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Thermomechanical buckling and postbuckling of multilayered composite panelsA study is made of the thermomechanical buckling and postbuckling responses of flat unstiffened composite panels. The panels are subjected to combined temperature change and applied edge displacement. The analysis is based on a first-order shear deformation, von Karman type nonlinear plate theory. A mixed formulation is used with the fundamental unknowns consisting of the generalized displacements and the stress resultants of the plate. An efficient multiple-parameter reduction method is used in conjunction with mixed finite element models, for determining the stability boundary and postbuckling response. The reduction method is also used for evaluating the sensitivity coefficients which measure the sensitivity of the buckling and postbuckling responses to variations in the different lamination and material parameters of the panel. Numerical results are presented showing the effects of variations in the laminate stacking sequence, fiber orientation, number of layers and aspect ratio of the panels on their thermomechanical buckling and postbuckling responses and their sensitivity coefficients.
Document ID
19920051761
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Noor, Ahmed K.
(NASA Langley Research Center Hampton, VA, United States)
Starnes, James H., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Peters, Jeanne M.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Structural Mechanics
Report/Patent Number
AIAA PAPER 92-2541
Meeting Information
Meeting: AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Location: Dallas, TX
Country: United States
Start Date: April 13, 1992
End Date: April 15, 1992
Accession Number
92A34385
Funding Number(s)
CONTRACT_GRANT: NCCW-0011
CONTRACT_GRANT: NAG1-1162
Distribution Limits
Public
Copyright
Other

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