| 摘要 |
<p>Aircraft fuselage made out with composite material and manufacturing processes. The structure of the fuselage (1 1 ) comprises a skin (13), a plurality of frames (17) positioned transversely to the longitudinal axis (9) of the fuselage (11) and a plurality of longitudinal stiffening elements (14, 15) that can be either stringers (14) or beams (15), being the ratio between the distance (X) between frames (17) and the distance (Y) between longitudinal stiffening elements (14, 15) is less than one. If the stiffening elements are stringers (14) the manufacturing process is based on assembling the fuselage section (11) joining the skin (13) with the stringers (14) to the frames (17). If the stiffening elements are beams (15) the manufacturing process is based on joining the skin to an internal structure made up with frames (17) and beams (15).</p> |
