Int.J.Numer.Meth.Engng. 30, 833-858, 1990


A LAYERED COMPOSITE SHELL ELEMENT FOR ELASTIC
AND THERMOELASTIC STRESS AND STABILITY ANALYSIS
AT LARGE DEFORMATIONS

K. Dorninger and F.G. Rammerstorfer

Institute of Lightweight Structures and Aerospace Engineering,
TU Wien, Vienna, Austria


Abstract - A finite shell element for layered fibre reinforced composite shells has been developed. The degeneration principle is used in combination with specific kinematic assumptions. The thermo-elstic material is either described by the behaviour of the local components, i.e. fibre and matrix material laws and geometrical configuration in each layer, or by the overall orthotropic layer material laws.
Thickness integration for obtaining the different contributions to the shell element's stiffness matrix is performed analytically and prior to the numerical in-plane integration. This leads to a considerable saving in computer time during the incremental-interactive analysis.
Geometrical non-linearities in terms of large deformations and material non-linearities in terms of layer cracking are taken into account. Accompanying eigenvalue analyses allow the determination of the - sometimes rather complicated - buckling behavior with nonlinear buckling deformations.


(hjb,960626)