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From:
Z. Gürdal (1), B.F. Tatting (2), C.K. Wu (3)
(1) Aerospace Structures Chair holder, Delft University of Technology, The Netherlands
(2) ADOPTECH Inc., Blacksburg, VA, USA
(3) NASA Langley Research Center, Hampton, VA, USA
“Variable stiffness composite panels: Effects of stiffness variation on the in-plane and buckling response”, Composites Part A: Applied Science and Manufacturing, Vol. 39, No. 5, pp. 911-922, May 2008
ABSTRACT: Descriptions of fiber orientation variation for flat rectangular composite laminates that possess variable stiffness properties are introduced. The simplest definition employs a unidirectional variation based on a linear function for the fiber orientation angle of the individual layers. Analyses of variable stiffness panels for in-plane and buckling responses are developed and demonstrated for two distinct cases of stiffness variations. The first case assumes a stiffness variation in the direction of the loading, and numerical results indicate small improvements in buckling load for some panel configurations due to favorable distribution of the transverse stresses over the panel planform. The second case varies the stiffness perpendicular to the loading, and provides a much higher degree of improvement due to the re-distribution of the applied loads. It is also demonstrated that the variable stiffness concept provides a flexibility to the designer for trade-offs between overall panel stiffness and buckling load, in that there exist many configurations with equal buckling loads yet different global stiffness values, or vice versa.
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