A METHOD OF MANUFACTURING SINGLE PIECE FUSELAGE BARRELS IN A COMPOSITE MATERIAL

A vacuum bag (18) is placed around the inner forming surface (IML) of an inner mandrel with radially retractable sectors (11a, l ib) 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...

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Bibliographische Detailangaben
Hauptverfasser:	CERRETA PIETRANTONIO, INSERRA IMPARATO SABATO
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	AEROPLANES AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING AIRCRAFT AVIATION COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDEDFOR SHAPING OR JOINING OF PLASTICS TRANSPORTING WORKING OF PLASTICS WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL
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Beschreibung
Zusammenfassung:	A vacuum bag (18) is placed around the inner forming surface (IML) of an inner mandrel with radially retractable sectors (11a, l ib) 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) int