-Asσ+σ1,Asσ≤T≤AfσΘT-Afσ+σ2,T≥Afσ,
during cooling(10)σr=ΘT-Afσ+σ2,Msσ≤T≤AfσEξε0-Eξ0ε0+Ωξξs+ΘT-Msσ+σ3,Mfσ≤T≤Msσ,where ξ denotes the martensite fraction, E
(
ξ
) denotes the elastic modulus of SMA, Θ denotes the thermal elastic modulus, T denotes temperature and T
0 is the reference temperature, and Ω
ξ denotes the phase transformation coefficient. The subscript 0 denotes initial state. A
s
σ and A
f
σ denote the start and finish temperatures of austenite in stress, and M
s
σ and M
f
σ denote the start and finish temperatures of martensite in stress. ξ
s is the martensite fraction induced by stress. And the subscript “s” denotes martensite fraction induced by stress corresponding to initial state. The first expression in (9) is used for SMA in the initial martensite state, while the third expression among them is used for SMA in 100% austenite state, and the second one among them is used for SMA in the phase transformation state from martensite to austenite.The transformation process from martensite to austenite (M
→
A) and from austenite to martensite are given, respectively, as follows (A
→
M): (11)ξM→A=ξs02cos⁡πAf-AsT-As-σrCA+1,(12)ξA→M=1-ξs02·cos⁡πσscr-σfcrσr-σfcr-CMT-Ms+1+ξs02,where M
s and M
f are the start and finish temperature points during the phase transformation from austenite to martensite and A
s and A
f are the start and finish temperature points during the phase transformation from martensite to austenite, respectively. C
A and C
M are material constant of SMA fibers. σ
s
c
r and σ
f
c
r are the start and finish stress points of phase transformation, respectively.In (9) and (10), σ
1 and σ
2 are the start and finish stress for the transformation (M
→
A); σ
3 is the start stress for the transformation (A
→
M).σ
1, σ
2, and σ
3 can be determined as follows:(13)σ1=ΘAsσ-T0+σ0,σ2=σ1+EAε0-Eξ0ε0-Ωξ0ξs0+ΘAfσ-Asσσ3=σ2+ΘMsσ-Afσ,Asσ=aAAs-bAσ0+bAΘT0aA+ΘbA,Afσ=aAAs-bAσ1-bAEAε0+bAEξ0ε0+bAΩξ0ξs0+bAΘAsσ+πaA+bAΘ,Msσ=σ2-σscr+CMMs-ΘAfσCM-Θ,Mfσ=σ3-σfcr+Eξ0ε0-EAε0+Ωξ0ξs0-ΘMsσ+CMMs+σfcr-σscr/πarccos⁡2ξ0-1CM-Θ.The elastic modulusE
s
ξ and the phase transformation coefficient Ω
ξ can be expressed, respectively, as(14)Eξ=EA+ξEM-EA,(15)Ωξ=-εLEξ,where E
M and E
A are Young’s modulus in the martensite and austenite phase, respectively, and ε
L is recovery strain limit.Substituting (3)–(5) into (2) results in(16)V=12∫0LNε-+Mκ-+Ms∂u1∂x1+Qsu1dx,where the following stress resultants are introduced:(17)N=∫AσxdA,M=∫AσxzdA,Ms=∫AσxfdA,Qs=∫Aτxz∂f∂xdA.Here N and M are the axial force and moment stress resultants; Q
s and M
s are stress resultants associated with the shear deformation. Using the stress-strain relation of the SMA reinforced lamina, the stress resultants can be expressed in terms of the strains as follows:(18)
N
M
M
s
=
b
A
11
B
11
E
11
B
11
D
11
F
11
E
11
F
11
H
11
ε
-
κ
-
u
1
′
-
N
T
M
T
M
s
T
+
N
r
M
r
M
s
r
,
Q
s
=
b
A
55
u
1
,where(19)A11,B11,D11=∑k=1n∫hk-1hkQ-111,z,z2dz,E11,F11,H11=∑k=1n∫hk-1hkQ-11f,fz,f2dz,A55=∑k=1n∫hk-1hkQ-55∂f∂x2dz,NT,MT,MsT=∑k=1n∫hk-1hkQ-11cαxΔT1,z,fdz,Nr,Mr,Msr=∑k=1n∫hk-1hkm2Vsσr1,z,fdz.Here, the superscripts “T” and “r” refer to the in-plane forces and moments induced by temperature and recovery stress of SMA fibers, respectively.By using (4), the variation of the strain energy (16) can be written as(20)
δ
V
=
∫
0
L
-
∂
N
∂
x
δ
u
-
∂
∂
x
N
∂
w
∂
x
+
∂
2
M
∂
x
2
δ
w
+
Q
s
-
∂
M
s
∂
x
δ
u
1
d
x
.The kinetic energy of the composite beam can be expressed as(21)T=12∫0L∫AρU˙2+W˙2dAdx=b2∫0L∫-h/2h/2ρu˙-z∂w˙∂x+fu˙12+w˙2dzdx,where the dot denotes differentiation with respect to time.The variation of the kinetic energy (21) is given as(22)
