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, comprising the stepsof:a1) arranging, on a curing surface (22), a first panel (12a), made of acomposite material,comprising a skin (16) having a first side (16') and a plurality of stringers(18) that extendparallel to a longitudinal direction (x);b) alternately arranging, on said first side (16') of the first panel (12a)along a transversedirection (y), a rib (14), made of non-polymerized composite material - eachrib (14)comprising a plate (15), a first pair of flanges (15a) and a second pair offlanges (15b)arranged at opposite ends of said plate (15) - by placing the first pair offlanges (15a) onsaid first side (16') of the first panel (12a), and a tool (24) - each tool(24) comprising acentral part (24a), a bottom part (24b) and a top part (24c), wherein thecentral part (24a)of each tool (24) is interposed between said bottom part (24b) and said toppart (24c) andmay be extracted in a transverse direction (y) - between each pair ofconsecutive ribs (14)and in contact with both;c) arranging a second panel (12b), made of a composite material, comprising askin (16),having a first side (16'), and a plurality of stringers (18) that extend alonga longitudinaldirection (x), by putting said second panel (12b) in contact with the secondpair of flanges(15b) of each rib (14);d) pulling out the central part (24a) of each tool (24) along the transversedirection (y) andsubsequently removing the top part (24c) and the bottom part (24b) of eachtool (24); ande) subjecting the first panel (12a), the second panel (12b), and each rib (14)to a curingprocess in autoclave with vacuum bag, according to a specific pressure andtemperaturecycle, for curing the non-polymerized components.