Supersonic flutter suppression of piezolaminated cylindrical panels based on multifield layerwise theory

For the aerothermoelastic analysis of cylindrical piezolaminated shells, geometrically nonlinear finite elements based on the multifield layerwise theory have been developed. Present multifield layerwise theory describes zigzag displacement, thermal and electric fields providing a more realistic multiphysical description of fully and partially piezolaminated panels. By applying a Hans Krumhaar's supersonic piston theory, supersonic flutter analyses are performed for the cylindrical piezolaminted shells subject to thermal and piezoelectric loads. The possibility to increase flutter boundary and reduce thermoelastic deformations of piezolaminated panels is examined using piezoelectric actuation. Results show that active piezoelectric actuation can effectively increase the critical aerodynamic pressure by retarding the coalescence of flutter modes and compensating thermal stresses.