| 摘要 |
The invention relates to an aircraft fuselage (1) produced by assembling, at a circumferential joint (5), at least two sections (11a, 11b), each section comprising a coating (12a, 12b) and at least one element of at least one stiffener, the said two elements having a closed cross section and being assembled by a splicing piece (3)(30)(300). The elements (2a, 2b) of the stiffener and the splicing piece (3)(30)(300) are made of composite. Said splicing piece, which has two flanges (34, 35)(102, 112)(303)is fixed to the coatings (12a, 12b) and to the stiffener elements (2a, 2b) by working fastenings (7) positioned only on the flanges (34, 35)(102, 112)(303) of the said splicing piece. |
