An aircraft quality sandwich panel has the characteristics listed in the table.

a. Use the data and Eqs (12.30)- (12.32) of the text to calculate the equivalent density, flexural modulus and strength.

b. Plot these on a copy of a modulus-density, a Strength-Density and Modulus-Strength chart (Figures 3.3, 3.4 and 3.5). Do the flexural properties of the panel lie in a region of property space not filled by monolithic materials?

Data From Equation (12.30)

Data From Equation (12.32)

Data From Figure 3.3

Data From Figure 3.4

Data From Figure 3.5

Transcribed Image Text:

Data for glass fibre/aluminium honeycomb sandwich panel Face material Core material 0.38 mm glass fiber/epoxy 3.2 mm cell, 97.8 kg/m, 5052 Alu honeycomb Panel weight per unit area, m 2.65 kg/m Panel length, L 510 mm Panel width, b Panel thickness, d Flexural stiffness EI 51 mm 10.0 mm 67 Nm Failure moment Mf 160 Nm