| 摘要 |
<p>The invention relates to a process for the production of a component (3, 35), in particular of an angled component (4) for linking a skin of a fuselage cell to a ring frame of an aircraft, where the component (3, 35) is subjected to a forming process along at least two edge lines (7-10, 15-17, 40, 41, 43) by edges of a level cut-to-size section (1, 36), and the cut-to-size section (1, 36) is composed of a thermoplastic reinforced with a plurality of carbon fibre layers. According to the invention, inter-laminar slip of the fibre layers is substantially excluded in a first step of the forming process, whereas in a second step of the forming process an upper tool and a lower tool (25) are used for consolidation of the component (3, 35), i.e. the final shaping through application of pressure on all sides. Complex components (3, 35) with at least two edge lines (7-10, 15-17, 40, 41, 43) can be produced by this method, where they run at angles with respect to one another at from about 0° to 90° - preferably from 30° to 90° - and moreover lie in at least two different planes (21-24, 37-39, 42). The invention also relates to a thermoplastic component (3, 35) reinforced with a plurality of fibre layers and produced by the process, in particular an angled component (4) for the inner linking of a ring frame to a skin of a fuselage shell of an aircraft.</p> |
