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Acoustical Modeling of Laminated Composite Cylindrical Double-Walled Shell Lined with Porous Materials

Written By

K. Daneshjou, H. Ramezani and R. Talebitooti

Submitted: December 10th, 2011 Published: October 24th, 2012

DOI: 10.5772/48646

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1. Introduction

Although the researchers have done many efforts to perform the numerical model such as FEM (Finite Elements Method) to investigate the wave prorogation through the shells, the analytical vibro-acoustic modeling of the composite shells is unavoidable because of the accuracy of the model in a broadband frequency. Bolton et. al. [1] investigated sound transmission through sandwich structures lined with porous materials and following Lee et. al. [2] proposed a simplified method to analyze curved sandwich structures. Daneshjou et. al. [3-5] studied an exact solution to estimate the transmission loss of orthotropic and laminated composite cylindrical shells with considering all three displacements of the shell. Recently the authors [6] have presented an exact solution of free harmonic wave propagation in a double-walled laminated composite cylindrical shell whose walls sandwich a layer of porous material using an approximate method. This investigation is focused on sound transmission through the sandwich structure, which includes the porous material core between the two laminated composite cylindrical shells to predict the reliable results for all structures used foam as an acoustic treatment.

Wave propagation through a composite cylindrical shell lined with porous materials is investigated, based on classical laminated theory. The porous material is completely modeled using elastic frame. The vibro-acoustic equations of the shell are derived considering both the shell vibration equations and boundary conditions on interfaces. These coupled equations are solved simultaneously to calculate the Transmission Loss (TL). Moreover, the results are verified with a special case where the porosity approaches zero. Finally, the numerical results are illustrated to properly study the geometrical and physical properties of composite and porous material. In addition, the effects of the stacking sequence of composite shells and fiber directions are properly studied.

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2. Propagation of sound in porous media

If the porous material is assumed a homogeneous aggregate of the elastic frame and the fluid trapped in pores, its acoustic behavior can be considered by the following two wave equations (See Eq. (22) and Eq. (25) of [1]):

4es+A12es+A2es=0E1
2ϖ+ξt2ϖ=0E2

Eqs. (1) and (2) determine 2 elastic longitudinal waves and 1 rotational wave, respectively. In Eqs. (1) and (2) is the vector differential operator, es=.u¯is the solid volumetric strain, u¯is the displacement vector of the solid, ϖ=×u¯is the rotational strain in the solid phase, A1=ω2(φρ22+μρ112χρ12)/(φμχ2), A2=ω4(ρ22ρ11(ρ12)2)/(φμχ2), and ξt is the wave number of the shear wave (See Eq. 10).ρ11, ρ12and ρ22 are equivalent masses given by:

ρ11=ρ1+ρajσrϕ2(1ω+4jα2κvρ0σr2Λ2ϕ2)E3
ρ12=ρa+jσrϕ2(1ω+4jα2κvρ0σr2Λ2ϕ2)E4
ρ22=ϕρ0+ρajσrϕ2(1ω+4jα2κvρ0σr2Λ2ϕ2)E5

where j is the imaginary unitj2=1. ρ1and ρ0 are the densities of the solid and fluid parts of the porous material. Moreover, parametersα, κv, Λ, σr, ϕand ω are tortuosity, air viscosity, viscous characteristic length, flow resistivity, porosity, and angular frequency, respectively.χ, φand μ represent material properties:χ=(1ϕ)G, μ=ϕG, φ=A+2δ, δ=E/2(1+ν)andA=νE/(1+ν)(12ν). Eand v are the in vacuo Young’s modulus and Poisson’s ratio of the bulk solid phase, respectively. Assuming that pores are shaped in cylindrical form, an expression for G is:

G=ρ0c22{1+[(ς1)ϕσr/NPr0.52jωρ0α][J1(2NPr0.52ωρ0αj/ϕσr)J0(2NPr0.52ωρ0αj/ϕσr)]}1E6

where ς is the ratio of specific heats, c2is the speed of sound in the fluid phase of porous materials, NPrrepresents the Prandtl number, and J0 and J1 are Bessel functions of the first kind, zero and first order, respectively. ρais the inertial coupling term:

ρa=ϕρ0(α1)E7

The complex wave numbers of the two compression (longitudinal) waves, ξαand ξβ are:

ξα2=ω22(φμχ2)(φρ22+μρ112χρ12+)E8
ξβ2=ω22(φμχ2)(φρ22+μρ112χρ12)E9

where

=(φρ22+μρ112χρ12)24(φμχ2)(ρ22ρ11ρ122)E10

and the wave number of the shear (rotational) wave is:

