| 摘要 |
<p>This invention provides a method for producing a structural component, particularly in the aerospace sector. An unhardened prepreg fabric (6) is formed from a composite fibre material, hardenable at a first hardening temperature, into a predetermined shape. The unhardened prepreg fabric (6) is then connected to at least one hardening part (12, 13) of a composite fibre material partially hardened at a second hardening temperature for holding the unhardened prepreg fabric (6) in the predetermined shape, wherein the second hardening temperature is lower than the first hardening temperature. In a further method step the unhardened prepreg fabric (6) connected to the at least one holding part (12, 13) is hardened at the first hardening temperature to form the structural component. The idea on which this invention is based consists in replacing expensive tools of special steel previously used for holding dimensionally unstable prepreg fabrics with at least one holding part (12, 13) of composite fibre materials, wherein the at least one holding part (12, 13) has a lower hardening temperature than the prepreg fabric (6), and can therefore be produced with a lower cost tool.</p> |
