The Buckling And Postbuckling Analysis Of Flat Composite Stiffened Panels Loaded In Axial Compression

There is little application of structures which withstand loads higher than buckling load in a lot of design apartments and research centers, although we have to pay weight for structures that are not full used of. It's mainly because current analysis methods can not accurately represent the critical failure mechanisms of stiffened composite structures. Therefore,finite element method analysis of stability of composite stiffened panels is important for airplane structures design.ABAQUS numerical investigations have been conducted into the buckling and post-buckling behavior of composite stiffened panels which subject to compression loaded along axis. Buckling module in ABAQUS was used to simulate buckle behavior. The postbuckling model was consisted of shell elements which were monitored by Hashin criterion and connected by adhesive elements for stiffener-skin interfaces. Risk algorithm and Second Name criterion have been implemented into nonlinear finite element solver to predict the debonding of stiffened panels. The numerical results were compared with experimental to ensure efficiency of this analysis. This work was valuable for control of weight of planes and some other similar research.