Free vibration analysis of sandwich panel

摘要: Use of Sandwich construction for an aircraft structural component is very common to the present day. One primary requirements aerospace materials that they should have low density, stiff and strong. panels are thin-walled structures fabricated from two flat sheets separated by a density core. The core investigated here aluminium honeycomb structure because excellent crush strength fatigue resistance. high stiffness weight ratio with respect equivalent solid plate Modeling developed in FEA (ANSYS) consideration rotary inertia. free vibration analysis isotropic sandwich studied. results compared experimental analytical work. Eight nodded isoparametric shell element used (ANSYS). Convergence study also included accuracy results. Analytical based on classical bending theory. Mode shapes corresponding natural frequencies studied simply supported panel. Parameter studies panel covered this analysis. A detailed parameter has been carried out increasing depth as percentage its total thickness, while maintaining constant mass.