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Aerothermoelastic Analysis of Cylindrical Piezolaminated Shells Using Multifield Layerwise Theory

[+] Author Affiliations
Il-Kwon Oh

LG Electronics, Inc., Seoul, Korea

In Lee

Korea Advanced Institute of Science and Technology, Taejon, Korea

Paper No. IMECE2002-33621, pp. 539-546; 8 pages
doi:10.1115/IMECE2002-33621
From:
  • ASME 2002 International Mechanical Engineering Congress and Exposition
  • 5th International Symposium on Fluid Structure Interaction, Aeroelasticity, and Flow Induced Vibration and Noise
  • New Orleans, Louisiana, USA, November 17–22, 2002
  • Conference Sponsors: Applied Mechanics Division
  • ISBN: 0-7918-3659-2 | eISBN: 0-7918-1691-5, 0-7918-1692-3, 0-7918-1693-1
  • Copyright © 2002 by ASME

abstract

For the aerothermoelastic analysis of cylindrical piezolaminated shells, geometrically nonlinear finite elements based on the multi-field layerwise theory have been developed. Present multi-field layerwise theory describes zigzag displacement, thermal and electric fields providing a more realistic multi-physical 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.

Copyright © 2002 by ASME
Topics: Shells

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