δ
T
=
-
b
∫
0
L
m
1
u
¨
-
m
2
∂
w
¨
∂
x
+
m
4
u
¨
1
δ
u
+
m
1
w
¨
+
m
2
∂
u
¨
∂
x
-
m
3
∂
2
w
¨
∂
x
2
+
m
5
∂
u
¨
1
∂
x
δ
w
+
m
4
u
¨
-
m
5
∂
w
¨
∂
x
+
m
6
u
¨
1
δ
u
1
d
x
,where(23)m1=∑k=1n∫hk-1hkρdz,m2=∑k=1n∫hk-1hkρzdz,m3=∑k=1n∫hk-1hkρz2dz,m4=∑k=1n∫hk-1hkρfdz,m5=∑k=1n∫hk-1hkρfzdz,m6=∑k=1n∫hk-1hkρf2dz.The work done by nonconservative forces can be given as(24)Wnc=-b∫0Lqwdx,where q is the out-of-plane mechanical load.Applying Hamilton principle leads to the following equations of motion:(25)m1u¨-m2∂w¨∂x+m4u¨1-1b∂N∂x=0,m1w¨+m2∂u¨∂x-m3∂2w¨∂x2+m5∂u¨1∂x-1b∂∂xN∂w∂x+∂2M∂x2=q,m4u¨-m5∂w¨∂x+m6u¨1+1bQs-1b∂M∂x=0.The simplified nonlinear governing equations can be obtained from (25) by setting the in-plane inertia and rotational terms equal to zero.The resulting equations are(26)∂N∂x=0,m1w¨+m5∂u¨1∂x-1b∂∂xN∂w∂x+∂2M∂x2=q,m6u¨1+1bQs-1b∂M∂x=0.From the first equation of (26), it is evident that the axial force N is a constant, which means that the following equation holds:(27)
∂
N
∂
x
=
∂
∂
x
A
11
∂
u
∂
x
+
1
2
∂
w
∂
x
2
-
B
11
∂
2
w
∂
x
2
+
E
11
∂
u
1
∂
x
-
N
T
+
N
r
=
0
.Integrating (27) along the x-axis yields(28)u=-12∫0x∂w∂x2dx+B11A11∂w∂x-E11A11u1+1A11NT-Nr+C1x+C2.Using the in-plane boundary conditionsu
(
0
,
t
)
=
u
(
L
,
t
)
=
0 in (28), the constants C
1 and C
2 can be determined as(29)C1=A112L∫0L∂w∂x2dx-B11L∂wL,t∂x-∂w0,t∂x+E11Lu1L,t-u10,t-NT-Nr,C2=1A11E11u10,t-B11∂w0,t∂x.To this end, we can obtain the following axial forceN in terms of displacements:(30)N=bA11At-NT+Nr,where(31)At=12L∫0L∂w∂x2dx+E11LA11u1L,t-u10,t-B11LA11∂wL,t∂x-∂w0,t∂x.Finally, by substituting (18) and (30) into the second and third equations of (26), the nonlinear equations of motion for SMA hybrid composite beam in terms of displacements can be written as(32)m1w¨+m5∂u¨1∂x-B112A11-D11∂4w∂x4-F11-B11E11A11∂3u1∂x3-A11At-NT+Nr∂2w∂x2=q,m6u¨1-H11-E112A11u¨1+A55u1-B11E11A11-F11∂3w∂x3=0.For a symmetric laminate, the stiffness coefficientsB
11
=
E
11
=
0. The equations of motion reduce to(33)m1w¨+m5∂u¨1∂x+D11∂4w∂x4-F11∂3u1∂x3-A112L∫0L∂w∂x2dx-NT+Nr∂2w∂x2=q,m6u¨1-H11∂2u1∂x2+A55u1+F11∂3w∂x3=0.The boundary conditions of a simply supported beam can be given as(34)w=M=Ms=0,atx=0,L.It can be proved that the simply supported boundary conditions also have the following form:(35)∂2w∂x2=∂u1∂x=0,atx=0,L.The Galerkin procedure is employed here to find the approximate solution of the nonlinear equations of motion (33). For simply supported beam the following form of displacements is assumed:(36)wx,t=Atsin⁡πxL,u1x,t=Btcos⁡πxL.Substitution of (36) into (33) and applying the Galerkin procedure yield (37)d2Adt2+α1d2Bdt2+α2A+α3B+α4A3=α5cos⁡ωt,d2Bdt2+β1B+β2A=0,where(38)α1=-πm5Lm1,α2=1m1πL4D11+πL2-NT+Nr,α3=-F11m1πL3,α4=A114m1πL4,α5=4q0m1,β1=1m6πL2H11+A55,β2=-F11m6πL3.In order to obtain the approximate solutions of nonlinear vibration (note that free vibration equations can be obtained from (37) by setting nonconservative force terms α
5 equal to zero), we use the harmonic balance method to solve (37).The nonlinear natural frequency equation and the steady-state forced response equation are obtained, respectively, as(39)ωn2=12β1+α2+34α4A02-α1β2±β1+α2+34α4A02-α1β22-4β1α2+34α4A02-α3β2,B0=β2ωn2-β1A0,(40)34α4A-3+α3-α1ω2β2ω2-β12+α2-ω2A--α5=0,B-=β2ω2-β1A-,where A
0, B
0 and A
-, B
- are the nonlinear free and forced vibration amplitudes, respectively, and ω
n and ω are the nonlinear fundamental frequency and excited frequency, respectively.