ξt2=ω2δ(ρ22ρ11ρ122ρ22)E11
δis the shear modulus of the porous material.
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3. Simplified method

As the full method is too complicated to model the porous layer in the curved sandwich structures, thus a simplified method is expanded for this category of structures [2]. The foundation of this approximate method considers the strongest wave between those ones. It includes two steps. At the first step a flat double laminated composite with infinite extents with the same cross sectional construction is considered using the full method. Then, only the strongest wave number is chosen from the results and the material is modeled using the wave number and its corresponding equivalent density. Thus, the material is modeled as an equivalent fluid.

The strain energy which is related to the displacement in the solid and fluid phases can be defined for each wave component. The energy terms can be represented as follows; E1sand E1f for the airborne wave, E3sand E3f for the frame wave and E5s for the shear wave, which the subscripts s and f represent the solid and fluid phase, respectively. For each new problem, comparing the ratios of the energy carried by the frame wave and the shear wave to the airborne wave in the fluid and solid phases: i.e., E1fE1f, E1sE1f, E3fE1f, E3sE1f, E5sE1fshow the strongest wave component in the entire frequency range.

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4. Model specification

Figure 1 shows a schematic of the cylindrical double shell of infinite length subjected to a plane wave with an incidence angleγ. The radii and the thicknesses of the shells are Ri,e and hi,e in which the subscripts i and e represent the inner and outer shells. A concentric layer of porous material is installed between the shells. The acoustic media in the outside and the inside of the shell are represented by density and speed of sound: (s1,c1)outside and (s3,c3) inside.

Figure 1.

Schematic diagram of the double-walled cylindrical composite shell lined with porous materials

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5. Applying full method to two-dimensional problem

For a two-dimensional problem as shown in the xy plane of Fig. 2, the potential of the incident wave can be expressed as [1]:

i=ej(ξxx+ξ1yy)E12

whereξx=ξ1sinγ, ξ1y=ξ1cosγ, ξ1=ω/c1, c1is the speed of sound in incident Medium, γis the angle of incidence.

Figure 2.

Illustration of wave propagation in the porous layer

Three kinds of the waves propagate in porous material, therefore six traveling waves, which have the same trace wave numbers, are induced by an oblique incident wave in a finite depth layer of porous material, as shown in Fig. 2. The x and y direction components of the displacements and stresses of the solid and fluid phases were derived by Bolton et. al. [1]. The displacements in the solid phase are:

u^x=jξxejξxx[D1ξα2ejξαyy+D2ξα2ejξαyy+D3ξβ2ejξβyy+D4ξβ2ejξβyy]E13
jξtyξt2ejξxx[D5ejξtyyD6ejξtyy]E14
u^y=jejξxx[ξαyξα2D1ejξαyyξαyξα2D2ejξαyy+ξβyξβ2D3ejξβyyξβyξβ2D4ejξβyy]E15
+jξxξt2ejξxx[D5ejξtyy+D6ejξtyy]E16

The displacements in the fluid phase are:

U^x=jξxejξxx[b1D1ξα2ejξαyy+b1D2ξα2ejξαyy+b2D3ξβ2ejξβyy+b2D4ξβ2ejξβyy]E17
jgξtyξt2ejξxx[D5ejξtyyD6ejξtyy]E18
U^y=jejξxx[b1ξαyξα2D1ejξαyyb1ξαyξα2D2ejξαyy+b1ξβyξβ2D3ejξβyyb1ξβyξβ2D4ejξβyy]E19
+jgξxξt2ejξxx[D5ejξtyy+D6ejξtyy]E20

The stresses in the solid phase are:

σ^ys=ejξxx[(2δξαy2ξα2+A+b1χ)D1ejξαyy+(2δξαy2ξα2+A+b1χ)D2ejξαyy+(2δξβy2ξβ2+A+b2χ)D3ejξβyy+(2δξβy2ξβ2+A+b2χ)D4ejξβyy+2δξxξtyξt2(D5ejξtyyD6ejξtyy)]E21
τ^xy=ejξxxδ[2ξxξαyξα2(D1ejξαyyD2ejξαyy)+2ξxξβyξβ2(D3ejξβyyD4ejξβyy)+(ξx2ξty2)ξt2(D5ejξtyy+D6ejξtyy)]E22

The stresses in the fluid phase are:

σ^f=ejξxx[(χ+b1μ)D1ejξαyy+(χ+b1μ)D2ejξαyy+(χ+b2μ)D3ejξβyy+(χ+b2μ)D4ejξβyy]E23

whereξαy=ξα2ξx2, ξβy=ξβ2ξx2, ξty=ξt2ξx2, j=1, b1=(ρ11μρ12χ)(ρ22χρ12μ)(ϕμχ2)[ω2(ρ22χρ12μ)]ξα2, b2=(ρ11μρ12χ)(ρ22χρ12μ)(ϕμχ2)[ω2(ρ22χρ12μ)]ξβ2, andg=ρ12ρ22.

