A simple principle of stacking sequence design is presented. The multidelamination-interface design suggests that more possible delamination interfaces between the 0/90 plies should be designed, i.e., the 900 plies are better to be separated, the thickness of the 900 plies is reduced to one ply. Results show that for the symmetric balanced laminate, matrix crack can be suppressed in the CFRP laminate and delayed in the GFRP laminate, and edge delamination will be delayed in the laminate under the static inplane loading. This method stems from the approximate analysis in which the principles of the Linear Elastic Fracture Mechanics are employed. It is also verified by the delamination moment analysis. These results are expected to be extended to the laminate subjected to the impact loading.
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