## 3. Numerical Results and Discussions

### 3.1. Model Validation

Gunda et al. [11] presented large amplitude free vibration analysis of laminated composite beam based on the concept of coupled displacement field (CDF). They obtained the nonlinear natural frequency by using Rayleigh-Ritz (R-R) method. Accuracy of the closed-form expressions presented using R-R (CDF) method was evaluated using the finite element formulation. A graphite-epoxy laminated simply supported beam with six layers of uniform thickness and having a length of 0.25 m, a width of 0.01 m, and a height of 0.001 m is considered for establishing results [11]. The material properties considered are E
1
=
155 GPa, E
2
=
12.1 GPa, ν
12
=
0.248, G
12
=
4.4 GPa, and ρ
=
1570 kg/m3.Figure1 presents the numerical results for the nonlinear natural frequency with the free vibration amplitude, as a function of the SMA fiber volume fraction V
s. For each stacking sequence as described in [11], the SMA fibers are arranged to orientate at 0°. The results show that higher nonlinear natural frequency can be achieved for the active composite beams as compared with exact results for passive one reported by Gunda et al. [11] (V
s
=
0.0).Figure 1
Large amplitude vibration behavior of laminated composite beams with symmetric layup orientations (T = 50°C, ε
0
=
0.03): (a) cross-ply; (b) [90°/90°/0°]s; (c) [0°/90°/90°]s; and (d) unidirectional.
(a)
(b)
(c)
(d)


### 3.2. Parametric Analysis

Nonlinear free vibration and forced behavior of the composite beams with embedded SMA fibers are studied. The composite matrix material used in the numerical examples is glass/epoxy. Its properties are listed in Table2. The [45/−45/0
S
M
A/90]s symmetrically laminated simply supported beam with eight layers of the same thickness and total thickness of 0.001 m is considered in this work. The material properties of SMA fiber are listed in Table 3.Table 2
The material parameters of glass/epoxy.
E
1
m (GPa)
25 × 10−3
E
2
m (GPa)
1 × 10−3
G
12
m (GPa)
0.5 × 10−3
ρ (kg/m−3)
1856
v
12
m
0.25
α
1
m (1/°C)
0.2 × 10−6
α
2
m (1/°C)
16 × 10−6Table 3
Material properties of SMA wires.
SMA (nitinol)
E
A/MPa
67 × 103
E
M/MPa
26.3 × 103
σ
s
c
r/MPa
100
σ
f
c
r/MPa
170
ε
L
0.067
Θ/(MPa/°C)
0.55
M
f/°C
9
M
s/°C
18.4
A
s/°C
34.5
A
f/°C
49
C
M/(MPa/°C)
8
C
A/(MPa/°C)
13.8
ρ/(kg/m3)
6450The length and width of the beam are assumed to be 0.1 m and 0.01 m, respectively.The variation of the nonlinear natural frequency with the free vibration amplitude is presented in Figure2. Composite beams with four different L
/
h (i.e., L
/
h
=
5, 10, 20, and 50) are considered. As can be seen from the figures, L
/
h is an important parameter in the analysis of vibration of the composite beams. It is also seen that the shear deformation effect can be neglected for L
/
h of 50.Figure 2
Variation of the nonlinear natural frequency with the free vibration amplitudeA
0 (T = 50°C, ε
0
=
0.03, V
s
=
0.005, and h
=
0.001 m): (a) L
/
h
=
5; (b) L
/
h
=
10; (c) L
/
h
=
20; and (d) L
/
h
=
50.
(a)
(b)
(c)
(d)Table4 presents the nonlinear natural frequency for the composite beams having different V
s using different beam theories. In the table, it can be noted that the nonlinear natural frequencies initially decrease for the composite beams with low value of V
s. This is due to the compressive force induced by the thermal expansion of the composite and SMA fibers. The nonlinear natural frequencies are then increased with increasing of V
s. It is evidenced that the compressive force induced by the thermal expansion of the composite could be overcome by a tensile force induced by the strain recovery of the prestrained SMA fibers with high value of V
s at a temperature above A
f. The above-mentioned characteristics are more evident for higher value of A
0
/
h. It is also seen that, for the composite beams with high value of A
0
/
h, the effect of shear deformation is more significant.Table 4
The nonlinear natural frequency for different values ofV
s with various A
0
/
h (L
/
h
=
6, T = 60°C, and ε
0
=
0.03).
A
0
/
h
Beam theory
V
s = 0.000
V
s = 0.005
V
s = 0.150
1
Euler-Bernoulli
2.0707 × 104
1.8512 × 104
3.9777 × 104
Timoshenko
1.4572 × 104
1.4222 × 104
3.8129 × 104
5
Euler-Bernoulli
6.4337 × 104
5.2779 × 104
6.1971 × 104
Timoshenko
6.2632 × 104
5.1432 × 104
6.0927 × 104
7
Euler-Bernoulli
8.8599 × 104
7.2309 × 104
7.8094 × 104
Timoshenko
8.7369 × 104
7.1331 × 104
7.7268 × 104Table5 presents the nonlinear natural frequency for the composite beams having different ε
0 using different beam theories. As shown in the table, the initial strain of SMA fibers appears to have marginal effect on nonlinear natural frequencies.Table 5
The nonlinear natural frequency for different values ofε
0 with various A
0
/
h (L
/
h
=
6, T = 60°C, and V
s = 0.005).
