Abstract:
A method for predicting and analyzing the ultimate load and the location of failure of fiber-reinforced composite wing stringer subjected to compressive loading was proposed. A three dimensional FE model was established for displacement and damage analysis. The onset of damage was predicted by 2DHashin’s initiation criterion. A new stiffness degradation method of damaged material was suggested. The progression of damage was controlled by a damage evolution law, which combines stress failure and fracture energy dissipation of fracture mechanics. The model characterized damages in the form of damage variables. It was implemented with a user subroutine UMAT of ABAQUS/Standard by using a viscous regularization method which improves the convergence. The numerical prediction was compared with the experimental results of the compression test of composite wing stringers, and the ultimate load and failure location correlate well with the prediction results.
Key words： 

Key words: fiber-reinforced composite, wing stringer, progressive damage, compressive damage