Computing of Post-buckling Simulation in Functionally Graded Materials - A Review Paper

A review on the recent development in the non-linear flutter and thermal buckling of an FGM panel under the combined effect of elevated temperature conditions and aerodynamic loading is investigated using a finite element model based on the thin plate theory and von Karman straindisplacement relations to account for moderately large deflection. It is found that the temperature increase has an adverse effect on the FGM panel flutter characteristics through decreasing the critical dynamic pressure. Decreasing the volume fraction enhances flutter characteristics but this is limited by structural integrity aspect. Structural finite element analysis has been employed to determine the FGM panel's adaptive response while under the influence of a uniaxial compressive load in excess of its critical buckling value. With the increase in use of composite materials within aerospace platforms, it is envisaged that the hybrid adaptive FGM panel's configuration will extend the operational performance over conventional materials and structures, particularly when the structure is exposed to an elevated temperature.