A
0
/
h
Beam theory
ε
0
=
0.000
ε
0
=
0.030
ε
0
=
0.075
1
Euler-Bernoulli
1.8463 × 104
1.8512 × 104
1.8564 × 104
Timoshenko
1.4159 × 104
1.4222 × 104
1.4290 × 104
5
Euler-Bernoulli
5.2761 × 104
5.2779 × 104
5.2798 × 104
Timoshenko
5.1413 × 104
5.1432 × 104
5.1451 × 104
7
Euler-Bernoulli
7.2295 × 104
7.2309 × 104
7.2323 × 104
Timoshenko
7.1317 × 104
7.1331 × 104
7.1346 × 104Table6 presents the nonlinear natural frequency for the composite beams having different T using different beam theories. It can be observed that the actuation temperature of SMA fiber has much more influence for the low value of A
0
/
h than for the high value of A
0
/
h.Table 6
The nonlinear natural frequency for different values ofT with various A
0
/
h (L
/
h
=
6, ε
0
=
0.03, and  V
s = 0.005).
A
0
/
h
Beam theory
T = 20°C
T = 60°C
T = 120°C
1
Euler-Bernoulli
1.7838 × 104
1.8512 × 104
1.9347 × 104
Timoshenko
1.3332 × 104
1.4222 × 104
1.5295 × 104
5
Euler-Bernoulli
5.2551 × 104
5.2779 × 104
5.3073 × 104
Timoshenko
5.1197 × 104
5.1432 × 104
5.1733 × 104
7
Euler-Bernoulli
7.2145 × 104
7.2309 × 104
7.2520 × 104
Timoshenko
7.1165 × 104
7.1331 × 104
7.1545 × 104The variation of the nonlinear natural frequency with the actuation temperature of SMA fibers for composite beams (ε
0
=
0.03, V
s
=
0.005, and A
0
/
h
=
1) with three different L
/
h (i.e., L
/
h
=
5, 10, and 20) is presented in Figure 3. The phase transformation M
→
A is induced during heating, and the phase transformation A
→
M is induced during cooling. The curves of the nonlinear natural frequency versus temperature are typical hysteresis loops in a thermal cycle; the nonlinear natural frequency increases with the increase in temperature during heating, but decline with the decrease in temperature during cooling. Furthermore, it can be seen that the nonlinear natural frequency increases with a decrease in L
/
h of the composite beam. In short composite beams, great differences exist between nonlinear natural frequencies evaluated using the Euler-Bernoulli’s beam theory and Timoshenko’s beam theory. However, these differences can be neglected in long composite beams.Figure 3
Variation of the nonlinear natural frequency with the actuation temperature of SMA fibers (ε
0
=
0.03, V
s
=
0.005, and A
0
/
h
=
1): (a) L
/
h
=
5; (b) L
/
h
=
10; and (c) L
/
h
=
20.
(a)
(b)
(c)AmplitudeA
- versus frequency responses of the composite beams with SMA fibers in the phase transformation state from martensite to austenite are shown, respectively, in Figure 4 under the excitations. In the figure, L
/
h varying from 5 to 50 are considered to observe their effects on the steady-state responses. From the three figures it can be seen that deformation shear has significant effect on the shapes of the frequency-response curves for lower L
/
h. The results also show that the response curves bend more strongly towards the ω-axis direction as L
/
h decreases.Figure 4
Frequency responses of the composite beams in the phase transformation state from martensite to austenite under the excitations (T = 50°C, ε
0
=
0.03, V
s
=
0.005, and q
0
=
10 N): (a) L
/
h
=
5; (b) L
/
h
=
10; and (c) L
/
h
=
50.