These complex relations and six constants D1D6 have to be determined by applying boundary conditions (BCs). When the elastic porous material is bonded directly to a panel, there exist six BCs. Also, the transverse displacement and in-plane displacement at the neutral axis can be followed as [1]:

wt(x,t)=Wt(x)ejωtandwp(x,t)=Wp(x)ejωtE24
Wt(x)and Wp(x) are transverse and in-plane displacements. Four BCs are obtained from the interface compatibility:
Vy=jωWt(x),u^y=Wt(x),U^y=Wt(x)andu^x=Wp(x)(/+)hp2dWt(x)dxE25

where hP is the panel thickness and Vy is the normal acoustic particle velocity. Two BCs are obtained from the equations of motion, followed as:

(+/)p^amb(/+)qPjξxhP2τ^xy=(D^ξx4ω2I)WtB^ξx3jWPE26
(+/)τ^yx=(A^ξx2ω2I)WPB^ξx3jWtE27
p^ambis the acoustic pressures applied on the panel, qPis the normal force per unit panel area exerted on the panel by the elastic porous materialqP=σ^ysσ^f. The Inertia term, I, and the extensional, coupling and bending stiffness, A^, B^and D^ are [8]:
I=l=1Lρ(l)(ylyl1)E28
A^=l=1LQ^(l)(ylyl1)E29
B^=12l=1LQ^(l)(yl2yl12)E30
D^=13l=1LQ^(l)(yl3yl13)E31

where ρ(l) is the mass density of the lth layer of the shell per unit midsurface area and yl is the distance from the midsurface to the surface of the lth layer having the farthest y coordinate. The material constant Q^(l) is defined as Q^(l)=E1(l)1v12v21 where E1(l) is module of elasticity in the direction 1, and v12(l) and v21(l) are Poisson’s ratios in the directions 1 and 2 of the lth ply, respectively. The fiber coordinates of ply is described, as 1 and 2, where direction 1 is parallel to the fibers and 2 is perpendicular to them. In BCs, the first signs are appropriate when the porous material is attached to the positive y facing surface of the panel, and the second signs when the porous material is attached to the negative y facing surface.

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6. Prediction of ratios of the energy

The energy related to the waves in the fluid phase and solid phase are descript as follows [2].

The airborne wave:

E1f=12[ϕ.|(χ+b1μ)b1ξαy2ξα2D12|]E32
E1s=12[(1ϕ).|(2δξαy2ξα2+A+b1χ)ξαy2ξα2D12|]E33

And the frame wave:

E3f=12[ϕ.|(χ+b2μ)b2ξβy2ξβ2D32|]E34
E3s=12[(1ϕ).|(2δξβy2ξβ2+A+b2χ)ξβy2ξβ2D32|]E35
E5s=12[(1ϕ).|2δ(ξty2ξt2)2D52|]E36

where the subscripts f and s represents the fluid and solid phases, respectively.

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7. Formulation of the problem

In the external space, the wave equation becomes [3]:

c12(pI+p1R)+2(pI+p1R)t2=0E37

where pI and p1R are the acoustic pressures of the incident and reflected waves and 2 is the Laplacian operator in the cylindrical coordinate system, and c1 is the speed of sound of outside medium. The wave equations in the fluid phase of the porous layer and internal space are the same as Eq. (33) with different variable names.

