Section 5 Sandwich Panels

501. Consideration of buckling

Buckling strength of sandwich panels related to longitudinal hull girder strength or local axial loads are to be dealt with individually.

502. Minimum requirements to structural sandwich panels

1. The reinforcement of skin laminates is to contain at least 40 % continuous fibres.

2. The mechanical properties of the core material of structural sandwich panels are to comply with the following minimum requirements (refer to Table 3.5.1).

Table 3.5.1 Mechanical Properties of Sandwich Panels

3. The mass of reinforcement (g m ) in skin laminates in structural sandwich panels should

not be less than the following.

to be submitted.

However, Details including laminating process such as work sheets

≥

for

m

:

:

:

mass of reinforcement per unit area,

given in Table 3.5.2 (For mixed material reinforcements can be found by linear inter-

polation in the table according to the relative percentage of each material with respect to weight per unit area.)

given in Table 3.5.2.

4. Deviation from the minimum requirements

may be accepted by the Society on consideration of

yacht type and service restriction or based on documentation of equivalent resistance to loads de- scribed in Table 3.5.1.

Table 3.5.2

and

503. Bending

1. Normal stresses in skin laminates and core shear stresses

(1) Maximum normal stresses in the skin laminates of a sandwich panel subject to uniform lateral pressure is given by the following formula :

N mm

: For stresses parallel to the longest edge, refer to Fig 3.5.4.

: For stresses parallel to the shortest edge, refer to Fig 3.5.4.

: section modulus of the sandwich panel per unit breadth (mm mm ). For a sandwich-

panel with skins of equal thickness =

: factor, as defined in follows.

= or

according to Fig 3.5.5, for panels with fixed edges or partially fixed

edges.

for stresses parallel to the longest edge.

for stresses parallel to

shortest edge.

(2) The maximum core shear stresses at the midpoints of the panel edges of a sandwich panel sub- ject to lateral pressure is given by the following formula :

N mm

= , for core shear stress at midpoint of longest panel edge, see Fig 3.5.6.

= for core shear stress at midpoint of shortest panel edge, see Fig 3.5.6.

Fig 3.5.4 Factors

and

Fig 3.5.5 factor

Fig 3.5.6 Factors

and

2. Local skin buckling

The critical local buckling ing formula :

stress for skin laminates exposed to compression is given by the follow-

N mm

3. Deflection

The deflection at the midpoint of a flat panel is given by the following formula :

and : refer to Table 3.5.7.

: factor, as defined in follows.

= 1.0, panels with simply supported edges.

= refer to Fig 3.5.8, panels with fixed edges or partially fixed.

: modulus of elasticity, refer to Table 3.5.3.

Fig 3.5.7 Factors

and

Fig 3.5.8 Factor

Table 3.5.3 Modulus of Elasticity

4. Allowable stresses and deflections

The maximum normal stresses in skin laminates, core greater than given values in following Table 3.5.4.

shear stresses and deflection are not to be

Table 3.5.4 Allowable Stresses and Deflection