(a)
(b)
(c)Figures5 and 6 present the variation of the nonlinear natural frequency with the free vibration amplitude for different V
s. The results show that the effect of SMA fiber volume fraction is important.Figure 5
Variation of the nonlinear natural frequency with the free vibration amplitudeA
0 for different V
s (T = 50°C, ε
0
=
0.005, and L
/
h
=
10).Figure 6
Variation of the nonlinear natural frequency with the free vibration amplitudeB
0 for different V
s (T = 50°C, ε
0
=
0.005, and L
/
h
=
10).Figures7 and 8 present the variation of the nonlinear natural frequency with the free vibration amplitude for different T. The results show that the nonlinear natural frequency increases with the increase of the actuation temperature of SMA fibers.Figure 7
Variation of the nonlinear natural frequency with the free vibration amplitudeA
0 for differentT (V
s
=
0.005, ε
0
=
0.01, and L
/
h
=
10).Figure 8
Variation of the nonlinear natural frequency with the free vibration amplitudeB
0 for differentT (V
s
=
0.005, ε
0
=
0.01, and L
/
h
=
10).Figures9 and 10 present the variation of the nonlinear natural frequency with the free vibration amplitude for different ε
0. The results show that the initial strain of SMA fibers appears to have marginal effect on the nonlinear natural frequency.Figure 9
Variation of the nonlinear natural frequency with the free vibration amplitudeA
0 for different ε
0 (V
s
=
0.005,T = 60°C, and L
/
h
=
10).Figure 10
Variation of the nonlinear natural frequency with the free vibration amplitudeB
0 for different ε
0 (V
s
=
0.005,T = 60°C, and L
/
h
=
10).Figure11 presents variation of the nonlinear natural frequency with the actuation temperature of SMA fibers for the composite beams with different V
s. As shown in Figure 11, the nonlinear natural frequency of the composite beam without SMA fibers (V
s
=
0) is seen to decrease linearly with the increase of temperature. This is because there is not recovery stress of the SMA fiber in this case, as a result of the stiffness softening; therefore, the nonlinear natural frequency is reduced. However, it is seen from Figure 11 that SMA fiber embeddings result in significant increase of the nonlinear natural frequency compared with the result of the composite beams without SMA.Figure 11
Variation of the nonlinear natural frequency with the actuation temperature for differentV
s (ε
0
=
0.03, A
0
/
h
=
1, and L
/
h
=
10).Figure12 presents variation of the nonlinear natural frequency with the actuation temperature of SMA fibers for the composite beams with different ε
0. The results show that there is an obvious change in the shapes of nonlinear natural frequency versus temperature curves as the initial strain of SMA wire is increased.Figure 12
Variation of the nonlinear natural frequency with the actuation temperature for differentε
0 (V
s
=
0.005, A
0
/
h
=
1, and L
/
h
=
10).Figure13 presents variation of the nonlinear natural frequency with the actuation temperature of SMA fibers for the composite beams with different A
0. The increase of free vibration amplitude is accompanied by the shift of these hysteresis loops of nonlinear natural frequency versus temperature towards higher nonlinear natural frequency. It seems that the hysteresis effect is more significant for linear vibration beam (A
0
=
0), in comparison with nonlinear vibration beams (A
0
≠
0).Figure 13
Variation of the nonlinear natural frequency with the actuation temperature for differentA
0 (ε
0
=
0.03, V
s
=
0.005, and L
/
h
=
10).Figures14 and 15 present the variation of amplitudes A
- and B
- with excited frequency, respectively. Also the effect of the volume fraction of SMA fibers is shown in these figures. The results show that the increase of V
s leads to the shift of steady-state responses curves towards higher excited frequency.Figure 14
AmplitudeA
- versus frequency responses of the composite beams in the phase transformation state from martensite to austenite under the excitations (T = 60°C, ε
0
=
0.008, q
0
=
10 N, and L
/
h
=
10).Figure 15
AmplitudeB
- versus frequency responses of the composite beams in the phase transformation state from martensite to austenite under the excitations for different V
s (T = 60°C, ε
0
=
0.008, q
0
=
10 N, and L
/
h
=
10).Figures16 and 17 present the variation of amplitudes A
- and B
- with excited frequency, respectively. The effect of ε
0 is also considered. It can be seen that the increase of ε
0 leads to the shift of steady-state responses curves towards higher excited frequency.Figure 16
AmplitudeA
- versus frequency responses of the composite beams in the phase transformation state from martensite to austenite under the excitations for different ε
0 (T = 60°C, V
s
=
0.005, q
0
=
10 N, and L
/
h
=
10).Figure 17
AmplitudeB
- versus frequency responses of the composite beams in the phase transformation state from martensite to austenite under the excitations for different ε
0 (T = 60°C, V
s
=
0.005, q
0
=
10 N, and L
/
h
=
10).Figures18 and 19 present the variation of amplitudes A
- and B
- with excited frequency, respectively, for different T. As can be clearly seen in the figure, the steady-state responses curves shift towards higher excited frequency as T increases.Figure 18
AmplitudeA
- versus frequency responses of the composite beams in the phase transformation state from Martensite to Austenite under the excitations for different T (ε
0
=
0.036, V
s
=
0.005, q
0
=
10 N, L
/
h
=
10).Figure 19
AmplitudeB
- versus frequency responses of the composite beams in the phase transformation state from martensite to austenite under the excitations for different T (ε
0
=
0.036, V
s
=
0.005, q
0
=
10 N, and L
/
h
=
10).


## 3.1. Model Validation

Gunda et al. [11] presented large amplitude free vibration analysis of laminated composite beam based on the concept of coupled displacement field (CDF). They obtained the nonlinear natural frequency by using Rayleigh-Ritz (R-R) method. Accuracy of the closed-form expressions presented using R-R (CDF) method was evaluated using the finite element formulation. A graphite-epoxy laminated simply supported beam with six layers of uniform thickness and having a length of 0.25 m, a width of 0.01 m, and a height of 0.001 m is considered for establishing results [11]. The material properties considered are E
1
=
155 GPa, E
2
=
12.1 GPa, ν
12
=
0.248, G
12
=
4.4 GPa, and ρ
=
1570 kg/m3.Figure1 presents the numerical results for the nonlinear natural frequency with the free vibration amplitude, as a function of the SMA fiber volume fraction V
s. For each stacking sequence as described in [11], the SMA fibers are arranged to orientate at 0°. The results show that higher nonlinear natural frequency can be achieved for the active composite beams as compared with exact results for passive one reported by Gunda et al. [11] (V
s
=
0.0).Figure 1
Large amplitude vibration behavior of laminated composite beams with symmetric layup orientations (T = 50°C, ε
0
=
0.03): (a) cross-ply; (b) [90°/90°/0°]s; (c) [0°/90°/90°]s; and (d) unidirectional.
