Method for producing aerospace and space navigation fiber composite material member and molded core

摘要

In a process to manufacture an aircraft fuselage stringer in composite material, an elastic core sleeve is inserted in a profiled case and secured by an external ring clip. The elastic core sleeve is then filled with a packing agent e.g. quartz sand via an inlet (4). The clamp is then released and the form core placed on a backing plate for the carbon fiber and resin layup process. The clamp facilitates the formation of a vacuum on the core sleeve outer surface (1d). The case is a tube with a closed cross-section. The layup is cured by external application of heat and pressure. The form core corners are fitted with metal or plastic gussets (13) to prevent the creation of sharp bends in the fiber layup. The lay-up process uses e.g. hand preparation, prepreg layup, injection press layup, or vacuum infusion. The form core folded cross-section is omega, trapezoidal, triangular ring-shaped and/or corrugated. The form core is a plastic e.g. polyamide or polytetrafluoroethene. Also claimed is a commensurate aircraft fuselage stringer made of composite material.