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Thermomechanical postbuckling analysis of laminated composite shellsThe nonlinear response of laminated composite structures subjected to thermal loads is investigated. Analysis is performed using a refined theory and an associated finite element model for geometrically nonlinear analysis of laminated composite shell structures. The model is based on a third-order displacement field which accounts for both transverse shear and transverse normal deformations. Numerical studies of simply-supported plates and cylindrical panels indicate that when the panels are free to expand or contract in the transverse direction, the predicted critical buckling temperatures do not depend significantly upon whether or not transverse normal deformations are explicitly accounted for in the analysis model. However, the critical buckling temperatures are strongly dependent upon whether or not the transverse normal deformations are restrained along the boundaries of the panels.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Averill, R. C.
(Michigan State Univ. East Lansing, United States)
Reddy, J. N.
(Texas A & M Univ. College Station, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA(ASME)ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pt. 1 (A93-33876 1
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Structural Mechanics
Report/Patent Number
AIAA PAPER 93-1337
Accession Number
Funding Number(s)
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