BIAXIAL BUCKLING OF THIN LAMINATED COMPOSITE PLATES modified version


(osama mohammed elmardi suleiman khayal) #1

Abstract— Finite element (FE) method is presented for the
analysis of thin rectangular laminated composite plates
under the biaxial action of in – plane compressive loading.
The analysis uses the classical laminated plate theory
(CLPT) which does not account for shear deformations. In
this theory it is assumed that the laminate is in a state of
plane stress, the individual lamina is linearly elastic, and
there is perfect bonding between layers. The classical
laminated plate theory (CLPT), which is an extension of
the classical plate theory (CPT) assumes that normal to the
mid – surface before deformation remains straight and
normal to the mid – surface after deformation. Therefore,
this theory is only adequate for buckling analysis of thin
laminates.
A Fortran program has been compiled. New numerical
results are generated for in – plane compressive biaxial
buckling which serve to quantify the effects of lamination
scheme, aspect ratio, material anisotropy, fiber orientation
of layers, reversed lamination scheme and boundary
conditions.
It was found that symmetric laminates are stiffer than the
anti – symmetric one due to coupling between bending and
stretching which decreases the buckling loads of
symmetric laminates. The buckling load increases with
increasing aspect ratio, and decreases with increase in
modulus ratio. The buckling load will remain the same
even when the lamination order is reversed. The buckling
load increases with the mode number but at different rates
depending on the type of end support. It is also observed
that as the mode number increases, the plate needs
additional support.32-44,Tesma212,IJEAST.pdf (760.9% u)