Exercise 6.5 Compute the stresses in laminate coordinates at topand bottom of each lamina in Example 6.1 (p. 178) when the laminateis subjected to ?0x = 765(10?6) mm/mm, ?0y = ?280(10?6) mm/mm, ?xy= 34.2(10?6)1/mm and all remaining strains and curvatures equal tozero.
Note: this is Example 6.1 Compute the coefficients in the platestiffness equations (6.9) for a two- lamina laminate with ?1 = 55?,?2 = ?55?, t1 = t2 = 0.635 mm
with material properties given E1 = 19.981 GPa, ?12 = 0.274, E2= 11.389 GPa, G12 = G13 = 3.789 GP a [172]. assume the out-of-planeshear modulus G23 ?= Gm = 0.385 GP a.