(a)
(b)
(c)
(d)


## 3.2. Parametric Analysis

Nonlinear free vibration and forced behavior of the composite beams with embedded SMA fibers are studied. The composite matrix material used in the numerical examples is glass/epoxy. Its properties are listed in Table2. The [45/−45/0
S
M
A/90]s symmetrically laminated simply supported beam with eight layers of the same thickness and total thickness of 0.001 m is considered in this work. The material properties of SMA fiber are listed in Table 3.Table 2
The material parameters of glass/epoxy.
E
1
m (GPa)
25 × 10−3
E
2
m (GPa)
1 × 10−3
G
12
m (GPa)
0.5 × 10−3
ρ (kg/m−3)
1856
v
12
m
0.25
α
1
m (1/°C)
0.2 × 10−6
α
2
m (1/°C)
16 × 10−6Table 3
Material properties of SMA wires.
SMA (nitinol)
E
A/MPa
67 × 103
E
M/MPa
26.3 × 103
σ
s
c
r/MPa
100
σ
f
c
r/MPa
170
ε
L
0.067
Θ/(MPa/°C)
0.55
M
f/°C
9
M
s/°C
18.4
A
s/°C
34.5
A
f/°C
49
C
M/(MPa/°C)
8
C
A/(MPa/°C)
13.8
ρ/(kg/m3)
6450The length and width of the beam are assumed to be 0.1 m and 0.01 m, respectively.The variation of the nonlinear natural frequency with the free vibration amplitude is presented in Figure2. Composite beams with four different L
/
h (i.e., L
/
h
=
5, 10, 20, and 50) are considered. As can be seen from the figures, L
/
h is an important parameter in the analysis of vibration of the composite beams. It is also seen that the shear deformation effect can be neglected for L
/
h of 50.Figure 2
Variation of the nonlinear natural frequency with the free vibration amplitudeA
0 (T = 50°C, ε
0
=
0.03, V
s
=
0.005, and h
=
0.001 m): (a) L
/
h
=
5; (b) L
/
h
=
10; (c) L
/
h
=
20; and (d) L
/
h
=
50.
(a)
(b)
(c)
(d)Table4 presents the nonlinear natural frequency for the composite beams having different V
s using different beam theories. In the table, it can be noted that the nonlinear natural frequencies initially decrease for the composite beams with low value of V
s. This is due to the compressive force induced by the thermal expansion of the composite and SMA fibers. The nonlinear natural frequencies are then increased with increasing of V
s. It is evidenced that the compressive force induced by the thermal expansion of the composite could be overcome by a tensile force induced by the strain recovery of the prestrained SMA fibers with high value of V
s at a temperature above A
f. The above-mentioned characteristics are more evident for higher value of A
0
/
h. It is also seen that, for the composite beams with high value of A
0
/
h, the effect of shear deformation is more significant.Table 4
The nonlinear natural frequency for different values ofV
s with various A
0
/
h (L
/
h
=
6, T = 60°C, and ε
0
=
0.03).
A
0
/
h
Beam theory
V
s = 0.000
V
s = 0.005
V
s = 0.150
1
Euler-Bernoulli
2.0707 × 104
1.8512 × 104
3.9777 × 104
Timoshenko
1.4572 × 104
1.4222 × 104
3.8129 × 104
5
Euler-Bernoulli
6.4337 × 104
5.2779 × 104
6.1971 × 104
Timoshenko
6.2632 × 104
5.1432 × 104
6.0927 × 104
7
Euler-Bernoulli
8.8599 × 104
7.2309 × 104
7.8094 × 104
Timoshenko
8.7369 × 104
7.1331 × 104
7.7268 × 104Table5 presents the nonlinear natural frequency for the composite beams having different ε
0 using different beam theories. As shown in the table, the initial strain of SMA fibers appears to have marginal effect on nonlinear natural frequencies.Table 5
The nonlinear natural frequency for different values ofε
0 with various A
0
/
h (L
/
h
=
6, T = 60°C, and V
s = 0.005).
A
0
/
h
Beam theory
ε
0
=
0.000
ε
0
=
0.030
ε
0
=
0.075
1
Euler-Bernoulli
1.8463 × 104
1.8512 × 104
1.8564 × 104
Timoshenko
1.4159 × 104
1.4222 × 104
1.4290 × 104
5
Euler-Bernoulli
5.2761 × 104
5.2779 × 104
5.2798 × 104
Timoshenko
5.1413 × 104
5.1432 × 104
5.1451 × 104
7
Euler-Bernoulli
7.2295 × 104
7.2309 × 104
7.2323 × 104
Timoshenko
7.1317 × 104
7.1331 × 104
7.1346 × 104Table6 presents the nonlinear natural frequency for the composite beams having different T using different beam theories. It can be observed that the actuation temperature of SMA fiber has much more influence for the low value of A
0
/
h than for the high value of A
0
/
h.Table 6
The nonlinear natural frequency for different values ofT with various A
0
/
h (L
/
h
=
6, ε
0
=
0.03, and  V
s = 0.005).
