METHOD FOR MANUFACTURING A MULTI-RIBBED WING BOX MADE OF COMPOSITE MATERIAL WITH INTEGRATED STIFFENED PANELS

摘要

A method for manufacturing a wing box (10) for aircraft by arranging a first composite panel (12a) comprising a skin (16) having a first side (16') and stringers (18) extending longitudinally; alternately arranging transversally, on said first side a non-polymerized rib (14) , each rib comprising a plate (15), a first pair of flanges (15a) and a second pair of flanges (15b) arranged at opposite ends of said plate by placing the first pair of flanges on said first side of the first panel, and a tool (24) comprising a central part (24a), a bottom part (24b) and a top part (24c), wherein the central part is interposed between said bottom and top parts; arranging a second composite panel (12b) comprising a skin (16), having a first side (16'), and stringers (18) extending longitudinally, by putting said second panel in contact with the second pair of flanges; transversally pulling out the central part of each tool and removing the top and bottom parts; and subjecting the assembly to a curing process.