Reinforcement Design For Composite Lower Wing Panel With A Cutout

The fibers are cut off at the openings of the laminate, which greatly weakens the stiffness andstrength of the structural, and reduces loading capacity of the structure. Therefore, it is important toanalyze the composite laminate with cutout in detail, and take effective measures to strengthen it.This article choses area around the access hole of composite lower wing panel from the aviationstructure as the research model, and studies how to design it, which including the following aspects:1, Introduce the progressive damage analysis based on Hashin failure criterion, the concepts andthe analysis method of the post-buckling stage for composite stiffened panel.2, Use finite element software ABAQUS to establish the initial model of the composite cutoutarea. Simulate laminate layer damage by progressive damage model based on Hashin failure criteria.Obtain tensile loading capability, stability loading capacity and compressive loading capacityrespectively.3, Reinforce of the cutout area by overall thickening, interleave reinforcement and flangereinforcement. Analyze the results of the initial model and three reinforcement models. The resultsshow that, interleave reinforcement, relative to overall thickening, and flange reinforcement, is thebest and lightest method of the three proposals when designing the reinforcement of the cutout area.4, When adjusting the layup proportion of the interleave model, we can find the tensile loadingcapability is improved by raising the percentage of0°layer, which improves the stiffness of thestructure.