# Analysis of the Nonlinear Structural-Acoustic Resonant Frequencies of a Rectangular Tube with a Flexible End Using Harmonic Balance and Homotopy Perturbation Methods

Authors: Y. Y. Lee
Journal: Abstract and Applied Analysis
 (2012)

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## Abstract

The structural acoustic problem considered in this study is the nonlinear resonant frequencies of a rectangular tube with one open end, one flexible end, and four rigid side walls A multiacoustic single structural modal formulation is derived from two coupled partial differential equations which represent the large amplitude structural vibration of the flexible end and acoustic pressure induced within the tube. The results obtained from the harmonic balance and homotopy perturbation approaches verified each other. The effects of vibration amplitude, aspect ratio, the numbers of acoustic modes and harmonic terms, and so forth, on the first two resonant natural frequencies, are examined.


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## Body

## 1. Introduction

Over the past decades, many researchers worked on linear structural-acoustic research works (e.g., [1–7]) and nonlninear structural vibration problems (e.g., [8–15]), separately. The structural-acoustic problem of rectangular tube (or similar problems) has been studied for many years in various studies. So far, only few research works about structural-acoustics have adopted the assumption of large amplitude vibration [16–20]. Few classical solutions for nonlinear structural-acoustic problems have been developed to date, although there are many approaches available for solving nonlinear governing differential equation (e.g., [21–30]. In the study reported in this paper, the homotopy perturbation and harmonic balance methods are used and assessed. It is because these two methods were employed to determine the large amplitude free vibration of beams and nonlinear oscillators in previous studies and agreed well with the other published results [31]. The results obtained from these two methods verified each other. In finite element and other numerical approaches for solving the problems of nonlinear structural vibrations (e.g., [32–35]), it is necessary for setting a set of residual equations or global matrix equations and then solving them for the eigenvalue solutions. All these approaches require a significant effort as an eigenvalue problem. The present study uses the multiacoustic and single structural mode approach to develop the classical solutions which do not require a significant amount of computational effort and preprocessing inputs.


## 2. Theory

### 2.1. Governing Equations

In Figure1, the acoustic pressure within the rectangular tube induced by the flexible end is given by the following homogeneous wave equation [1]:
(2.1)∇2P-1Ca2∂2P∂τ2=0,
where P = the pressure within the tube; τ = time; Ca = sound speed.Figure 1
The rectangular tube with one open end, one flexible end, and four rigid side walls.The boundary conditions are given by(2.2a)∂P∂x=0,atx=0anda,(2.2b)∂P∂y=0,aty=0andb,(2.2c)P=0,atz=0,(2.2d)∂P∂z=-ρa∂2wl(t)∂τ2φ(x,y),atz=l,where wl(τ)=Acos(ωτ)=flexible plate vibration response; φ(x,y)=vibration mode shape=sin(π/a)sin(π/b); ρa=airdensity;A=displacement amplitude (or displacement at time=0); ω=vibration frequency.According to [1], the general multiacoustic mode solution of (2.1) is
(2.3)P=∑uU∑vV[Luvsinh(μuvz)+Nuvcosh(μuvz)]cos(uπxa)cos(vπyb)cos(ωτ),
where μuv=(uπ/a)2+(vπ/b)2-(ω/Ca)2;u and v=0,2,4,… are the acoustic mode numbers; U and V are the last acoustic mode numbers; Luv and Nuv are unknown coefficients to be determined by the boundary conditions.Applying the boundary condition (2.2c) to (2.3) gives
(2.4)Nuv=0.
Then applying the boundary condition (2.2d) to (2.3) gives
(2.5)∂P∂z=∑uU∑vVLuvμuvcosh(μuvl)cos(uπxa)cos(vπyb)cos(ωτ)atz=l∂P∂z=-ρa∂2Acos(ωτ)∂τ2φ(x,y)=ρaω2Acos(ωτ)φ(x,y)⇒Luv=ρaω2αuvαcosAμuvcosh(μuvl),
where αuv=∫0b∫0aφ(x,y)cos(uπx/a)cos(vπy/b)dxdy;
(2.6)αcos=∫0b∫0a[cos(uπxa)cos(vπyb)]2dxdy.
Therefore, the acoustic pressure and modal acoustic pressure force acting on the flexible end at z=l are given by(2.7a)Pl=ρaω2∑uU∑vVαuvαcostanh(μuvl)μuvcos(uπxa)cos(vπyb)Acos(ωτ),(2.7b)Fl=∫0b∫0aPlφ(x,y)dxdyαφ=ρaω2∑uU∑vVαuv2αcosαφtanh(μuvl)μuvAcos(ωτ),where αφ=∫0b∫0aφ(x,y)2dxdy.According to the approach from Chu and Herrmann [15], the governing equation for the large amplitude vibration of a flexible plate is given by(2.8a)ρd2wldτ2+ρωs2wl+βwl3=0,
where ρ = the panel surface density; ωs=Et2/12ρ(1-ν2)[(π/a)2+(π/b)2] = the fundamental linear resonant frequency of the plate; β=(Eh/12(1-ν2))(γ/a4) is the nonlinear stiffness coefficient that is due to the large amplitude vibration; E is the Young’s modulus of the plate; γ=3π4[((3/4)-(ν2/4))(1+r4)+νr2];r=a/b is the aspect ratio; ν is Poisson’s ratio; and t = the plate thickness.Consider the modal acoustic pressure in (2.7b) on the plate. Equation (2.8a) is modified and given by
(2.8b)ρd2wldτ2+ρωs2wl+βwl3=Fl.


