Composite Materials Research Progress

92
Michaël Bruyneel
Figure 8.15. Evolution of the strain energy density in the [0/90]S laminate subjected to
N 2 = 1000N
/ mm .
Figure 8.16. Evolution of the strain energy density in the [0/90]S laminate subjected to
N 1 = 1000N
/ mm .
8.4. Optimal Design with Respect to Stiffness and Strength Restrictions
In this application a stiffened laminated composite panel subjected to a uniform pressure is
considered. The geometry, the boundary conditions and the stacking sequence of the different
parts of the panel are illustrated in Figure 8.17. The plies thickness is equal to 0.125 mm and
the base material is carbon/epoxy.