Finite element (FE) method is presented for the

analysis of thin rectangular laminated composite decks

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 developed. New numerical results are generated

for in – plane compressive biaxial buckling which serve to

quantify the effect of reversing lamination scheme on

buckling loading. The buckling loads have been

determined for two modulus ratios 40 and 5. It is observed

that, the buckling loads are completely the same for the

given first three modes. Therefore, it can be concluded that

the buckling load of laminated plates will remain the same

even if the lamination order is reversed. The reason behind

this is that the transformed elastic coefficients, , are

equal for both lamination schemes.32-40,Tesma307,IJEAST.pdf (386.0% u)

# EFFECT OF REVERSING LAMINATION SCHEME OF LAYERS ON BUCKLING LOAD FOR LAMINATED COMPOSITE DECKS PLATES

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