Analytical solutions for cross-plied composite shells under transverse
end load are presented. Based on a Saint-Venant's semi-inverse method
and the theory of cylindrically orthotropic elasticity, two connected
partial differential equations are developed using Lekhnitskii's stre
ss functions. Solutions are obtained using separation of variables and
solved the governing equations sequentially. Special cases of a singl
e transversely isotropic (0 degrees ply) shell, mu = 2 and/or xi = 3 o
ccurring in a layer are also briefly derived for stress and displaceme
nt response. To illustrate the fundamental nature of the problem, deta
iled distributions of radial strain and stress for two layups, [90/0](
2) and [0/90](2), with two different midradius to thickness ratios are
discussed.