The shell motions are described by classic theory, fully considering the displacements in all three directions. Let the axial coordinate bez, the circumferential direction be θ and the normal direction to the middle surface of the shell ber. Equations of motion in the axial, circumferential and radial directions of a laminated composite thin cylindrical shell in cylindrical coordinate can be written as below [7]:

Nαz+1Ri,eNαβθ+qαi,e=Ii,e2ui,e0t2E38
Nαβz+1Ri,eNβθ+1Ri,e[Mαβz+1Ri,eMββ]+qβi,e=Ii,e2vi,e0t2E39
2Mαz2NβRi,e+21Ri,e2Mαβθz+1Ri,e22Mβθ2+qzi,e=Ii,e2wi,e0t2E40

In which the subscripts i and e represent the inner and outer shells.qα, qβ, and qz are external pressure components.u0, v0, and w0 are the displacements of the shell at the neutral surface in the axial, circumferential, and radial directions respectively. The inertia terms are followed as:

I=I1+I2(1R)where[I1,I2]=l=1Lyl1ylρ(l)[1,z]dzE41
Ris cylindrical radius. Mid-surface strain and curvature can be expressed as:ε0α=u0z,
ε0β=1R{v0θ+w0}andγ0αβ=v0z+1Ru0θE42
κα=2w0z2,κβ=1R2{v0θ2w0θ2}andκ=1R{v0z22w0zθ}E43

The forces and moments are:

[NαNβNαβMαMβMαβ]=[A11A12A16B11B12B16A21A22A26B21B22B26A61A62A66B61B62B66B11B12B16D11D12D16B21B22B26D21D22D26B61B62B66D61D62D66][ε0αε0βγ0αβκακβκ]E44

where the extensional, coupling and bending stiffness, Ap˜q˜, Bp˜q˜and Dp˜q˜ are:

Ap˜q˜=l=1LQp˜q˜(l)(ylyl1)p˜,q˜=1,2,3E45
Bp˜q˜=12l=1LQp˜q˜(l)(yl2yl12)p˜,q˜=1,2,3E46
Dp˜q˜=13l=1LQp˜q˜(l)(yl3yl13)p˜,q˜=1,2,3E47
Qp˜q˜(l), material constant, is the function of physical properties of each ply. The displacement components of the inner and outer shell at an arbitrary distance r from the midsurface along the axial, the circumferential and the radial directions are [8]:
ue0=n=0une0cos(nθ)exp[j(ωtξ1zz)]E48
ve0=n=0vne0sin(nθ)exp[j(ωtξ1zz)]E49
we0=n=0wne0cos(nθ)exp[j(ωtξ1zz)]E50
ui0=n=0uni0cos(nθ)exp[j(ωtξ3zz)]E51
vi0=n=0vni0sin(nθ)exp[j(ωtξ3zz)]E52
wi0=n=0wni0cos(nθ)exp[j(ωtξ3zz)]E53

In Eqs. (44 - 46)ξ1, wave number in the external medium, is defined asξ1=ωc1, ξ1z=ξ1sinγ, ξ1r=ξ1cosγand in Eqs. (47 - 49)ξ3, wave number in the internal cavity, is expressed asξ3=ωc3, ξ3z=ξ1z,ξ3r=ξ32ξ3z2.

The boundary conditions at the two interfaces between the shells and fluid are [2]:

r(pI+p1R)=s12we0t2@r=ReE54
r(p2T+p2R)=s22we0t2@r=ReE55
r(p2T+p2R)=s22wi0t2@r=RiE56
r(p3T)=s32wi0t2@r=RiE57
s1and s3 are densities of outside and inside acoustic media, respectively. s2is the equivalent density of the porous material and can be obtained from the Simplified method as suggested in [2]. The harmonic plane incident wave pI can be expressed in cylindrical coordinates as [2]:
pI(r,z,θ,t)=p0ej(ωtξ1zz)n=0εn(j)nJn(ξ1rr)cos(nθ)E58

where p0 is the amplitude of the incident wave, n=0,1,2,3,...indicates the circumferential mode number, εn=1for n=0 and 2 forn=1,2,3,..., and Jn is the Bessel function of the first kind of ordern.

Considering the circular cylindrical geometry, the pressures are expanded as:

p1R(r,z,θ,t)=ej(ωtξ1zz)n=0pn1RHn2(ξ1rr)cos(nθ)E59
p2T(r,z,θ,t)=ej(ωtξ2zz)n=0pn2THn1(ξ2rr)cos(nθ)E60
p2R(r,z,θ,t)=ej(ωtξ2zz)n=0pn2RHn2(ξ2rr)cos(nθ)E61
p3T(r,z,θ,t)=ej(ωtξ3zz)n=0pn3THn1(ξ3rr)cos(nθ)E62

where Hn1 and Hn2 are the Hankel functions of the first and second kind of ordern, ξ2z=ξ3z=ξ1z, andξ2r=ξ22ξz2. The wave number, ξ2, in the porous core can be obtained from the simplified method as suggested in [2].

