Thickness Expansion Coefficients of Composite Laminates

  • N. J. Pagano
Part of the Solid Mechanics and Its Applications book series (SMIA, volume 34)


Fahmy and Ragai-Ellozy [1] have recently treated the problem of the thermal expansion coefficient in the thickness direction of a symmetric composite laminate. Unfortunately, however, an error has been made in their analysis. Specifically, Equation (1) of that work should take the form
$${a_{3r}} = {a_T} - \frac{1}{{1 - {v_{12}}{v_{21}}}}\left[ {({v_{13}} + {v_{12}}{v_{23}})({a_{1C}} - {a_L}) + ({v_{23}} + {v_{13}}{v_{21}})({a_{2c}} - {a_T})} \right]$$
in the notation of [1]. In particular, v 12 is major Poisson’s ratio.


Residual Stress Thickness Direction Classical Lamination Theory Laminate Composite Material Laminate Fiber 
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  1. 1.
    A. A. Fahmy and A. N. Ragai-Ellozy, “Thermal Expansion of Laminated Fiber Composites in the Thickness Direction,” J. Comp. Materials, Vol. 8 (1974), p. 90.ADSCrossRefGoogle Scholar
  2. 2.
    J. C. Halpin and N. J. Pagano, “Consequences of Environmentally Induced Dilatation in Solids,” in Recent Advances in Engineering Science, edited by A. C. Eringen, Gordon and Breach, London (1970), p. 33.Google Scholar
  3. 3.
    N. J. Pagano, “Exact Moduli of Anisotropic Laminates,” in Mechanics of Composite Materials,Vol. 2, edited by G. P. Sendeckyj, Academic Press, NY (to be published).Google Scholar

Copyright information

© Springer Science+Business Media Dordrecht 1994

Authors and Affiliations

  • N. J. Pagano
    • 1
  1. 1.Air Force Materials LaboratoryWright-Patterson Air Force BaseUSA

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