Thermally-induced, geometrically nonlinear response of symmetrically laminated composite platesThis paper discusses the thermally-induced geometrically nonlinear response of symmetrically laminated composite plates. The plate response is due to a temperature increase that is uniform in the plane of the plate but has a slight gradient through the thickness. The case of a completely uniform temperature increase but with an initial out-of-plane imperfection in the plate is also considered. Because they are closely allied problems, thermal buckling and postbuckling are discussed. Using variational methods in conjunction with a Rayleigh-Ritz formulation, these responses are investigated for two laminates, a (+/- 45/0/90)s and a (+/- 45/02)s, under two different simple support conditions.
Document ID
19920051759
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Meyers, C. A. (NASA Langley Research Center Hampton, VA, United States)
Hyer, M. W. (Virginia Polytechnic Institute and State University Blacksburg, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Structural Mechanics
Report/Patent Number
AIAA PAPER 92-2539
Meeting Information
Meeting: AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference