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Buckling response of laminates with spatially varying fiber orientationsThe buckling response of a symmetrically laminated composite panel with a spatially varying fiber orientation has been analyzed. Variation of the fiber orientation angle as a function of the position in the panel results in a composite laminate with stiffness properties that are functions of the panel coordinates. The laminates are therefore termed variable stiffness panels. The fiber orientation is assumed to vary only in one spatial direction, although the analysis can be extended to fiber orientations that vary in two spatial directions. The Ritz Method has been used to find the buckling loads and buckling modes for the variable stiffness panels for two different cases. In one of the cases the fiber orientation is assumed to change in the direction of the applied load. The other case is the one in which the fiber orientation varies in a direction perpendicular to the loading direction. Improvements in the buckling load of up to 80 percent over straight fiber configurations were found. Results for three different panel aspect ratios are presented.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Olmedo, Reynaldo
(NASA Langley Research Center Hampton, VA, United States)
Gurdal, Zafer
(Virginia Polytechnic Inst. and State Univ. Blacksburg, 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. 4 (A93-33876 1
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Structural Mechanics
Report/Patent Number
AIAA PAPER 93-1567
Accession Number
Funding Number(s)
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