Substitution of the expressions in the displacements of the shell (Eq. (44)-Eq.(49)) and the acoustic pressures (Eq. (54)-Eq.(58)) equations into six shell equations (Eq. (34)-Eq.(36)) and four boundary conditions (Eq. (50)-Eq.(53)) yields ten equations, which can be decoupled for each mode if the orthogonality between the trigonometric functions is utilized. These ten equations can be sorted into a form of a matrix equation as follow:

[h]{uni0,vni0,wni0,une0,vne0,wne0,pn1R,pn2T,pn2R,pn3T}T={λ}E63

where [h] is a 10×10 matrix with components given in Appendix and {λ} is:

{λ}={0,0,0,0,0,p0εn(j)nJn(ξ1rRe)ξ1r,p0εn(j)ndJn(ξ1rRe)drξ1r,0,0,0}TE64

The ten unknown coefficientspn1R, pn2T, pn2R, pn3T, une0, vne0, wne0, uni0, vni0and wni0 are obtained in terms of p0 with solving Eq. (59) for each moden, which then can be substituted back into Eqs. (44) to (49) and (54) to (58) to find the displacements of the shell and the acoustic pressures in series forms.

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8. Calculation of transmission losses (TLs)

The transmission coefficient, τ(γ), is the ratio of the amplitudes of the incident and transmitted waves. τ(γ)is obviously a function of the incidence angle γ defined by [2]:

τ(γ)=n=0Re{pn3THn1(ξ3rRi)(jωw1n0)}s1c1πRiεnRecos(γ)p02E65

where εn=1 for n=0 and εn=2 forn=1,2,3,.... Re{}and the superscript represents the real part and the complex conjugate of the argument.

To consider the random incidences, τ(γ)can be averaged according to the Paris formula [9]:

τ¯=20γmτ(γ)sinγcosγdγE66

where γm is the maximum incident angle. Integration of Eq. (62) is conducted numerically by Simpson’s rule. Finally, the average TLs is obtained as:

TLavg=10log1τ¯E67

In the following, the averaged TLs of the structure is calculated in terms of the 1/3 octave band for random incidences.

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9. Convergence algorithm

Eqs. (44) to (49) and (54) to (58) are obtained in series form. Therefore, enough numbers of modes should be included in the analysis to make the solution converge. Therefore, an iterative procedure is constructed in each frequency, considering the maximum iteration number. Unless the convergence condition is met, it iterates again. When the TLs calculated at two successive calculations are within a pre-set error bound, the solution is considered to have converged. An algorithm for the calculation of TLs at each frequency is followed as:

REPEAT

TLn=10log1τ¯E68
Setn=n+1E69
UNTIL|TLn+1||TLn|<106E70
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10. Numerical results

Parametric numerical studies of transmission loss (TLs) are conducted for a double-walled composite laminated cylindrical shell lined with porous material specified as follows, considering 1/3 octave band frequency. Table 1 presents the geometrical and environmental properties of a sandwich cylindrical structure. Each layer of the laminated composite shells are made of graphite/epoxy, see Table 2. The plies were arranged in a [0,45,90,45,0]s pattern.

The results are verified by those investigated by the authors’ previous work for an especial case in which the porous material properties go into fluid phase (In other world, the porosity is close to 1). The comparison of these results shown in Fig. 3, indicates a good agreement.

The calculated transmission loss for the laminated composite shell is compared with those of other authors for a special case of isotropic materials. In other word, in this model the mechanical properties of the lamina in all directions are chosen the same as an isotropic material such as Aluminum, and then the fiber angles are approached into zero. Fig. 4 compares the TL values of the special case of laminated composite walls obtained from present model and those of aluminum walls from Lee’s study [2]. The results show an excellent agreement.

We are going to verify the model in behavior comparing the results of cylindrical shell in a case where the radius of the cylindrical shell becomes large or the curvature becomes negligible with the results of the flat plate done by Bolton [1] (See Fig. 5). It should be also noted that both structures sandwich a porous layer and have the same thickness. Although it is not expected to achieve the same results as the derivation of the shell equations is quite different comparing with derivation of plate equations, however, the comparison between the two curves indicate that they behave in a same trend in the broadband frequencies.

AmbientOuter ShellPorous CoreInner ShellCavity
MaterialAirCompositePorous MaterialCompositeAir
Density (kg/m3)1.21---0.94
Speed of Sound (m/s)343---389
Radius (mm)-172.5-150-
Thickness (mm)-2203-
Bulk Density of Solid Phase* (kg/m3)--30--
Bulk Young’s Modulus* (kPa)--800--
Bulk Poisson’s Ratio (-)--0.4--
Flow Resistivity (MKs)--25000--
Tortuosity (-)--7.8--
Porosity (-)--0.9--
Loss Factor (-)--0.265--

Table 1.

