A computational investigation of the stiffened composite panel with discrete-source damage

The mechanical responses change in the stiffened composite panels because of discrete-source damage. FEA method was used to study the damage propagation and failure properties of stiffened composite panels with discrete-source damage. The influence of discrete-source damage on residual strength of the composite panel was also investigated. It has showed that there is high strain concentration at the notch tip. Based on different failure criteria, FEA method with progressive failure procedure was used to simulate the damage progression and failure procedure of the notched stiffened composite panel effectively. The global models were set up firstly to calculate the stress distribution and evaluate the residual strength of the panels with different cut angles. The local model was set up secondly to simulate the local damage and failure extending both in-plane and interface. The in-plane and interface damage mechanisms could be considered in this model. The research results indicated that notched composite panel was suitable to simulate the damage property of stiffened composite panel with discrete-source damage. The changes in the cut angles are not significant influenced residual strength of the composite panel with discrete-source damage.