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

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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. (c) 2005 Elsevier Ltd. All rights reserved.
Publisher
ACADEMIC PRESS LTD ELSEVIER SCIENCE LTD
Issue Date
2006-04
Language
English
Article Type
Article
Citation

JOURNAL OF SOUND AND VIBRATION, v.291, no.3-5, pp.1186 - 1201

ISSN
0022-460X
DOI
10.1016/j.jsv.2005.07.033
URI
http://hdl.handle.net/10203/5569
Appears in Collection
ME-Journal Papers(저널논문)AE-Journal Papers(저널논문)
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