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

• Published in: Journal of sound and vibration Vol. 291; no. 3; pp. 1186 - 1201
• Main Authors: Oh, I.K., Lee, I.
• Format: Journal Article
• Language: English
• Published: London Elsevier Ltd 01.01.2006; Elsevier
• Subjects: Actuation; Electric fields; Exact sciences and technology; Flutter; Fundamental areas of phenomenology (including applications); Panels; Physics; Piezoelectricity; Shells; Solid mechanics; Static elasticity (thermoelasticity...); Structural and continuum mechanics; Supersonic flutter; Vibration; Vibration, mechanical wave, dynamic stability (aeroelasticity, vibration control...); Supersonic flow; Aeroelastic flutter; Displacement(deformation); Large displacement; Thermal load; Revolution shell; Modeling; Finite element method; Critical pressure; Active system; Piezoelectricity; Thermoelasticity; Vibration control; Piecewise linear system; Aeroelasticity; Cylindrical shell; Structural analysis
• ISSN: 0022-460X; 1095-8568
• DOI: 10.1016/j.jsv.2005.07.033

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.