### 2.2. Harmonic Balance Method

Consider the structural vibration response in terms of harmonic terms [20]:(2.9a)wl=∑hHAhcos(hωτ),
where Ah is the amplitude of the hth harmonic response; h=1,3,…H; and H is the last harmonic order number; A=∑hHAh.Then, the modal acoustic pressure force atz=l in (2.7b) is revised and also consists of higher harmonic terms. 								(2.9b)Fl(t)=ρa∑hH∑uU∑vV(hω)2αuv2αcosαφtanh(μuv,hl)μuv,hAhcos(hωτ),where μuv,h=(uπ/a)2+(vπ/b)2-(hω/Ca)2.Similarly, (2.8a) is revised and given by
(2.10)ρd2wldτ2+ρωs2wl+βwl3=ρa∑hH∑uU∑vV(hω)2αuv2αcosαφtanh(μuv,hl)μuv,hAhcos(hωτ)⇒-ρ(hω)2Ah+ρωs2Ah+βGh(A1,A3…AH)=ρa(hω)2∑uU∑vVαuv2αcosαφtanh(μuv,hl)μuv,hAh,
where Gh is a set of functions which contains A1,A3,…AH.IfH=1, then
(2.11)G1(A1)=34A13.
Consider the harmonic balance for H=1 and ignore the higher harmonic terms in (2.10). Then, the following equation is obtained:
(2.12)-ρ(ω)2A1+ρωs2A1+β34A13=ρa(ω)2∑uU∑vVαuv2αcosαφtanh(μuv,1l)μuv,1A1.
If H=5, then(2.13a)G1(A1,A3,A5)=34A13+34A12A3+32A32A1+32A52A1+34A32A5+32A1A3A5,(2.13b)G3(A1,A3,A5)=34A33+14A13+32A12A3+32A52A3+34A12A5+32A1A3A5,(2.13c)G5(A1,A3,A5)=34A53+32A12A5+34A12A3+34A32A1+32A32A5.Consider the harmonic balance for H=1,3,5 and ignore the higher harmonic terms in (2.10). Then, the following three equations are obtained:(2.14a)-ρ(ω)2A1+ρωs2A1+βG1(A1,A3…AH)=ρa(ω)2∑uU∑vVαuv2αcosαφtanh(μuv,1l)μuv,1A1,(2.14b)-ρ(3ω)2A3+ρωs2A3+βG3(A1,A3…AH)=ρa(3ω)2∑uU∑vVαuv2αcosαφtanh(μuv,3l)μuv,3A3,(2.14c)-ρ(5ω)2A5+ρωs2A5+βG5(A1,A3…AH)=ρa(5ω)2∑uU∑vVαuv2αcosαφtanh(μuv,5l)μuv,5A5.
According to (2.9a), one more equation is obtained:
(2.14d)A=A1+A3+A5.Note that A is the initial modal displacement which is a known parameter. Thus, there are four unknowns A1,A3,A5, and ω in (2.14a)–(2.14d). The resonant frequency ω is obtained by solving the four equations.


