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)

# BIAXIAL BUCKLING OF THIN LAMINATED COMPOSITE PLATES modified version

**osama64**(osama mohammed elmardi suleiman khayal) #1