Most sandwich panels are made up of two face sheets and a core. The core is often light, weak and
contributes very little to the stiffness of the panel. This enables a very rough analysis to be made by
assuming that the core is just air and that the cross‐section of the panel is equivalent to a rectangular crosssection tube. Using this assumption derive an equation for E~ in terms of the outer dimensions of the panel (b>>h) and the value of E for the face material. Hint: equate equations 1 and 2 for the same values of span,deflection, force and C1 and note that because b>>h the rectangular tube second moment of area can be given as I ~ h2tb / 2 . Note that you are not calculating a value here, just finding an expression in terms of the aforementioned variables.
Use the assumption in the previous point to derive an approximate equation for the effective density, ρeff , of the panel. Hint: start by assuming the panel is b x b x h in size and calculate the volume of material in the two face sheets of thickness t (you can ignore the side strips). Your equation will be in terms of t/h.
Use your equations to estimate the effective stiffness of a wood (parallel direction) face‐sheet sandwich
panel (with a negligible weak light foam core). Assume the panel apparent density is 50 kg/m3. Comment on whether the result falls in the ‘desired’ region of property space in Figure 1.
s= (L^3*F)/C*E*I and s=(L^3*F)/C*Eeff*Iouter
Area box tube( neglecting sides) 2*t*b, Volume bt = 2*t*b^2
The Attempt at a Solution
Assuming L, F,S and C are the same we are left with E*I=Eeff*Iouter
Eeff/E = 6t/h
ρeff=m/b*b*h and ρ=m/2*t*b^2
I think I have derived the equations correctly except for the E and the ρ stop the equation being used to find the desired values.
Thanks in advance for any help.