NTRS - NASA Technical Reports Server

Back to Results
Thermomechanical buckling of multilayered composite panels with cutoutsA study is made of the thermomechanical buckling of flat unstiffened composite panels with central circular cutouts. The panels are subjected to combined temperature changes and applied edge loading (or edge displacements). The analysis is based on a first-order shear deformation plate theory. A mixed formulation is used with the fundamental unknowns consisting of the generalized displacements and the stress resultants of the plate. Both the stability boundary and the sensitivity coefficients are evaluated. The sensitivity coefficients measure the sensitivity of the buckling response to variations in the different lamination and material parameters of the panel. Numerical results are presented showing the effects of the variations in the hole diameter, laminate stacking sequence, fiber orientation, and aspect ratio of the panel on the thermomechanical buckling response and its sensitivity coefficients.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
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 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 93-1336
Accession Number
Funding Number(s)
Distribution Limits

Available Downloads

There are no available downloads for this record.
No Preview Available