Vibration of sandwich panels using {3,2}-order plate theory

H. S. Turkmen, V. Z. Dogan, E. Madenci, A. Tessler

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

This paper concerns the evaluation of fundamental natural frequencies and mode shapes of simply-supported sandwich panels using Navier-type solutions within the {3,2}-order equivalent single-layer theory. The kinematic assumptions of the theory are cubic in-plane displacements and a quadratic transverse displacement The theory also assumes a cubic distribution of the transverse normal stress that is continuous across the laminate. The Euler-Lagrange equations of motion and consistent boundary conditions are obtained from Hamilton's principle. The predictive capability of the theory is assessed for homogeneous, laminated composite, and sandwich panels. The fundamental natural frequencies are compared with previously published results for varying plate aspect ratio, length-to-thickness ratio, and material modulus.

Original languageEnglish (US)
Title of host publicationCollection of Technical Papers - 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
Pages8146-8156
Number of pages11
ISBN (Print)1563478927, 9781563478925
DOIs
StatePublished - 2007
Event48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference - Waikiki, HI, United States
Duration: Apr 23 2007Apr 26 2007

Publication series

NameCollection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Volume8
ISSN (Print)0273-4508

Other

Other48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
CountryUnited States
CityWaikiki, HI
Period4/23/074/26/07

ASJC Scopus subject areas

  • Architecture
  • Materials Science(all)
  • Aerospace Engineering
  • Mechanics of Materials
  • Mechanical Engineering

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