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As an efficient lightweight structure, Composite sandwich panel has been widely used in aerospace industry.  In recent years, several stringers will be reinforced in the core material to achieve a specific strength and stiffness, as well as to increase the reliability of the structure. For such new type of composite sandwich structure, the failure modes and damage mechanism will behave some new forms. The debonding defects of interface between the sheet and core often occur in manufacturing process for composite sandwich structure, moreover, the stringers laid in the sandwich structure will cause a geometric discontinuous of honeycomb core, as well as the discontinuous of load transfer, as a result, this local stress concentration will induce structural easy to be damaged. It is necessary to further research the damage mechanism and corresponding modeling and calculation method in numerical simulation for such complicate structure. This paper investigated the damage and failure behavior of composite sandwich structure with stringer reinforcement under compression. The material damage of core near stringers, the debonding damage of interface between sheet and core, the progressive damage of the composite sheet such as fiber breakage, matrix cracking and fiber/matrix damage were considered in the numerical simulation. The mechanism of damage evolution and the coupling effect of different damages or defects were studied, the failure modes and the whole failure process were obtained by numerical simulation, and some critical damage modes and failure behavior of composite sandwich structure with stringer reinforcement under compression were revealed.

modeling,simulation, numerical methods