A
0
/
h
Beam theory
T = 20°C
T = 60°C
T = 120°C
1
Euler-Bernoulli
1.7838 × 104
1.8512 × 104
1.9347 × 104
Timoshenko
1.3332 × 104
1.4222 × 104
1.5295 × 104
5
Euler-Bernoulli
5.2551 × 104
5.2779 × 104
5.3073 × 104
Timoshenko
5.1197 × 104
5.1432 × 104
5.1733 × 104
7
Euler-Bernoulli
7.2145 × 104
7.2309 × 104
7.2520 × 104
Timoshenko
7.1165 × 104
7.1331 × 104
7.1545 × 104The variation of the nonlinear natural frequency with the actuation temperature of SMA fibers for composite beams (ε
0
=
0.03, V
s
=
0.005, and A
0
/
h
=
1) with three different L
/
h (i.e., L
/
h
=
5, 10, and 20) is presented in Figure 3. The phase transformation M
→
A is induced during heating, and the phase transformation A
→
M is induced during cooling. The curves of the nonlinear natural frequency versus temperature are typical hysteresis loops in a thermal cycle; the nonlinear natural frequency increases with the increase in temperature during heating, but decline with the decrease in temperature during cooling. Furthermore, it can be seen that the nonlinear natural frequency increases with a decrease in L
/
h of the composite beam. In short composite beams, great differences exist between nonlinear natural frequencies evaluated using the Euler-Bernoulli’s beam theory and Timoshenko’s beam theory. However, these differences can be neglected in long composite beams.Figure 3
Variation of the nonlinear natural frequency with the actuation temperature of SMA fibers (ε
0
=
0.03, V
s
=
0.005, and A
0
/
h
=
1): (a) L
/
h
=
5; (b) L
/
h
=
10; and (c) L
/
h
=
20.
(a)
(b)
(c)AmplitudeA
- versus frequency responses of the composite beams with SMA fibers in the phase transformation state from martensite to austenite are shown, respectively, in Figure 4 under the excitations. In the figure, L
/
h varying from 5 to 50 are considered to observe their effects on the steady-state responses. From the three figures it can be seen that deformation shear has significant effect on the shapes of the frequency-response curves for lower L
/
h. The results also show that the response curves bend more strongly towards the ω-axis direction as L
/
h decreases.Figure 4
Frequency responses of the composite beams in the phase transformation state from martensite to austenite under the excitations (T = 50°C, ε
0
=
0.03, V
s
=
0.005, and q
0
=
10 N): (a) L
/
h
=
5; (b) L
/
h
=
10; and (c) L
/
h
=
50.
(a)
(b)
(c)Figures5 and 6 present the variation of the nonlinear natural frequency with the free vibration amplitude for different V
s. The results show that the effect of SMA fiber volume fraction is important.Figure 5
Variation of the nonlinear natural frequency with the free vibration amplitudeA
0 for different V
s (T = 50°C, ε
0
=
0.005, and L
/
h
=
10).Figure 6
Variation of the nonlinear natural frequency with the free vibration amplitudeB
0 for different V
s (T = 50°C, ε
0
=
0.005, and L
/
h
=
10).Figures7 and 8 present the variation of the nonlinear natural frequency with the free vibration amplitude for different T. The results show that the nonlinear natural frequency increases with the increase of the actuation temperature of SMA fibers.Figure 7
Variation of the nonlinear natural frequency with the free vibration amplitudeA
0 for differentT (V
s
=
0.005, ε
0
=
0.01, and L
/
h
=
10).Figure 8
Variation of the nonlinear natural frequency with the free vibration amplitudeB
0 for differentT (V
s
=
0.005, ε
0
=
0.01, and L
/
h
=
10).Figures9 and 10 present the variation of the nonlinear natural frequency with the free vibration amplitude for different ε
0. The results show that the initial strain of SMA fibers appears to have marginal effect on the nonlinear natural frequency.Figure 9
Variation of the nonlinear natural frequency with the free vibration amplitudeA
0 for different ε
0 (V
s
=
0.005,T = 60°C, and L
/
h
=
10).Figure 10
Variation of the nonlinear natural frequency with the free vibration amplitudeB
0 for different ε
0 (V
s
=
0.005,T = 60°C, and L
/
h
=
10).Figure11 presents variation of the nonlinear natural frequency with the actuation temperature of SMA fibers for the composite beams with different V
s. As shown in Figure 11, the nonlinear natural frequency of the composite beam without SMA fibers (V
s
=
0) is seen to decrease linearly with the increase of temperature. This is because there is not recovery stress of the SMA fiber in this case, as a result of the stiffness softening; therefore, the nonlinear natural frequency is reduced. However, it is seen from Figure 11 that SMA fiber embeddings result in significant increase of the nonlinear natural frequency compared with the result of the composite beams without SMA.Figure 11
Variation of the nonlinear natural frequency with the actuation temperature for differentV
s (ε
0
=
0.03, A
0
/
h
=
1, and L
/
h
=
10).Figure12 presents variation of the nonlinear natural frequency with the actuation temperature of SMA fibers for the composite beams with different ε
0. The results show that there is an obvious change in the shapes of nonlinear natural frequency versus temperature curves as the initial strain of SMA wire is increased.Figure 12