### 2.3. Homotopy Perturbation Method

Consider the free large amplitude vibration of a flexible panel and the corresponding governing equation(2.15)d2wldτ2+ωs2wl+β′wl3=0,
where β′=β/ρ.Using the homotopy perturbation approach [29, 30], equation (2.15) can be linearized and construct the following homotopy (note that there are some alternative ways of constructing the homotopy equation, e.g., [36]):(2.16a)d2wldτ2+ω2wl+q(ωs2wl-ω2wl+β′wl3)=0,(2.16b)wl=wl,0+qwl,1+⋯,where q∈[0,1].wl,0 and wl,1 are the linear and first order approximate terms. Their initial conditions and approximate forms are given by(2.17a)wl,0=A;dwl,0dτ=0,atτ=0,(2.17b)wl,1=0;dwl,1dτ=0,atτ=0,(2.17c)wl,0=Acos(ωt),(2.17d)wl,1=B(cos(ωτ)-13cos(3ωτ)),where ω is the approximate natural frequency of the nonlinear system. A and E and vibration amplitudes of the wl,0 and wl,1, respectively.Substituting (2.16b) into (2.16a), collecting terms of the same power of q, gives(2.18a)d2wl,0dτ2+ω2wl,0=0,(2.18b)d2wl,1dτ2+ω2wl,1+β′wl,03+(ωs2-ω2)wl,0=0.According to [37], the variational formulation is given by
(2.19)J(wl,1)=∫02π/ω{-12(dwl,1dτ)2+ω2wl,12+(ωs2-ω2)wl,0wl,1+β′wl,03wl,1}dτ=0.
Consider ∂J/∂B=0 and ∂J/∂ω=0. Then, the resonant frequency is given by
(2.20)ωo2-ωs2-34β′A2=0⇒ωo=ωs2+34β′A2,
where ωo is the resonant frequency of the large amplitude vibration.Now consider the modal acoustic pressure force acting on the panel in (2.7b). Equation (2.18a) can be rewritten and given by
(2.21)d2wl,0dτ2+ωo2wl,0=Fl⇒-ρω2A+ρωs2A+β34A3=ρa(ω)2∑uU∑vVαuv2αcosαφtanh(μuvl)μuvA.
Equation (2.21) is exactly the same as (2.12), which is developed from the harmonic balance method.


