A METHOD OF MANUFACTURING SINGLE PIECE FUSELAGE BARRELS IN COMPOSITE MATERIAL

摘要

A vacuum bag (18) is placed around the inner forming surface (IML) of an inner mandrel with radially retractable sectors (11a 11b) having parallel longitudinal slots (17). Stringers (30) of composite material are positioned in the slots (17). A respective elongated inner support (31) is placed in each stringer covered by an impermeable tubular bag (32). A skin (37) of composite material is laminated around the stringers (30) the coated supports (31 32) and the inner forming surface (IML). An outer curing tool (50 51) closes around the skin (37) defining an outer forming surface (OML) for the fuselage barrel leaving an annular gap (G) of predetermined radial width between the outer surface of the skin (37) and the outer forming surface (OML). Vacuum is applied to the volume enclosed between the vacuum bag (18) and the outer tool (50 51) so as to enlarge the diameter of the uncured barrel causing the barrel to be released from the inner mandrel (10) and bringing the outer surface of the skin (37) into contact with the inner surface (OML) of the outer tool (50 51).