Output details

Buckling of composite plate assemblies using higher order shear deformation theory- An exact method of solution

The top skin of an aircraft wing is usually idealised as plate assemblies. It experiences compressive load and is prone to buckling phenomena. The problem is compounded for composite materials which have very low shear strength. The paper combines for the first time a higher order shear deformation theory with the dynamic stiffness method for an accurate prediction of composite wing’s buckling strength. This is a step-change from current practices. The paper dispenses with the manipulative ad-hoc concept of shear correction factor which often incurs considerable errors in composite structures.