## 2.1. Governing Equations

In Figure1, the acoustic pressure within the rectangular tube induced by the flexible end is given by the following homogeneous wave equation [1]:
(2.1)∇2P-1Ca2∂2P∂τ2=0,
where P = the pressure within the tube; τ = time; Ca = sound speed.Figure 1
The rectangular tube with one open end, one flexible end, and four rigid side walls.The boundary conditions are given by(2.2a)∂P∂x=0,atx=0anda,(2.2b)∂P∂y=0,aty=0andb,(2.2c)P=0,atz=0,(2.2d)∂P∂z=-ρa∂2wl(t)∂τ2φ(x,y),atz=l,where wl(τ)=Acos(ωτ)=flexible plate vibration response; φ(x,y)=vibration mode shape=sin(π/a)sin(π/b); ρa=airdensity;A=displacement amplitude (or displacement at time=0); ω=vibration frequency.According to [1], the general multiacoustic mode solution of (2.1) is
(2.3)P=∑uU∑vV[Luvsinh(μuvz)+Nuvcosh(μuvz)]cos(uπxa)cos(vπyb)cos(ωτ),
where μuv=(uπ/a)2+(vπ/b)2-(ω/Ca)2;u and v=0,2,4,… are the acoustic mode numbers; U and V are the last acoustic mode numbers; Luv and Nuv are unknown coefficients to be determined by the boundary conditions.Applying the boundary condition (2.2c) to (2.3) gives
(2.4)Nuv=0.
Then applying the boundary condition (2.2d) to (2.3) gives
(2.5)∂P∂z=∑uU∑vVLuvμuvcosh(μuvl)cos(uπxa)cos(vπyb)cos(ωτ)atz=l∂P∂z=-ρa∂2Acos(ωτ)∂τ2φ(x,y)=ρaω2Acos(ωτ)φ(x,y)⇒Luv=ρaω2αuvαcosAμuvcosh(μuvl),
where αuv=∫0b∫0aφ(x,y)cos(uπx/a)cos(vπy/b)dxdy;
(2.6)αcos=∫0b∫0a[cos(uπxa)cos(vπyb)]2dxdy.
Therefore, the acoustic pressure and modal acoustic pressure force acting on the flexible end at z=l are given by(2.7a)Pl=ρaω2∑uU∑vVαuvαcostanh(μuvl)μuvcos(uπxa)cos(vπyb)Acos(ωτ),(2.7b)Fl=∫0b∫0aPlφ(x,y)dxdyαφ=ρaω2∑uU∑vVαuv2αcosαφtanh(μuvl)μuvAcos(ωτ),where αφ=∫0b∫0aφ(x,y)2dxdy.According to the approach from Chu and Herrmann [15], the governing equation for the large amplitude vibration of a flexible plate is given by(2.8a)ρd2wldτ2+ρωs2wl+βwl3=0,
where ρ = the panel surface density; ωs=Et2/12ρ(1-ν2)[(π/a)2+(π/b)2] = the fundamental linear resonant frequency of the plate; β=(Eh/12(1-ν2))(γ/a4) is the nonlinear stiffness coefficient that is due to the large amplitude vibration; E is the Young’s modulus of the plate; γ=3π4[((3/4)-(ν2/4))(1+r4)+νr2];r=a/b is the aspect ratio; ν is Poisson’s ratio; and t = the plate thickness.Consider the modal acoustic pressure in (2.7b) on the plate. Equation (2.8a) is modified and given by
(2.8b)ρd2wldτ2+ρωs2wl+βwl3=Fl.


## 2.2. Harmonic Balance Method

Consider the structural vibration response in terms of harmonic terms [20]:(2.9a)wl=∑hHAhcos(hωτ),
where Ah is the amplitude of the hth harmonic response; h=1,3,…H; and H is the last harmonic order number; A=∑hHAh.Then, the modal acoustic pressure force atz=l in (2.7b) is revised and also consists of higher harmonic terms. 								(2.9b)Fl(t)=ρa∑hH∑uU∑vV(hω)2αuv2αcosαφtanh(μuv,hl)μuv,hAhcos(hωτ),where μuv,h=(uπ/a)2+(vπ/b)2-(hω/Ca)2.Similarly, (2.8a) is revised and given by
(2.10)ρd2wldτ2+ρωs2wl+βwl3=ρa∑hH∑uU∑vV(hω)2αuv2αcosαφtanh(μuv,hl)μuv,hAhcos(hωτ)⇒-ρ(hω)2Ah+ρωs2Ah+βGh(A1,A3…AH)=ρa(hω)2∑uU∑vVαuv2αcosαφtanh(μuv,hl)μuv,hAh,
where Gh is a set of functions which contains A1,A3,…AH.IfH=1, then
(2.11)G1(A1)=34A13.
Consider the harmonic balance for H=1 and ignore the higher harmonic terms in (2.10). Then, the following equation is obtained:
(2.12)-ρ(ω)2A1+ρωs2A1+β34A13=ρa(ω)2∑uU∑vVαuv2αcosαφtanh(μuv,1l)μuv,1A1.
If H=5, then(2.13a)G1(A1,A3,A5)=34A13+34A12A3+32A32A1+32A52A1+34A32A5+32A1A3A5,(2.13b)G3(A1,A3,A5)=34A33+14A13+32A12A3+32A52A3+34A12A5+32A1A3A5,(2.13c)G5(A1,A3,A5)=34A53+32A12A5+34A12A3+34A32A1+32A32A5.Consider the harmonic balance for H=1,3,5 and ignore the higher harmonic terms in (2.10). Then, the following three equations are obtained:(2.14a)-ρ(ω)2A1+ρωs2A1+βG1(A1,A3…AH)=ρa(ω)2∑uU∑vVαuv2αcosαφtanh(μuv,1l)μuv,1A1,(2.14b)-ρ(3ω)2A3+ρωs2A3+βG3(A1,A3…AH)=ρa(3ω)2∑uU∑vVαuv2αcosαφtanh(μuv,3l)μuv,3A3,(2.14c)-ρ(5ω)2A5+ρωs2A5+βG5(A1,A3…AH)=ρa(5ω)2∑uU∑vVαuv2αcosαφtanh(μuv,5l)μuv,5A5.
According to (2.9a), one more equation is obtained:
(2.14d)A=A1+A3+A5.Note that A is the initial modal displacement which is a known parameter. Thus, there are four unknowns A1,A3,A5, and ω in (2.14a)–(2.14d). The resonant frequency ω is obtained by solving the four equations.


