Fem Simulation On The Notched Strength Of Composite Laminates

At present, composite laminates have been widely used in the fields of aircraft and aerospace because of its excellent mechanical characteristics and designable. However, we have to add drilling or openings in the composite laminates due to the assembly or the layout needs on the aircraft structure. Openings can cause stress concentration, which has serious effect on the bearing capacity and the life of composite structures. So it has very important significance to research on the notched strength of composite laminates.The former work related to the notched strength of composite laminates has been summarized comprehensively in this thesis. Also, it has summed up many prediction models basing on various hypotheses, analyzed damage mechanism to different types of laminate in this thesis. Considering many former methods depend on experiments, progressive damage method was adopted by means of computer simulation to predict the notched strength of composite laminates in this thesis.Damage mechanism of different ply was analyzed by parametric models created by commercial finite element software. The element stress was analyzed and the damage state was judged by C program. The property of elements which suffered damage should be degenerated according to some certain rules adopted in this paper by C program and script languages. Strength of laminates containing central hole can be calculated by running PCL command to invoke ply information as well as different computer programs which encapsulated in the ISIGHT, a kind of commercial software step by step. Comparing with the experiment value, the result in this paper is satisfying.