|
|
||
|
|
|
|
This and the next 2 images are from:
S. Buesing and H.-G. Reimerdes (Department of Aerospace and Lightweight Structures, RWTH Aachen University, 52062 Aachen, Germany),
“A strip element with interface layer for the prediction of delamination in buckled composite panels”, The European Commission Project COCOMAT (Improved MATerial Exploitation at Safe Design of COmposite Airframe Structures by Accurate Simulation of COllapse), 2006
ABSTRACT: An element for the prediction of delamination is presented, that is based on the combination of two shells with an interface layer. This interface layer enables the calculation of stresses between the shells, which are the input for a failure criterion indicating the onset of delamination between the shells. The element is implemented into a tool for the postbuckling simulation of composite stiffened panels, which is based on the discretisation of the structure by strip elements, while the buckling and postbuckling behaviour are described by trigonometric functions. As less degrees of freedom are necessary compared to a finite element formulation, the computational effort is reduced. Implementing the strip element with interface layer into this tool enables the prediction of the onset of delamination during the postbuckling analysis. In the following, the approach and its validation are presented.
Page 102 / 227