Optimal Design Of Composite Material Adhesive-rivet Hybrid Repair

Composite materials have been widely used in aircraft structures, it is easy to cause all kinds of damage and defect during the process of manufacture, transport and service. How to repair these damages and defects to restore the strength and rigidity of structures, so that it can be safely served, needs to be urgently solved. The main repair procedures for composite material structure are adhesive bonding repair, rivet bonding repair and mechanical-adhesive mixed repair, currently among which a little few research is concentrated on the mechanical-adhesive mixed repair.In the thesis, the design of adhesive-rivet hybrid repair procedure for the damaged fuselage skin is made. In order to research the variation of stress and the stress distribution in different adhesive layers, the composite material laminate mechanical-adhesive mixed repair simulation model is built with the application of ANSYS finite element software in this article, then a comparison with adhesive bonding repair which applies the same constraint and load condition is made. The conclusion provides some worthwhile theoretical references for the design of composite material repair procedure. Finally an optimal design for the ply angle in the laminate hybrid repair structure is made with the process of the hybrid repair model and its optimal result analysis, a better laminate ply procedure which is applied to repair is established.The adhesive-rivet hybrid repair procedure which is established in this paper exerts a positive effect on broadening and improving the current composite material repair technology.