Geometrical and environmental properties [2]

Graphite/epoxyGlass/epoxy
Axial Modulus (GPa)137.938.6
Circumferential Modulus (GPa)8.968.2
Shear Modulus (GPa)7.14.2
Density (kg/m3)16001900
Major Poisson’s Ratio (-)0.30.26

Table 2.

Orthotropic properties [3]

Figure 6 indicates that whenever the radius of the shell descends, the TL of the shell is ascending in low frequency region. It is due to the fact that the flexural rigidity of the cylinder will be increased with reduction of shells radii. In addition, decreasing the radius of the shell leads to weight reduction and then in high frequency especially in Mass-controlled region the power transmission into the structure increases.

Figure 7 shows the effect of the composite material on TL. Materials chosen for the comparison are graphite/epoxy and glass/epoxy (Table 2). The figure shows that material must be chosen properly to enhance TL at Stiffness-control zone. The results represent a desirable level of TL at Stiffness-control zone (Lower frequencies) for graphite/epoxy. It is readily seen that, in higher frequency, as a result of density of materials, the TL curves are ascending. Therefore, the TL of glass/epoxy is of the highest condition in the Mass-controlled region.

It is well anticipated that increase of porous layer thickness leads to increase of TL. As illustrated in Fig. 8, a considerable increase due to thickening the porous layer is obtained. As it is well obvious from this figure, the weight increase of about 12% (hc=60mm) and 25% (hc=100mm), the averaged TL values are properly increased about 35% and 60%, respectively in broadband frequency. It is a very interesting result that can encourage engineers to use these structures in industries.

Figure 9 shows a comparison between the transmission loss for a ten-layered composite shell and an aluminum shell with the same radius and thickness. Since, the composite shell is stiffer than the aluminum one, its TL is upper than that of aluminum shell in the Stiffness-controlled region. However, as a result of lower density of composite shell, it does not appear to be effective as an aluminum shell in Mass-controlled region.

The effect of stacking sequence is shown in Fig. 10. Two patterns [0,90,0,90,0]s and [90,0,90,0,90]s are defined to designate stacking sequence of plies. The arrangements of layers are so effective on TLs curve, especially on Stiffness-controlled region. However, no clear discrepancy is depicted in Mass-controlled region.

Figure 3.

Comparison of cylindrical double-walled shell with and without foam where porosity close to 1

Figure 4.

Comparison of cylindrical isotropic double-walled shell with special case of laminated composite double-walled shell (Ri=150mm, Re=200mm, hi=3mm, he=2mm, and hc=47.5mm)

Figure 5.

Comparison of an isotropic cylindrical double-walled shell with a negligible curvature and a double-panel structure

Figure 6.

Comparison of a cylindrical double-walled shell lined with porous material with different inner shell’s radius

Figure 7.

Comparison of a TL curves for ten-layer laminated composite shell with different material

Figure 8.

Comparison of a cylindrical double-walled shell lined with porous material with different core thickness

Figure 9.

Comparison between Aluminum and ten-layer laminated composite shell

Figure 10.

TL curves for the ten-layered composite shell with respect to stacking sequence

11. Conclusions

Transmission losses (TLs) of double-walled composite laminated shells sandwiching a layer of porous material were calculated. It is also considered the acoustic-structural coupling effect as well as the effect of the multi-waves in the porous layer. In order to make the problem solvable, one dominant wave was used to model the porous layer. In general the comparisons indicated the benefits of porous materials. Also, a considerable increase due to thickening the porous layer was obtained. For example, the weight increase of about 12% and 25% may respectively lead to an increase of 35% or 60% in amount of averaged TL values in broadband frequency. In addition, it was shown that increasing the axial modulus of plies made the TL be increased in low frequency range. Moreover, the comparison of double-walled shell with a gap and the one sandwiched with porous materials (where the porosity is close to 1) indicated a good agreement. Eventually the arrangement of layers in laminated composite can be so effective in Stiffness-controlled region. Therefore, optimizing the arrangement of layers can be useful in future study.