Variation of the nonlinear natural frequency with the actuation temperature for differentε
0 (V
s
=
0.005, A
0
/
h
=
1, and L
/
h
=
10).Figure13 presents variation of the nonlinear natural frequency with the actuation temperature of SMA fibers for the composite beams with different A
0. The increase of free vibration amplitude is accompanied by the shift of these hysteresis loops of nonlinear natural frequency versus temperature towards higher nonlinear natural frequency. It seems that the hysteresis effect is more significant for linear vibration beam (A
0
=
0), in comparison with nonlinear vibration beams (A
0
≠
0).Figure 13
Variation of the nonlinear natural frequency with the actuation temperature for differentA
0 (ε
0
=
0.03, V
s
=
0.005, and L
/
h
=
10).Figures14 and 15 present the variation of amplitudes A
- and B
- with excited frequency, respectively. Also the effect of the volume fraction of SMA fibers is shown in these figures. The results show that the increase of V
s leads to the shift of steady-state responses curves towards higher excited frequency.Figure 14
AmplitudeA
- versus frequency responses of the composite beams in the phase transformation state from martensite to austenite under the excitations (T = 60°C, ε
0
=
0.008, q
0
=
10 N, and L
/
h
=
10).Figure 15
AmplitudeB
- versus frequency responses of the composite beams in the phase transformation state from martensite to austenite under the excitations for different V
s (T = 60°C, ε
0
=
0.008, q
0
=
10 N, and L
/
h
=
10).Figures16 and 17 present the variation of amplitudes A
- and B
- with excited frequency, respectively. The effect of ε
0 is also considered. It can be seen that the increase of ε
0 leads to the shift of steady-state responses curves towards higher excited frequency.Figure 16
AmplitudeA
- versus frequency responses of the composite beams in the phase transformation state from martensite to austenite under the excitations for different ε
0 (T = 60°C, V
s
=
0.005, q
0
=
10 N, and L
/
h
=
10).Figure 17
AmplitudeB
- versus frequency responses of the composite beams in the phase transformation state from martensite to austenite under the excitations for different ε
0 (T = 60°C, V
s
=
0.005, q
0
=
10 N, and L
/
h
=
10).Figures18 and 19 present the variation of amplitudes A
- and B
- with excited frequency, respectively, for different T. As can be clearly seen in the figure, the steady-state responses curves shift towards higher excited frequency as T increases.Figure 18
AmplitudeA
- versus frequency responses of the composite beams in the phase transformation state from Martensite to Austenite under the excitations for different T (ε
0
=
0.036, V
s
=
0.005, q
0
=
10 N, L
/
h
=
10).Figure 19
AmplitudeB
- versus frequency responses of the composite beams in the phase transformation state from martensite to austenite under the excitations for different T (ε
0
=
0.036, V
s
=
0.005, q
0
=
10 N, and L
/
h
=
10).


## 4. Conclusions

Large amplitude free and forced vibration of the composite beams embedded with SMA fibers are presented. The presented model was used to predict the nonlinear natural frequencies and steady-state forced responses. Emphasis is placed on the study of the effects of shear deformation and SMA activation on the nonlinear dynamical behavior. The effect of shear deformation is modeled based on the first-order shear deformation beam theory. The recovery stress in the SMA fibers is found by employing thermomechanical constitutive equation of SMA proposed by Brinson. The von Kármán type nonlinear strain-displacement equation and Hamilton’s principle are used to derive the equations of motion for the composite beams embedded with SMA fibers. Using an analytical method based on the Galerkin method, the nonlinear governing equations of motion are solved. The closed-form solution is obtained for nonlinear free vibration and forced vibration analysis of the composite beams with SMA fibers. From the present analysis and the numerical results, the following main conclusions can be obtained:(1)
Using the first-order shear deformation theory, the nonlinear natural frequency is found to be much lower than its value predicted by the classical beam theory. Thus, the nonlinear natural frequency predicted by the classical beam theory is overestimated. However, the amplitude of forced response is underestimated based on the classical beam theory. The effect of the shear deformation may be neglected if the value ofL
/
h is about 50.
(2)
SMA fibers’ activation can significantly increase the nonlinear natural frequency through SMA phase transformation.
(3)
The volume fraction and the actuation temperature of SMA fibers affect the actuation performance of SMA significantly. There is an obvious increase in the nonlinear natural frequency as the SMA fibers’ fraction or actuation temperature is increased. In comparison with these two parameters, the initial strain of SMA fibers appears to have marginal effect on the nonlinear vibration behavior of the composite beams.



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*Source: 1056087-2016-08-03.xml*