## 2.3. Homotopy Perturbation Method

Consider the free large amplitude vibration of a flexible panel and the corresponding governing equation(2.15)d2wldτ2+ωs2wl+β′wl3=0,
where β′=β/ρ.Using the homotopy perturbation approach [29, 30], equation (2.15) can be linearized and construct the following homotopy (note that there are some alternative ways of constructing the homotopy equation, e.g., [36]):(2.16a)d2wldτ2+ω2wl+q(ωs2wl-ω2wl+β′wl3)=0,(2.16b)wl=wl,0+qwl,1+⋯,where q∈[0,1].wl,0 and wl,1 are the linear and first order approximate terms. Their initial conditions and approximate forms are given by(2.17a)wl,0=A;dwl,0dτ=0,atτ=0,(2.17b)wl,1=0;dwl,1dτ=0,atτ=0,(2.17c)wl,0=Acos(ωt),(2.17d)wl,1=B(cos(ωτ)-13cos(3ωτ)),where ω is the approximate natural frequency of the nonlinear system. A and E and vibration amplitudes of the wl,0 and wl,1, respectively.Substituting (2.16b) into (2.16a), collecting terms of the same power of q, gives(2.18a)d2wl,0dτ2+ω2wl,0=0,(2.18b)d2wl,1dτ2+ω2wl,1+β′wl,03+(ωs2-ω2)wl,0=0.According to [37], the variational formulation is given by
(2.19)J(wl,1)=∫02π/ω{-12(dwl,1dτ)2+ω2wl,12+(ωs2-ω2)wl,0wl,1+β′wl,03wl,1}dτ=0.
Consider ∂J/∂B=0 and ∂J/∂ω=0. Then, the resonant frequency is given by
(2.20)ωo2-ωs2-34β′A2=0⇒ωo=ωs2+34β′A2,
where ωo is the resonant frequency of the large amplitude vibration.Now consider the modal acoustic pressure force acting on the panel in (2.7b). Equation (2.18a) can be rewritten and given by
(2.21)d2wl,0dτ2+ωo2wl,0=Fl⇒-ρω2A+ρωs2A+β34A3=ρa(ω)2∑uU∑vVαuv2αcosαφtanh(μuvl)μuvA.
Equation (2.21) is exactly the same as (2.12), which is developed from the harmonic balance method.


