| 摘要 |
Aircraft fuselage frame in composite material with stabilising ribs which, in at least a first sector (31), comprises a frame (9) with an omega-shaped cross-section (11) formed by a top element (23), two webs (25, 25′), two feet (27, 27′) which includes at least one internal rib (41) formed by a top element (43) joined to the top element (23) of the frame (9), a web (45), two flanges (49, 49′) joined to the webs (25, 25′) of the frame (9) and a foot (47) aligned with the feet (27, 27′) of the frame (9). The invention also relates to a manufacturing procedure for the first sector (31) of the frame with stabilised web (10) comprising steps for: a) providing a frame (9) and at least one internal rib (41) with the configurations indicated; b) joining at least said internal rib (41) to the frame (9). |
