Modal analysis of sandwich panel with composite laminated faces

Eva Kormanikova1

1Department of Structural Mechanics, Technical University of Kosice, Košice, Slovakia

Vibroengineering PROCEDIA, Vol. 23, 2019, p. 105-109.
Received 15 March 2019; accepted 22 March 2019; published 25 April 2019

37th International Conference on Vibroengineering in Bratislava, Slovakia, April 25-26th, 2019

Copyright © 2019 Eva Kormanikova. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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A sandwich panel with laminate faces was used for free vibration analysis. The Shear Deformation Theory is considered for analysis. The effect of sandwich design parameters such as core thickness and fiber reinforced angle on vibration response is investigated. The modal analysis for various lengths of sandwich panel is done to find the limit length of the panel, which is sensitive to dynamic wind load.

  • A sandwich panel with laminate faces
  • Free vibration analysis
  • The Shear Deformation Theory
  • The effect of sandwich design parameters on vibration response
  • The limit length of the panel
  • Sensitivity to dynamic wind load

Keywords: sandwich panel, mode shape, natural frequencies, limit length.

1. Introduction

Sandwich panels are one of very important group of laminated composites. They consist of two thin faces with thickness of h1 and h3 and a core with thickness of h2. The faces are made of high strength materials having good properties under tension, such as fiber reinforced polymer matrix laminates used in this paper, while the core is made of lightweight materials such as foam, having good properties under compression. Sandwich composites combine lightness and flexural stiffness [1].

The analysis of simple sandwich structures may be achieved by analytical methods, by adapting the classical tools of structural analysis on anisotropic elastic structure face elements. For more complex structures, such as more general boundary conditions or loading, numerical methods such as Finite Element Method, Boundary Element Method, etc. are used [2-5].

The use of assumptions is necessary to mathematical modeling of laminated composites. These include an elastic behavior of fibers and matrices, a perfect bonding between fibers and matrices, low variation of the mechanical characteristics of the individual fibers, uniform fiber diameters, their regular arrangement in the matrix, etc.

Taking into account the different size scales of mechanical modelling of structure elements composed of fiber reinforced composites, the micro, macro and structural modeling levels must be considered [6-10].

2. First-order shear deformation theory (FSDT)

FSDT considers that transverse normal do not remain perpendicular to the midsurface after deformation. This theory is used for thicker plates or sandwiches taking into account the Reissner kinematics (Fig. 1).

Transverse shear stresses are added to the state of plane stress for this reason. Shear deformations are written following the Fig. 2:


where d is midplane distance of sandwich faces:


Fig. 1. Reissner kinematics

Reissner kinematics


Reissner kinematics


Fig. 2. Geometry of shear deformation

Geometry of shear deformation


Geometry of shear deformation


Internal forces are expressed by terms:


The constitutive equations for a sandwich are in the form:


with stiffness coefficients:

Aij=Aij1+Aij3,   Bij=12h2Aij3-Aij1,   Cij=Cij(1)+Cij(3),
Dij=12h(2)Cij(3)-Cij(1),   Aijs=Eijs h(2),   i,j=4,5,

where Aij, Dij are coefficients of extension and bending stiffness matrix, Bij, Cij are coefficients of extension-bending coupling stiffness matrix, Eijs are the transverse shear moduli of the core.

3. Free vibrations of sandwich plates

The equations to determine the natural frequencies of the symmetric sandwich panel are used [1]:


where ks is the transverse shear deformation factor given by value 5/6:

ρm=1hk=1Nρk(z(k)-z(k-1)),   I=ρmh31213k=1Nρk(z(k))3-(z(k-1))3,

where ρk is the mass density of the kth layer.

For the simply supported plate let:

w0x,y,t=w0°eiωmnt,   Φxx,y,t=Φx°eiωmnt,   Φy(x,y,t)=Φy°eiωmnt,

where m, n – are integers only, ωmn – is natural angular velocity.