## 3. Results and Discussions

In this numerical study, the first two resonant frequencies of the rectangular tube with a flexible end are considered and obtained by solving (2.10) and (2.21). The material properties of the flexible end or (flexible panel at z=l) are as follows: Young’s modulus = 7.1 × 1010 N/m2, Poisson’s ratio = 0.3, and mass density = 2700 kg/m3. The dimensions of the tube are 0.2 m × 0.2 m × 1.0 m. The panel thickness is 1 mm. The linear 1st structural resonant frequencies of the panel (not mounted to the tube end), ωs = 121.878 Hz. The first nine acoustic modes (i.e., u=0,2,4;v=0,2,4) and first three harmonic terms (i.e., H=1,3,5) are employed in the convergence study. Tables 1(a) and 1(b) the harmonic term convergence for various amplitudes. The four acoustic modes (i.e., u=0,2;v=0,2) are used in the cases in Tables 1(a) and 1(b). As aforementioned in (2.12) and (2.21), the linear resonant frequencies obtained from the homotopy perturbation method and the harmonic balance method with one harmonic term are exactly the same. It can be seen that the effect of the 3rd harmonic term on the first two resonant frequencies can be ignored. The solutions with the first two harmonic terms can achieve 3-digit accuracy. Tables 2(a) and 2(b) present the results of the acoustic mode convergence studies for various vibration amplitudes. One harmonic term (i.e., H=1) is used in the cases in Tables 2(a) and 2(b). It can be seen that the effect of the higher acoustic modes (i.e., u=4,6…;v=4,6…) on the first two resonant frequencies can be ignored. The solutions with the four acoustic modes can achieve 3-digit accuracy.Table 1
(a) Harmonic term convergence for various amplitudes (1st resonant frequency). (b) Harmonic term convergence for various amplitudes (2nd resonant frequency).
(a)
Homotopy perturbation
No. of harmonic terms = 1
2
3
A
/
t
=
0.2
ω
/
ω
s
=
0.64348
0.64348
0.64347
0.64347
0.6
0.66140
0.66140
0.66094
0.66091
1
0.67759
0.67759
0.67641
0.67619
1.4
0.68721
0.68721
0.68580
0.68530
(b)
Homotopy perturbation
No. of harmonic terms = 1
2
3
A
/
t
=
0.2
ω
/
ω
s
=
1.07786
1.07786
1.07784
1.07784
0.6
1.19539
1.19539
1.1936
1.19356
1
1.40661
1.40661
1.4005
1.40024
1.4
1.66715
1.66715
1.65219
1.6600Table 2
(a) Acoustic mode convergence for various amplitudes (1st resonant frequency). (b) Acoustic mode convergence for various amplitudes (2nd resonant frequency).
(a)
No. of acoustic modes = 1
4
9
A
/
t
=
0.2
0.64363
0.64348
0.64348
0.6
0.66148
0.66140
0.66139
1
0.67762
0.67759
0.67759
1.4
0.68723
0.68721
0.68721
(b)
No. of acoustic modes = 1
4
9
A
/
t
=
0.2
1.07985
1.07786
1.07781
0.6
1.19770
1.19539
1.19534
1
1.40935
1.40661
1.40655
1.4
1.67018
1.66715
1.66709In Figures2(a) and 2(b), the vibration amplitude ratio, A/h, is plotted against the frequency ratio for various panel thicknesses, t=0.5, 0.6, and 0.7 mm, and first two resonant frequencies.(a) The vibration amplitude ratio versus the 1st nonlinear resonant frequency (t=0.5, 0.6, 0.7 mm). (b) The vibration amplitude ratio versus the 2nd nonlinear resonant frequency (t=0.5, 0.6, 0.7 mm).
(a)
(b)The material properties and the other dimensions are the same as those considered in Tables1(a) and 1(b). The linear 1st structural resonant frequencies of the three panels (not mounted to the tube end) in Figures 2(a) and 2(b) are ωs=60.939, 73.127, and 85.315 Hz for t=0.5, 0.6, and 0.7 mm, respectively. Note that these three linear structural resonant frequencies are lower than the linear 1st acoustic resonant frequency of the tube with one rigid end and one open end (i.e., ωa = 85.75 Hz). Generally, the resonant frequencies in all cases are monotonically increasing with the amplitude ratio. In Figure 2(a), the 1st nonlinear resonant frequencies are much smaller than the corresponding linear 1st structural resonant frequencies when the amplitude ratio is small. In Figure 2(b), the 2nd nonlinear resonant frequencies are always higher than the 1st linear acoustic resonant frequency of the tube with one rigid end and one open end. According to a comparison between the three curves, the differences between the 1st nonlinear resonant frequencies of the three cases in Figure 2(a) are getting small for large amplitude ratio. On the contrary, the differences between the 2nd nonlinear resonant frequencies of the three cases in Figure 2(b) are getting large for large amplitude ratio.In Figures3(a) and 3(b), the vibration amplitude ratio, A/h, is plotted against the frequency ratio for various panel thicknesses, t=0.8, 0.9, and 1.0 mm, and first two resonant frequencies. The linear 1st structural resonant frequencies of the three panels (not mounted to the tube end) in Figures 3(a) and 3(b) are ωs=97.503, 109.69, and 121.878 Hz for t=0.8,0.9, and 1.0 mm respectively. Note that these three linear structural resonant frequencies are higher than the 1st linear acoustic resonant frequency of the tube with one rigid end and one open end. Although the curves in Figures 3(a) and 3(b) show similar trends in Figures 2(a) and 2(b), there are some other observations found. According to a comparison between the curves in Figures 2(a) and 3(a), the differences between the 1st nonlinear resonant frequencies in Figure 3(a) are obviously smaller than those in Figure 2(a) for all amplitude ratios. In Figure 3(b), the differences between the 2nd nonlinear resonant frequencies are quite constant for all amplitude ratios, while the differences between the 2nd nonlinear resonant frequencies in Figure 2(b) are getting large for large amplitude ratio.(a) The vibration amplitude ratio versus the 1st nonlinear resonant frequency (t=0.8, 0.9, 1 mm). (b) The vibration amplitude ratio versus the 2nd nonlinear resonant frequency (t=0.8, 0.9, 1 mm).
(a)
(b)In Figures4(a) and 4(b), the 1st and 2nd nonlinear resonant frequencies are plotted against ωs/ωa, for various vibration amplitude ratios (where ωs = the linear 1st structural resonant frequency of the panel, not mounted to the tube end; ωa = the linear 1st acoustic resonant frequency of the tube with one rigid end and one open end). In Figure 4(a), it can be seen that the 1st nonlinear resonant frequencies of all cases are always below ωa and getting close to it, when ωs/ωa is increasing. Similar to the observation in Figure 4(a), the 2nd nonlinear resonant frequencies of all cases in Figure 4(b) are always below 3ωa and getting close to it, when ωs/ωa is increasing. Besides, it can be seen that the 2nd nonlinear resonant of all cases always higher than a certain frequency and converge to it when ωa is getting small.(a) The 1st nonlinear resonant frequency versusωs/ωa (A/t=0.4, 0.8, 1.2 mm). (b) The 2nd nonlinear resonant frequency versus ωs/ωa (A/t=0.4, 0.8, 1.2 mm).
(a)
(b)In Figures5(a) and 5(b), the vibration amplitude ratio, A/h, is plotted against the frequency ratio for various aspect ratios, a/b=1, 1.5, and 2 mm, and first two resonant frequencies. The 1st linear structural resonant frequencies of the three cases are kept the same. It can be seen that the differences between the three curves are very small; and thus the effect of aspect ratio is very minimal on the nonlinear resonant frequencies of the structural acoustic system.(a) The vibration amplitude ratio versus the 1st nonlinear resonant frequency (a/b=1.0, 1.5, 2.0). (b) The vibration amplitude ratio versus the 2nd nonlinear resonant frequency (a/b=1.0, 1.5, 2.0).
(a)
(b)


