Use of the global model for determining interlaminar normal stress in composite laminates
- Univ. of Dayton, OH (United States)
The minimum number of kinematic variables in conjunction with higher order plate theories for approximating the stresses in the free-edge zone of a laminate under uniaxial inplane tension is examined. It is well recognized that classical shear deformation theory is not appropriate for such problems. The through-the-thickness normal strain component must be non-zero in order to obtain reasonable results. Two higher order theories are compared for approximating interlaminar stress distributions in the free-edge zone. These theories employ kinematic relations which lead to constant and linear distributions of transverse normal strain through-the-thickness of the laminate. Interlaminar stresses in the free-edge zone at the midplane and at the 0{degree}/90{degree} interface of a bidirectional laminate are considered. Difficulties associated with a constant through-the-thickness strain type theory in determining stresses at interlaminar locations other than the midplane are also addressed.
- OSTI ID:
- 237753
- Report Number(s):
- CONF-9510177--; ISBN 1-56676-376-2
- Country of Publication:
- United States
- Language:
- English
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