Nomenclature

A1,A2 Physical and geometrical factors

Ap˜q˜, Bp˜q˜, Dp˜q˜, A^, B^,D^ Stiffness coefficients

D1D6Wave equations constants

EBulk Young’s modulus

E1(l)Module of elasticity in the direction 1 of the lth ply

E1f,E1s ,E3s ,E3f ,E5s The strain energy associated with the displacement in the solid and fluid phases

JnBessel function of the first kind of order n

Hn1,Hn2 Hankel functions of the first and second kind of order n

I, I, I1,I2 Inertia terms

NPrPrandtl number

Nα, Nβ, Nαβ, Mα, Mβ,Mαβ Forces and Moments

Q^(l),Qp˜q˜(l) Material constant

Ri,ReRadii of inner and outer shell

VyNormal acoustic particle velocity

WI,WTThe incident and transmitted power flow per unit length of the shell

Wt(x),Wp(x) Transverse and in-plane displacements

c1,c3Speed of sound in external and cavity media

c2Speed of sound in the fluid phase of porous materials

esSolid volumetric strain

hi,heShell wall thickness of inner and outer shell

hPThickness of Panel

nCircumferential mode number

qα, qβ,qz External pressure components

p^ambAcoustic pressures applied on the panel

p0Pressure amplitude of the incident wave

p1R,p2T ,p2R ,p3T Incident, Reflected and transmitted pressures in external, porous layer and cavity media

s1,s2 ,s3 Density of external medium, equivalent density of the porous material and internal medium

u0,v0 ,w0 Displacements of the shell in the axial, circumferential, and radial directions

u¯Displacement vector of the solid

ylDistance from the midsurface to the surface of the lth layer having the farthest y coordinate

z,θ ,r Cylindrical coordinate

αTortuosity

εnNeumann factor

κvAir viscosity

δShear modulus of the porous material

ρ0Densities of the fluid parts of the porous material

ρ(l)Mass density of the lth layer of the shell per unit midsurface area

ρ1Bulk density of the solid phase

ρaInertial coupling term

ρ11,ρ12 ,ρ22 Equivalent masses

ΛViscous characteristic length

σrFlow resistivity

ϕPorosity

2Laplacian operator in the cylindrical coordinate system

γAngle of incidence

γmMaximum incident angle

χ,φ ,μ Material properties

ωAngular frequency

ϖRotational strain in the solid phase

ξ1,ξ3 Wave number in external and cavity media

ξα,ξβ ,ξt Complex wave numbers of the two compression and one shear waves

iPotential of the incident wave, 2D dimension

u^x, u^y, U^x,U^y Displacement components in the solid and fluid phases, 2D dimension

σ^ys, τ^xy,σ^f Stresses in the solid and fluid phases, 2D dimension

v12(l),v21(l) Poisson’s ratios in the directions 1 and 2 of the lth ply, 2D dimension

ν^Bulk Poisson’s ratio

η^Loss factor

ςRatio of specific heats

Re{},Real part and the complex conjugate

Appendix

The non-zero components of the matrix [h] appearing in equation (59) are followed as:

1,1=A11(jξz)2+2A161Ri(jξz)(n)+A661Ri2(n2)Iiω2E72
1,2=A121Ri(jξz)(n)+A16(jξz)2+B121Ri2(jξz)(n)+B16(jξz)2+A621Ri2(n2)+A661Ri(jξz)(n)+B621Ri3(n2)+B661Ri2(jξz)(n)E73
1,3=A121Ri(jξz)B11(jξz)3B121Ri2(jξz)(n2)3B161Ri(jξz)2(n)+A621Ri2(n)B621Ri3(n3)2B661Ri2(n2)(jξz)E74
2,1=A121Ri(jξz)(n)+A16(jξz)2+B121Ri2(jξz)(n)+B161Ri(jξz)2+A621Ri2(n2)+A661Ri(jξz)(n)+B621Ri3(n2)+B661Ri2(jξz)(n)E75
2,2=A221Ri2(n2)+2A261Ri(jξz)(n)+2B221Ri3(n2)+4B261Ri2(jξz)(n)+A66(jξz)2+2B661Ri(jξz)2+D221Ri4(n2)+2D231Ri3(jξz)(n)+D331Ri2(jξz)2Iiω2E76
2,3=A221Ri2(n)B121Ri(n)(jξz)2B221Ri3(n3)3B231Ri2(jξz)(n2)+A621Ri(jξz)+B61(jξz)32B661Ri(n)(jξz)2+B221Ri3(n)D211Ri2(jξz)2(n)D221Ri4(n3)3D231Ri3(jξz)(n2)+B321Ri2(jξz)D611Ri(jξz)32D331Ri2(jξz)2(n)E77
3,1=A121Ri(jξz)B11(jξz)3B121Ri2(jξz)(n2)3B161Ri(jξz)2(n)+A621Ri2(n)+B621Ri3(n3)2B661Ri2(n2)(jξz)E78
3,2=A221Ri2(n)B121Ri(n)(jξz)2B221Ri3(n3)3B231Ri2(jξz)(n2)+A621Ri(jξz)+B61(jξz)32B661Ri(n)(jξz)2+B221Ri3(n)D211Ri2(jξz)2(n)D221Ri4(n3)3D231Ri3(jξz)(n2)+B321Ri2(jξz)D611Ri(jξz)32D331Ri2(jξz)2(n)E79
3,3=A221Ri22B211Ri(jξz)22B221Ri3(n2)4B231Ri2(jξz)(n)+D11(jξz)42D121Ri2(n2)(jξz)2+4D161Ri(jξz)3(n)+4D621Ri3(jξz)(n3)+4D331Ri2(jξz)2(n2)+D221Ri4(n4)Iiω2E80
3,8=Hn1(ξ2rRi),3,9=Hn2(ξ2rRi),3,10=Hn1(ξ3rRi)E81
4,4=A11(jξz)2+2A161Re(jξz)(n)+A661Re2(n2)Ieω2E82
4,5=A121Re(jξz)(n)+A16(jξz)2+B121Re2(jξz)(n)+B161Re(jξz)2+A621Re2(n2)+A661Re(jξz)(n)+B621Re3(n2)+B661Re2(jξz)(n)E83
4,6=A121Re(jξz)B11(jξz)3B121Re2(jξz)(n2)3B161Re(jξz)2(n)+A621Re2(n)+B621Re3(n3)2B661Re2(n2)(jξz)E84
5,4=A121Re(jξz)(n)+A16(jξz)2+B121Re2(jξz)(n)+B161Re(jξz)2+A621Re2(n2)+A661Re(jξz)(n)+B621Re3(n2)+B661Re2(jξz)(n)E85
5,5=A221Re2(n2)+2A261Re(jξz)(n)+2B221Re3(n2)+4B261Re2(jξz)(n)+A66(jξz)2+2B661Re(jξz)2+D221Re4(n2)+2D231Re3(jξz)(n)+D331Re2(jξz)2Ieω2E86
5,6=A221Re2(n)B121Re(n)(jξz)2B221Re3(n3)3B231Re2(jξz)(n2)+A621Re(jξz)+B61(jξz)32B661Re(n)(jξz)2+B221Re3(n)D211Re2(jξz)2(n)D221Re4(n3)3D231Re3(jξz)(n2)+B321Re2(jξz)D611Re(jξz)32D331Re2(jξz)2(n)E87
6,4=A121Re(jξz)B11(jξz)3B121Re2(jξz)(n2)3B161Re(jξz)2(n)+A621Re2(n)+B621Re3(n3)2B661Re2(n2)(jξz)E88
6,5=A221Re2(n)B121Re(n)(jξz)2B221Re3(n3)3B231Re2(jξz)(n2)+A621Re(jξz)+B61(jξz)32B661Re(n)(jξz)2+B221Re3(n)D211Re2(jξz)2(n)D221Re4(n3)3D231Re3(jξz)(n2)+B321Re2(jξz)D611Re(jξz)32D331Re2(jξz)2(n)E89
6,6=A221Re22B211Re(jξz)22B221Re3(n2)4B231Re2(jξz)(n)+D11(jξz)42D121Re2(n2)(jξz)2+4D161Re(jξz)3(n)+4D621Re3(jξz)(n3)+4D331Re2(jξz)2(n2)+D221Re4(n4)Ieω2E90
6,7=Hn2(ξ1rRe),6,8=Hn1(ξ2rRe),6,9=Hn2(ξ2rRe),7,6=s1ω2E91
7,7=Hn2(ξ1rRe)ξ1r,8,6=s2ω2,8,8=Hn1(ξ2rRe)ξ2r,8,9=pn2RHn2(ξ2rRe)ξ2rE92
9,3=s2ω2,9,8=Hn1(ξ2rRi)ξ2r,9,9=Hn2(ξ2rRi)ξ2r,10,3=s3ω2,10,10=Hn1(ξ3rRi)ξ3rE93

Here:

()=ddr,ξz=ξ1z=ξ2z=ξ3z,ξ2r=ξ22ξz2.E94

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Written By

K. Daneshjou, H. Ramezani and R. Talebitooti

Submitted: December 10th, 2011 Published: October 24th, 2012