Ultimate length of sandwich panel depends on the ultimate frequency f0,lim  of dynamic loading affected to the structures:

L0,lim=πm2ks2A 552D11hρm+π2D11h  2ρ m2f0,lim2-πD11hρmf0,lim 2ks A 55 h ρmf0,lim .

4. Numerical solution of sandwich panels

For the numerical solution, the simply supported panel with laminate facings was used. Panel length is 3250, 4250, 5250, 6250, 7100 mm, nominal width is 1000 mm. The thickness of the panel is 40, 80 and 120 mm. The thickness of laminate facings is 1 mm, composed of eight layers of symmetric [0/±45/90]s, [0/90]2s and [0/0]2s laminates, respectively. The thickness of each laminate layer is 0.125 mm. Carbon fibers in epoxy matrix were considered [11], with the following characteristics: Ef= 230 GPa; Em= 3 GPa; νf=0.3; νm= 0.3; ξ= 0.6; ρc= 1508 kg/m3. Sandwich core, consisting of PUR foam, has material constants: EPUR= 25 MPa; νPUR= 0.3; ρPUR= 100 kg/m3.

Firstly, it has been done the modal analysis of the sandwich panels with a thickness of 40, 80 and , composed of eight layers of symmetric [0/±45/90]s, [0/90]2s and zero angles [0/0]2s laminates as sandwich outer layers for 3250 mm panel length.

Table 1 shows the first natural frequency depending on the variation of fiber reinforced angle of the laminate facings and the core thickness of the sandwich panel. The natural frequencies depend on the rotation of individual layers to the global coordinate system, while the lowest value of first natural frequency was obtained for the sandwich panel with [0/45/-45/90]s laminate faces and panel thickness 40 mm. Dependence of the natural frequencies from its natural mode shape of vibration by various faces is shown in the Fig. 3.

Table 1. First natural frequencies f [Hz] of sandwich panels with length L= 3250 mm

Natural mode shape
Laminate [0/90]2s
Laminate [0/±45/90]s
Laminate [0/0]2s
Thickness [mm]
Thickness [mm]
Thickness [mm]

Secondly, the modal analysis for various lengths of the sandwich panel with [0/45/-45/90]s laminate faces was made to find the limit length of the panel, which is sensitive to dynamic wind load with f0,lim= 5 Hz. The limit length of sandwich panels with [0/45/-45/90]s laminate faces was found for various thicknesses of the sandwich. For sandwich panel 40, 80 and 120 mm thick, the limit length is 5.0 m, 6.25 m and 7.1 m, respectively. These types of sandwich panels are not sensitive to dynamic wind load under calculated limit lengths (Fig. 4).

Fig. 3. Natural frequencies [Hz] of the first ten natural mode shapes of sandwich panels with 80 mm thickness

Natural frequencies [Hz] of the first ten  natural mode shapes of sandwich panels  with 80 mm thickness

Fig. 4. First natural frequencies [Hz] of sandwich panels with symmetric [0/±45/90]s laminate facings versus sandwich length

First natural frequencies [Hz] of sandwich panels with symmetric [0/±45/90]s laminate  facings versus sandwich length

5. Conclusions

The mechanical properties of sandwich panels with laminate faces were investigated. Computational program MATLAB was used to calculate the effective material properties of laminate faces [12, 13]. The type of faces of a sandwich panel and the core thickness affect its natural frequencies. The first natural frequency of investigated laminate panels with the length L= 3250 mm is up to f0,lim= 5 Hz (Table 1), therefore the panels are not sensitive to the dynamic wind load. The sandwich panels with [0/45/-45/90]s laminate faces and 40, 80 and 120 mm thick are not sensitive to dynamic wind load under their ultimate length 5.05 m, 6.25 and 7.1 m, respectively (Fig. 4).


This work was supported by the Scientific Grant Agency of the Ministry of Education of Slovak Republic and the Slovak Academy of Sciences under Projects VEGA 1/0374/19 and 1/0078/16.


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