Battle Damage Repair and Test of Composite Fuselage Panel with Hat Stringer

In this study, the composite fuselage panel with a hat stringer was taken as the research object. The compression tests of the non-damaged panel, the bonded repair panel and the bolted repair panel were completed. The effects of different repair methods were discussed. The tests verified that the bearing capacity of the panels repaired by adhesive and bolt can reach the strength level of the original structure. Both the bonded repair test specimens and the bolted repair test specimens keep the structure stable under 67% ultimate compression load and the structure does not fail under 100% ultimate load, which meet the design requirements of composite panel for battle damage repair. Compared with non-damaged panel, the ability of bolted repair test to withstand compression load is improved, which is caused by the increase of stiffness in the repair area. The ability of the bonded repair test to withstand the compression load is equivalent to the non-damaged panel.