Patent ID: 8226870

Claim:
A manufacturing process for manufacturing a rear pressure bulkhead ( 1 ) made of composite material for aircraft fuselage made of a single piece of composite material having a unitary composition throughout said bulkhead, said bulkhead comprising three layers: an outer layer ( 2 ) made of a fiber laminate, an inner layer ( 3 ) made of a fiber laminate and an intermediate layer or core ( 4 ) made of a lightweight material, the laminate of the outer layer ( 2 ) an inner layer ( 3 ) being symmetrical one another, said method comprising the following steps: a) curing the layer of the core ( 4 ) with a planar plate shape; b) heat machining and forming the layer of the core ( 4 ) so that it acquires its final shape; c) stabilizing the layer of the core ( 4 ) so that its shape is not modified during the final curing of the bulkhead ( 1 ); d) laminating the outer and inner laminates ( 2 ), ( 3 ) of the bulkhead ( 1 ) with a fiber placement machine or manually on a male jig on both sides of the layer of the core ( 4 ); and e) curing the assembly of the laminates ( 2 ), ( 3 ) and the core ( 4 ) in an autoclave wherein said bulkhead is able to sufficiently withstand strain and pressurization of the aircraft fuselage without any additional stiffening agents.