The objective of the work is to determine dynamic loading of air wings using Fem with axial compressive characteristic under strength and bucking constraints deploying the air wing design. The composite plate responses are sensitive to transverses shear deformation effects, and hence an accurate formulation has been employed for composite plates which includes the transverse shear deformation effects. Towards this, a plate formulation has been used which calculates the buckling load including the effects of transverse shear flexibility. The formulation first address the buckling problem of uni – axially and bi – axially loaded composite plates under simply supported boundary conditions and to study effect of angle of twist on natural frequencies of different plate and also considering the different Ply orientation.