Process to manufacture a composite fiber stringer for an aircraft fuselage

摘要

Claimed is a process to manufacture a composite aerospace component e.g. a fuselage stringer by the insertion of a core sleeve (9) in a tool (2) to determine the outer geometry of a form core (27). The core sleeve is then filled with a material then fixed by vacuum to form the core (27). The core is then encased in semi-finished fibers to form the composite component. The form core material is introduced to the form core either by gravity or by a blower. During introduction of the form core material, the sleeve is maintained in the open presentation by external suction. After filling is complete, the sleeve is released. During the subsequent fixing process, the vacuum is monitored and the values recorded for quality control purposes. During the fixing process, the core material is subject to vibration and/or compacting. The sleeve (9) has strengthened corners and a peel layer. Further claimed is a commensurate composite material aircraft fuselage stringer.