Composite material structure for aircraft fuselage and process for manufacturing it

A process for manufacturing a closed composite material structure (1) for aircraft fuselage comprising the following steps:

• a) sequentially arranging the stiffeners (4) on the male jig (2);
• b) laminating the composite material on the surface formed by the male jig (2) and the stiffeners (4) to form the outer panel (3) of the closed structure 1;
• c) placing a hold-down plate (9) on the outer surface of the outer panel (3);
• d) placing the necessary remaining auxiliary elements (13) for the autoclave curing of the composite materials used;
• e) curing the closed structure (1) inside the autoclave in high pressure and temperature conditions;
• f) separating the closed structure (1) from the male jig (2) according to a separation direction (11) and direction (12).