Process and assembly to manufacture aircraft skin with integral stringers in composite material using a steel wire removable form core winding

摘要

In a process to manufacture an aircraft fuselage skin panel with integral stringers in composite material (1), a core form (4) is prepared by a spiral steel wire winding to determine the form core outer shape. The pre-shaped core form is covered in by a fiber and resin (3) lay-up on a pre-determined length (14) of the form core, and then exposed to combined heat and pressure. The steel wire is heated during the winding process to prevent distortion by spring action. The form core is covered by a sleeve and a separation foil layer prior to application of carbon fiber and resin. The form core corners are fitted with 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. After fabrication and curing of the skin panel with integral stringers, the form core steel wire is extracted. Further claimed are a commensurate form core and an aircraft fuselage skin panel.