E. Madenci et A. Barut, THERMAL POSTBUCKLING ANALYSIS OF CYLINDRICALLY CURVED COMPOSITE LAMINATES WITH A HOLE, International journal for numerical methods in engineering, 37(12), 1994, pp. 2073-2091
A non-linear finite element analysis including a new flat shell elemen
t has been developed to examine the response of laminated panels going
through large deflections and rotations under uniform temperature cha
nge. The equilibrium path describing the relationship between temperat
ure and deflection is sensitive to the material system, hole size, in-
plane boundary conditions and radius of curvature. Certain laminate co
nfigurations exhibit snap-through and bifurcation along this path. The
accuracy of the results for a cylindrically curved panel is establish
ed by considering numerous validation problems with known solutions. T
he method has been demonstrated to be highly effective for predicting
the non-linear response of thin composite shells subjected to uniform
temperature change in the presence of large displacements and rotation
s and material anisotropy.