## 4. Conclusions

This paper presents a multimode formulation, based on the classical nonlinear panel and homogeneous wave equations, for the nonlinear vibrations of a flexible panel mounted to an end of a rectangular tube. The first two resonant frequencies are obtained by solving the multimode differential equations and using the harmonic balance method and homotopy perturbation method. The solutions from the two methods are found to agree well with each other. The convergence study shows the number of acoustic modes and harmonic terms needed for an accurate result. The effects of vibration amplitude, panel thickness, aspect ratio, and so forth have also been investigated. The main findings include the following:(1) if the linear 1st structural resonant frequency of the panel is higher than the linear 1st acoustic resonant frequency of the tube with one rigid end and one open end, the 1st nonlinear resonant frequency of the structural-acoustic system is less sensitive to the panel thickness than that of the rectangular tube, which the linear 1st structural resonant frequency of the panel is lower than the linear 1st acoustic resonant frequency; (2) if the linear 1st structural resonant frequency of the panel is lower than the linear 1st acoustic resonant frequency of the tube with one rigid end, the 2nd nonlinear resonant frequency of the structural-acoustic system is less sensitive to the panel thickness for small amplitude ratio, and more sensitive for large amplitude ratio; and (3) in each case considered, the 1st nonlinear resonant frequency is always lower than the linear 1st acoustic resonant frequency, and the 2nd nonlinear resonant frequency is always higher than the 1st linear acoustic resonant frequency and lower than 2nd linear acoustic resonant frequency, respectively.



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*Source: 391584-2012-12-06.xml*