Homogenization of corrugated core sandwich panels

TLDR: In this paper, the effective properties of corrugated core sandwich panels are investigated, based on the asymptotic expansion method, and an equivalent Reissner-Mindlin homogeneous plate is derived.

About: This article is published in Composite Structures.The article was published on 2003-02-01 and is currently open access. It has received 211 citations till now. The article focuses on the topics: Sandwich panel & Sandwich-structured composite.

Figures

Fig. 4. Alveolar geometries studied.

Fig. 3. Reference stiffened panel and stiffener dimensions, in mm.

Table 4 Effective moduli for the FRP honeycomb sandwich panel

Table 2 Engineering constants for the core material

Fig. 10. Von Mises stress (MPa) contour lines on the deformed shape vK11 .

Table 3 Engineering constants for face laminates

Frequently asked questions

Q1. What are the contributions in "Homogenization of corrugated core sandwiches panels" ?

In this paper, the authors considered a simple bending loading, still under the assumption of cylindrical bending, on a 10-period-long panel, in plane 13, when condition ~u ¼~0 is imposed at all the nodes in the cross-section of the origin. 

Q2. What is the method to solve the Kirchhoff Love plate problem?

Starting from 3D elastic problem, the asymptotic expansion method enables to recover, at the leading order, the Kirchhoff Love model. 

Q3. What are the parameters that can be determined for the different panels?

The values that parameters t, tf , tc and p should be given can then readily be determined, for stiffness moduli Em;fa and G m;f 12 to be at least within 5% of those of the stiffened panel. 

Q4. What is the definition of the numerical homogenization method?

In the following, the finite element computation of the plate effective properties will be called the numerical homogenization method. 

Q5. What is the effect of the assumptions on the effective properties of the basic cell problems?

One can easily verify that these assumptions have a negligible effect on effective properties since it s mainly the in-plane behavior of the core and the facings which is involved in the loadings of the basic cell problems. 

Q6. What is the way to determine the role of the facings on the panel?

Another way to pinpoint the important role played by the facings on the panel overall behavior consists in using the classical laminated plate theory to assess the equivalent behavior of a multilayered composite platemade of two facings and one intermediate layer whose Young s modulus is negligible compared to that of the facings. 

Q7. What is the way to model the alveolar panels?

This will make it possible to model the alveolar panels as equivalent homogeneous plates, and will reduce the computation time when the finite element analysis is made on the whole ship. 

Q8. How many mm thicknesses are needed to obtain the membrane moduli of the stiffened?

As for the other parameters, tf ; tc and p, they must respectively be set to 2.4 mm, 1 mm and 45 mm to obtain the membrane moduli Em1 and E m 2 of the stiffened panel. 

Q9. What is the value of modulus G13 for sandwich panels?

It appears then that the core shape has a strong influence on the value of modulus G13, and that T2 triangular stiffeners at 60 give the best transverse shear stiffness for sandwich panels. 

Q10. What is the main limitation of the homogenization method used here?

The main limitation of the homogenization method used here is that, at the leading order, it leads to an equivalent Kirchhoff Love homogeneous plate.